# Advanced Mechanics of Materials [6 ed.] 9780471438816

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Cover......Page 1
Title......Page 2
PREFACE......Page 4
CONTENTS......Page 6
1.1 REVIEW OF ELEMENTARY MECHANICS OF MATERIALS......Page 12
1.2 METHODS OF ANALYSIS......Page 16
1.3 STRESS-STRAIN RELATIONS......Page 19
1.4 FAILURE AND LIMITS ON DESIGN......Page 27
PROBLEMS......Page 33
2.1 DEFINITION OF STRESS AT A POINT......Page 36
2.2 STRESS NOTATION......Page 37
2.3 SYMMETRY OF THE STRESS ARRAY AND STRESS ON AN ARBITRARILY ORIENTED PLANE......Page 39
2.4 TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES......Page 42
2.5 DIFFERENTIAL EQUATIONS OF MOTION
OF A DEFORMABLE BODY......Page 61
2.6 DEFORMATION OF A DEFORMABLE BODY......Page 65
2.7 STRAIN THEORY, TRANSFORMATION OF STRAIN,
AND PRINCIPAL STRAINS......Page 66
2.8 SMALL DISPLACEMENT THEORY......Page 72
2.9 STRAIN MEASUREMENT AND STRAIN ROSElTES......Page 81
PROBLEMS......Page 83
3.1 FIRST LAW OF THERMODYNAMICS, INTERNAL-ENERGY DENSITY, AND COMPLEMENTARY INTERNAL-ENERGY DENSITY......Page 90
3.2 HOOKE’S LAW: ANISOTROPIC ELASTICITY......Page 95
3.3 HOOKE'S LAW: ISOTROPIC ELASTICITY......Page 96
3.4 EQUATIONS OF THERMOELASTICITY FOR ISOTROPIC MATERIALS......Page 102
3.5 HOOKE’S LAW: ORTHOTROPIC MATERIALS......Page 104
PROBLEMS......Page 112
4.1 LIMITATIONS ON THE USE OF UNIAXIAL
STRESS-STRAIN DATA......Page 115
4.2 NONLINEAR MATERIAL RESPONSE......Page 118
4.3 YIELD CRITERIA: GENERAL CONCEPTS......Page 124
4.4 YIELDING OF DUCTILE METALS......Page 128
4.5 ALTERNATIVE YIELD CRITERIA......Page 137
4.6 GENERAL YIELDING......Page 140
PROBLEMS......Page 152
5.1 PRINCIPLE OF STATIONARY POTENTIAL ENERGY......Page 158
5.2 CASTIGLIANO’S THEOREM ON DEFLECTIONS......Page 163
5.3 CASTIGLIANO'S THEOREM ON DEFLECTIONS
FOR LINEAR LOAD-DEFLECTION RELATIONS......Page 166
5.4 DEFLECTIONS OF STATICALLY DETERMINATE
STRUCTURES......Page 174
5.5 STATICALLY INDETERMINATE STRUCTURES......Page 188
PROBLEMS......Page 198
6.1
TORSION OF A PRISMATIC BAR OF CIRCULAR CROSS SECTION......Page 211
6.2 SAINT-VENANT'S SEMI
INVERSE METHOD......Page 220
6.3 LINEAR ELASTIC SOLUTION......Page 224
6.4 THE PRANDTL ELASTIC-MEMBRANE (SOAP-FILM)
ANALOGY......Page 227
6.5 NARROW RECTANGULAR CROSS SECTION......Page 230
6.6 TORSION OF RECTANGULAR CROSS SECTION
MEMBERS......Page 233
6.7 HOLLOW THIN-WALL TORSION MEMBERS AND MULTIPLY CONNECTED CROSS SECTIONS......Page 239
6.8 THIN-WALL TORSION MEMBERS
WITH RESTRAINED ENDS......Page 245
6.9 NUMERICAL SOLUTION OF THE TORSION PROBLEM......Page 250
6.10 INELASTIC TORSION: CIRCULAR CROSS SECTIONS......Page 253
6.11 FULLY PLASTIC TORSION: GENERAL CROSS SECTIONS......Page 261
PROBLEMS......Page 265
7.1 FUNDAMENTALS OF BEAM BENDING......Page 274
7.2
BENDING STRESSES IN BEAMS SUBJECTED TO NONSYMMETRICAL BENDING......Page 283
7.3 DEFLECTIONS OF STRAIGHT BEAMS SUBJECTED
TO NONSYMMETRICAL BENDING......Page 291
7.4 EFFECT OF INCLINED LOADS......Page 295
7.5
FULLY PLASTIC LOAD FOR NONSYMMETRICAL BENDING......Page 296
PROBLEMS......Page 298
8.1 APPROXIMATIONS FOR SHEAR IN THIN-WALL BEAM CROSS SECTIONS......Page 306
8.2 SHEAR FLOW IN THIN-WALL BEAM CROSS SECTIONS......Page 307
8.3 SHEAR CENTER FOR A CHANNEL SECTION......Page 309
8.4 SHEAR CENTER OF COMPOSITE BEAMS FORMED FROM STRINGERS AND THIN WEBS......Page 314
8.5 SHEAR CENTER OF BOX BEAMS......Page 317
PROBLEMS......Page 323
9.1 INTRODUCTION......Page 330
9.2 CIRCUMFERENTIAL STRESSES IN A CURVED BEAM......Page 331
9.3 RADIAL STRESSES IN CURVED BEAMS......Page 344
9.4 CORRECTION OF CIRCUMFERENTIAL STRESSES IN CURVED BEAMS HAVING I, T, OR SIMILAR CROSS SECTIONS......Page 349
9.5 DEFLECTIONS OF CURVED BEAMS......Page 354
9.6 STATICALLY INDETERMINATE CURVED BEAMS:
CLOSED RING SUBJECTED TO A CONCENTRATED LOAD......Page 359
9.7 FULLY PLASTIC LOADS FOR CURVED BEAMS......Page 361
PROBLEMS......Page 363
10.1 GENERAL THEORY......Page 368
10.2
INFINITE BEAM SUBJECTED TO A CONCENTRATED LOAD: BOUNDARY CONDITIONS......Page 371
10.3 INFINITE BEAM SUBJECTED TO A DISTRIBUTED LOAD SEGMENT......Page 380
10.4 SEMIINFINITE BEAM SUBJECTED TO LOADS
AT ITS END......Page 385
10.5 SEMIINFINITE BEAM WITH CONCENTRATED
LOAD NEAR ITS END......Page 387
10.6 SHORT BEAMS......Page 388
10.7 THIN-WALL CIRCULAR CYLINDERS......Page 389
PROBLEMS......Page 395
11.1
BASIC RELATIONS......Page 400
11.2 STRESS COMPONENTS AT SECTIONS FAR FROM ENDS FOR A CYLINDER WITH CLOSED ENDS......Page 403
1 1.3 STRESS COMPONENTS AND RADlAL DISPLACEMENT FOR CONSTANT TEMPERATURE......Page 406
1 1.4 CRITERIA OF FAILURE......Page 410
11.5 FULLY PLASTIC PRESSURE AND AUTOFRETTAGE......Page 416
11.6 CYLINDER SOLUTION FOR TEMPERATURE
CHANGE ONLY......Page 420
11.7 ROTATING DISKS OF CONSTANT THICKNESS......Page 422
PROBLEMS......Page 430
CHAPTER 12. ELASTIC AND INELASTIC
STABILITY OF COLUMNS......Page 434
12.1 INTRODUCTION TO THE CONCEPT OF COLUMN
BUCKLING......Page 435
12.2 DEFLECTION RESPONSE OF COLUMNS TO COMPRESSIVE LOADS......Page 436
12.3 THE EULER FORMULA FOR COLUMNS WITH PINNED ENDS......Page 439
12.4 EULER BUCKLING OF COLUMNS WITH LINEARLY ELASTIC END CONSTRAINTS......Page 447
12.5 LOCAL BUCKLING OF COLUMNS......Page 451
12.6 INELASTIC BUCKLING OF COLUMNS......Page 453
PROBLEMS......Page 461
13.1 INTRODUCTION......Page 468
13.2 STRESS RESULTANTS IN A FLAT PLATE......Page 469
13.3 KINEMATICS: STRAIN-DISPLACEMENT RELATIONS FOR PLATES......Page 472
13.4 EQUILIBRIUM EQUATIONS FOR SMALL-DISPLACEMENT THEORY OF FLAT PLATES......Page 477
13.5 STRESS-STRAIN-TEMPERATURE RELATIONS
FOR ISOTROPIC ELASTIC PLATES......Page 480
13.6 STRAIN ENERGY OF A PLATE......Page 483
13.7 BOUNDARY CONDITIONS FOR PLATES......Page 484
13.8 SOLUTION OF RECTANGULAR PLATE
PROBLEMS......Page 487
13.9 SOLUTION OF CIRCULAR PLATE PROBLEMS......Page 497
PROBLEMS......Page 511
CHAPTER 14. STRESS CONCENTRATIONS......Page 513
14.1 NATURE OF A STRESS CONCENTRATION PROBLEM AND THE STRESS CONCENTRATION FACTOR......Page 515
14.2 STRESS CONCENTRATION FACTORS: THEORY OF ELASTICITY......Page 518
14.3 STRESS CONCENTRATION FACTORS: COMBINED LOADS......Page 526
14.4 STRESS CONCENTRATION FACTORS: EXPERIMENTAL TECHNIQUES......Page 533
14.5 EFFECTIVE STRESS CONCENTRATION FACTORS......Page 541
14.6 EFFECTIVE STRESS CONCENTRATION FACTORS: INELASTIC STRAINS......Page 547
PROBLEMS......Page 550
CHAPTER 15. FRACTURE MECHANICS......Page 554
15.1 FAILURE CRITERIA AND FRACTURE......Page 555
15.2 THE STATIONARY CRACK......Page 562
15.3 CRACK PROPAGATION AND THE STRESS INTENSITY FACTOR......Page 566
15.4 FRACTURE: OTHER FACTORS......Page 572
PROBLEMS......Page 575
CHAPTER 16. FATIGUE: PROGRESSIVE FRACTURE......Page 578
16.1 FRACTURE RESULTING FROM CYCLIC LOADING......Page 579
16.3 EFFECTIVE STRESS CONCENTRATION FACTORS: OTHER INFLUENCES......Page 586
16.4 LOW CYCLE FATIGUE AND THE ε-N RELATION......Page 591
PROBLEMS......Page 596
17.1 INTRODUCTION......Page 600
17.2 THE PROBLEM OF DETERMINING CONTACT STRESSES......Page 601
17.3 GEOMETRY OF THE CONTACT SURFACE......Page 602
17.4 NOTATION AND MEANING OF TERMS......Page 607
17.5 EXPRESSIONS FOR PRINCIPAL STRESSES......Page 608
17.6 METHOD OF COMPUTING CONTACT STRESSES......Page 609
17.7 DEFLECTION OF BODIES IN POINT CONTACT......Page 618
17.8 STRESS FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL TO CONTACT AREA......Page 622
17.9 STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA......Page 624
PROBLEMS......Page 633
18.1 DEFINITION OF CREEP AND THE CREEP CURVE......Page 635
18.3 ONE-DIMENSIONAL CREEP FORMULAS FOR METALS SUBJECTED TO CONSTANT STRESS AND ELEVATED TEMPERATURE......Page 637
18.4 ONE-DIMENSIONAL CREEP OF METALS SUBJECTED TO VARIABLE STRESS AND TEMPERATURE......Page 642
18.5 CREEP UNDER MULTIAXIAL STATES OF STRESS......Page 651
18.6 FLOW RULE FOR CREEP OF METALS SUBJECTED TO MULTIAXIAL STATES OF STRESS......Page 654
18.7 AN APPLICATION OF CREEP OF METALS......Page 660
18.8 CREEP OF NONMETALS......Page 661
APPENDIX A. AVERAGE MECHANICAL PROPERTIES OF SELECTED MATERIALS......Page 667
AUTHOR INDEX......Page 670
SUBJECT INDEX......Page 682
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##### Citation preview

SIXTH EDITION

ADVANCED MECHANICS OF MATERIALS ARTHUR P. BORES1 Professor Emeritus Civil and Architectural Engineering The University of Wyoming at Laramie and Professor Emeritus Theoretical and Applied Mechanics University of Illinois at Urbana-Champaign

RICHARD J. SCHMIDT Professor Civil and Architectural Engineering The University of Wyoming at Laramie

JOHN WILEY & SONS, INC.

Acquisitions Editor Joseph Hayton Marketing Manager Katherine Hepburn Senior Production Editor Valerie A . Vargas Karin Kincheloe Senior Designer Production Management Services Argosy This book was set in 10/12 Times Roman by Argosy and printed and bound by Hamilton Printing. The cover was printed by Lehigh Press. This book is printed on acid-free paper.

00

Copyright 2003 0 John Wiley & Sons, Inc. All rights reserved. No part of this publication may be reproduced, stored in a retrieval system, or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, scanning, or otherwise, except as permitted under Sections 107 or 108 of the 1976 United States Copyright Act, without either the prior written permission of the Publisher, or authorization through payment of the appropriate per-copy fee to the Copyright Clearance Center, 222 Rosewood Drive, Danvers, MA 01923, (978) 750-8400, fax (978) 750-4470. Requests to the Publisher for permission should be addressed to the Permissions Department, John Wiley & Sons, Inc., 111 River Street, Hoboken, NJ 07030, (201) 748-6000, fax (201) 748-6088, e-mail: [email protected] To order books please call 1 (800) 225-5945.

Library of Congress Cataloging in Publication Data: Boresi, Arthur P. (Arthur Peter), 1924Advanced mechanics of materials /Arthur P. Boresi, Richard J. Schmidt.4th ed. p. cm. Includes bibliographicalreferences and index. ISBN 0-471-43881-2 (cloth : alk. paper) 1. Strength of materials. I. Schmidt, Richard J. (Richard Joseph), 1954- 11. Title. TA405 .B66 2002 620.1'12--d~21 2002026738

ISBN 978-0-471-43881-6

Printed in the United States of America 10987

PREFACE

This book is written as a text for advanced undergraduates and graduate students in aerospace, civil, and mechanical engineering and applied mechanics. It is also intended as a reference for practitioners. The book contains topics sufficient for two academic semesters or three quarters. Thus, there is enough variety that instructors of a one-semester course or one- or two-quarter courses can choose topics of interest to students.

New to this Edition In this sixth edition, we have attempted to thoroughly review the fifth edition with the intention of clarifying and condensing the presentation, updating many of the examples and homework problems, and adding selected new topics. In the face of these additions, we have also attempted to control the growth in size of the book. Such is a difficult task. Based on a survey of the market, the final chapter, finite element methods, has been removed from the book and is available at no cost from the book Web site: http:llwww.wiley.comlcollegelboresi. Those topics that we have retained are presented with detail and precision, as in previous editions of the book. Throughout the revision process, the philosophy of previous editions has been maintained. That is, we have attempted to develop the topics from basic principles so that the applicability and limitations of the methods are clear. Without an understanding of the underlying principles and assumptions upon which analysis methods are based, users of those methods may be limited to application of the methods to known problems. Furthermore, they may not have the necessary understanding to extend or adapt the theories and developments to their own applications. Hence, we regard concepts and fundamentals as no less important than application of solution methods in problem solving.

Organization In Chapter 1 basic concepts of one-dimensional load-stress, load-deflection, and stress-strain diagrams are introduced. A discussion of the tension test and associated material properties is presented, followed by a brief introduction to failure theories. Theories of stress and strain follow in Chapter 2. Definitions of the stress tensor and various stress quantities are developed from detailed examination of equilibrium conditions for a body. Likewise, definitions of strain are developed from a consideration of deformation of a body. Here, the independence and similarity of the theories of stress and strain become evident. Chapter 3 joins the theories of stress and strain by the theory of linear stress-strain-temperature relations, based upon the requirements of the first law of thermodynamics. Stress-strain relations and material constants for anisotropic, orthotropic, and isotropic materials are discussed. Yield theory is developed in Chapter 4. Starting with one-dimensional stress-strain behavior, the concepts of yield criteria, yield functions, and yield surfaces are developed to describe nonlinear material response for multiaxial stress states. The von Mises and Tresca criteria are discussed and compared in detail. The application of energy methods, Chapter 5, includes a discussion of the dummy load method and its relation to the Castigliano method.

vii

viii

PREFACE

Chapters 6-12 treat classical topics in mechanics of materials. That is, these chapters use fundamental concepts of equilibrium, compatibility conditions, constitutive relations, and material response to study the behavior of selected mechanical and structural members. Specifically, the following topics are considered: torsion, nonsymmetrical bending, shear center, curved beams, beams on elastic foundations, thick-wall cylinders, and column stability. Key kinematic and material response assumptions are emphasized in order to highlight the applicability and limitations of the analysis methods. Chapters 13-18 contain selected topics that are not generally treated by the mechanics of materials method, but are nevertheless areas of interest and advanced study for practicing engineers. This part of the book contains a mix of topics involving both behavior of structural and mechanical systems (flat plates, stress concentrations, and contact stresses) as well as detailed study of material behavior (fracture mechanics and fatigue).

Acknowledgments We thank Joe Hayton, Engineering Editor at Wiley, for his help and advice during the development of this edition. In addition, we also appreciate the help of Valerie Vargas, Production Editor, Adriana Lavergne at Argosy for work on composition, and David Wood at Wellington Studios for work on the illustration program. We acknowledge the help of the following reviewers, who offered useful insights into developing this edition: Abhijit Bhattacharyya, University of Alberta Bill Y. J. Chao, University of South Carolina Ali Fatemi, University of Toledo Stephen Folkman, Utah State University Stephen M. Heinrich, Marquette University Thomas Lacy, Wichita State University Craig C. Menzemer, University of Akron James A. Nemes, McGill University Steven O’Hara, Oklahoma State University Pizhong Qiao, University of Akron Robert Yuan, University of Texas-Arlington

Supplements Instructors who adopt the book for their courses may access solutions to the homework problems from the John Wiley & Sons Web site: http://www.wiley.com/ collegelboresi.Contact your local sales representative for additional details. Finally, we welcome comments, suggestions, questions, and corrections that you might wish to offer. Send your remarks to Dr. Arthur P. Boresi, Department of Civil and Architectural Engineering, University of Wyoming, Laramie, WY 8207 1-3295.

CONTENTS CHAPTER 1

1.1

1.2

1.3

1.4

INTRODUCTION

2.7

1

Review of Elementary Mechanics of Materials 1 1.1.1 Axially Loaded Members 1 1.1.2 Torsionally Loaded Members 3 1.1.3 Bending of Beams 3 Methods of Analysis 5 1.2.1 Method of Mechanics of Materials 6 1.2.2 Method of Continuum Mechanics and the Theory of Elasticity 7 1.2.3 Deflections by Energy Methods 7 Stress-Strain Relations 8 1.3.1 Elastic and Inelastic Response of a Solid 8 1.3.2 Material Properties 10 Failure and Limits on Design 16 1.4.1 Modes of Failure 19 Problems 22 References 24

2.8

2.9

CHAPTER 3

RELATIONS 3.1

CHAPTER 2

THEORIES OF STRESS AND STRAIN

25

~~~~~~

2.1 2.2 2.3

2.4

2.5

2.6

Definition of Stress at a Point 25 Stress Notation 26 Symmetry of the S t r e s s h a y and Stress on an Arbitrarily Oriented Plane 28 2.3.1 Symmetry of Stress Components 28 2.3.2 Stresses Acting on Arbitrary Planes 29 2.3.3 Normal Stress and Shear Stress on an Oblique Plane 30 Transformation of Stress, Principal Stresses, and Other Properties 31 2.4.1 Transformation of Stress 31 2.4.2 Principal Stresses 32 2.4.3 Principal Values and Directions 33 2.4.4 Octahedral Stress 36 2.4.5 Mean and Deviator Stresses 37 2.4.6 Plane Stress 38 2.4.7 Mohr’s Circle in Two Dimensions 40 2.4.8 Mohr’s Circles in Three Dimensions 43 Differential Equations of Motion of a Deformable Body 50 2.5.1 Specialization of Equations 2.46 52 Deformation of a Deformable Body 54

Strain Theory, Transformation of Strain, and Principal Strains 55 2.7.1 Strain of a Line Element 55 2.7.2 Final Direction of a Line Element 57 2.7.3 Rotation Between Two Line Elements (Definition of Shear Strain) 58 2.7.4 Principal Strains 60 Small-DisplacementTheory 61 2.8.1 Strain Compatibility Relations 62 2.8.2 Strain-Displacement Relations for Orthogonal Curvilinear Coordinates 63 Strain Measurement and Strain Rosettes 70 Problems 72 References 78

3.2 3.3

3.4 3.5

79

First Law of Thermodynamics, Internal-EnergyDensity, and Complementary Internal-Energy Density 79 3.1.1 Elasticity and Internal-Energy Density 81 3.1.2 Elasticity and Complementary Internal-Energy Density 82 Hooke’s Law: Anisotropic Elasticity 84 Hooke’s Law: Isotropic Elasticity 85 3.3.1 Isotropic and Homogeneous Materials 85 3.3.2 Strain-Energy Density of Isotropic Elastic Materials 85 Equations of Thennoelasticity for Isotropic Materials 91 Hooke’s Law: Orthotropic Materials 93 Problems 101 References 103

CHAPTER 4

4.1

LINEAR STRESS-STRAIN-TEMPERATURE

INELASTIC MATERIAL. BEHAVIOR

104

Limitations on the Use of Uniaxial Stress-Strain Data 104 4.1.1 Rate of Loading 105 4.1.2 Temperature Lower Than Room Temperature 105 4.1.3 Temperature Higher Than Room Temperature 105

ix

X

4.2 4.3

4.4

4.5

4.6

CONTENTS

4.1.4 Unloading and Load Reversal 105 4.1.5 Multiaxial States of Stress 106 Nonlinear Material Response 107 4.2.1 Models of Uniaxial StressStrain Curves 108 Yield Criteria: General Concepts 113 4.3.1 Maximum Principal Stress Criterion 114 4.3.2 Maximum Principal Strain Criterion 116 4.3.3 Strain-Energy Density Criterion 116 Yielding of Ductile Metals 117 4.4.1 Maximum Shear-Stress (Tresca) Criterion 118 4.4.2 Distortional Energy Density (von Mises) Criterion 120 4.4.3 Effect of Hydrostatic Stress and the z-Plane 122 Alternative Yield Criteria 126 4.5.1 Mohr-Coulomb Yield Criterion 126 4.5.2 Drucker-Prager Yield Criterion 128 4.5.3 Hill’s Criterion for Orthotropic Materials 128 General Yielding 129 4.6.1 Elastic-Plastic Bending 131 4.6.2 Fully Plastic Moment 132 4.6.3 Shear Effect on Inelastic Bending 134 4.6.4 Modulus of Rupture 134 4.6.5 Comparison of Failure Criteria 136 4.6.6 Interpretation of Failure Criteria for General Yielding 137 Problems 142 References 146

CHAPTER 5

5.1 5.2 5.3

5.4

5.5

6.2

147

Principle of Stationary Potential Energy 147 Castigliano’sTheorem on Deflections 152 Castigliano’sTheorem on Deflections for Linear Load-Deflection Relations 155 5.3.1 Strain Energy U, for Axial Loading 156 5.3.2 Strain Energies U, and Us for Beams 158 5.3.3 Strain Energy U, for Torsion 160 Deflections of Statically Determinate Structures 163 5.4.1 Curved Beams Treated as Straight Beams 165 5.4.2 Dummy Load Method and Dummy Unit Load Method 170 Statically Indeterminate Structures 177 5.5.1 Deflections of Statically Indeterminate Structures 180 Problems 187 References 199

CHAPTER 6

6.1

APPLICATIONS OF ENERGY METHODS

TORSION

6.2.2

Stresses at a Point and Equations of Equilibrium 210 6.2.3 Boundary Conditions 211 6.3 Linear Elastic Solution 213 6.3.1 Elliptical Cross Section 214 6.3.2 Equilateral Triangle Cross Section 215 6.3.3 Other Cross Sections 216 6.4 The Prandtl Elastic-Membrane (Soap-Film)Analogy 216 6.4.1 Remark on Reentrant Corners 219 6.5 Narrow Rectangular Cross Section 219 6.5.1 Cross Sections Made Up of Long Narrow Rectangles 221 Torsion of Rectangular Cross Section Members 222 6.6 Hollow Thin-Wall Torsion Members and Multiply 6.7 Connected Cross Sections 228 6.7.1 Hollow Thin-Wall Torsion Member Having Several Compartments 230 Thin-Wall Torsion Members with Restrained 6.8 Ends 234 6.8.1 I-Section Torsion Member Having One End Restrained from Warping 235 6.8.2 Various Loads and Supports for Beams in Torsion 239 Numerical Solution of the Torsion Problem 239 6.9 6.10 Inelastic Torsion: Circular Cross Sections 243 6.10.1 Modulus of Rupture in Torsion 244 6.10.2 Elastic-Plastic and Fully Plastic Torsion 244 6.10.3 Residual Shear Stress 246 Fully Plastic Torsion: General Cross Sections 250 6.1 Problems 254 References 262 CHAPTER 7

7.1

7.2

200

Torsion of a Prismatic Bar of Circular Cross Section 6.1.1 Design of Transmission Shafts 204 Saint-Venant’s Semiinverse Method 209 6.2.1 Geometry of Deformation 209

200

BENDING OF STRAIGHT BEAMS

Fundamentals of Beam Bending 263 7.1.1 Centroidal Coordinate Axes 263 7.1.2 Shear Loading of a Beam and Shear Center Defined 264 7.1.3 Symmetrical Bending 265 7.1.4 Nonsymmetrical Bending 268 7.1.5 Plane of Loads: Symmetrical and Nonsymmetrical Loading 268 Bending Stresses in Beams Subjectedto Nonsymmetrical Bending 272 7.2.1 Equations of Equilibrium 272 7.2.2 Geometry of Deformation 273 7.2.3 StressStrain Relations 273 7.2.4 Load-Stress Relation for Nonsymmetrical Bending 273 7.2.5 Neutral Axis 274 7.2.6 More Convenient Form for the Flexure Stress O,,

7.3

263

275

Deflections of Straight Beams Subjected to Nonsymmetrical Bending 280

xi

CONTENTS

7.4 7.5

Effect of Inclined Loads 284 Fully Plastic Load for Nonsymmetrical Bending Problems 287 References 294

10.5 285

10.6 10.7

SHEAR CENTER FOR THIN-WALL BEAM CROSS SECTIONS 295

CHAPTER 8

8.1 8.2 8.3 8.4 8.5

Approximationsfor Shear in Thin-Wall Beam Cross Sections 295 Shear Flow in Thin-Wall Beam Cross Sections 296 Shear Center for a Channel Section 298 Shear Center of Composite Beams Formed from Stringers and Thin Webs 303 Shear Center of Box Beams 306 Problems 312 References 318

CHAPTER 9

9.1 9.2 9.3

9.4

9.5 9.6 9.7

Introduction 319 Circumferential Stresses in a Curved Beam 320 9.2.1 Location of Neutral Axis of Cross Section 326 Radial Stresses in Curved Beams 333 9.3.1 Curved Beams Made from Anisotropic Materials 334 Correction of CircumferentialStresses in Curved Beams Having I, T, or Similar Cross Sections 338 9.4.1 Bleich's Correction Factors 340 Deflections of Curved Beams 343 9.5.1 Cross Sections in the Form of an I, T, etc. 346 Statically Indeterminate Curved Beams: Closed Ring Subjected to a Concentrated Load 348 Fully Plastic Loads for Curved Beams 350 9.7.1 Fully Plastic Versus Maximum Elastic Loads for Curved Beams 351 Problems 352 References 356

CHAPTER 10

10.1 10.2

10.3

10.4

BEAMS ON ELASTIC FOUNDATIONS

CHAPTER 1'1

11.1

11.2

11.3

CURVED BEAMS 319

Semiinfinite Beam with Concentrated Load Near Its End 376 ShortBeams 377 Thin-Wall Circular Cylinders 378 Problems 384 References 388

11.4

11.5 11.6

11.7

THE THICK-WALL CYLINDER 389

Basic Relations 389 11.1.1 Equation of Equilibrium 391 11.1.2 Strain-Displacement Relations and Compatibility Condition 391 11.1.3 Stress-Strain-Temperature Relations 392 11.1.4 Material Response Data 392 Stress Components at Sections Far from Ends for a Cylinder with Closed Ends 392 11.2.1 Open Cylinder 394 Stress Components and Radial Displacement for Constant Temperature 395 11.3.1 Stress Components 395 11.3.2 Radial Displacement for a Closed Cylinder 396 11.3.3 Radial Displacement for an Open Cylinder 396 Criteria of Failure 399 11.4.1 Failure of Brittle Materials 399 11.4.2 Failure of Ductile Materials 400 11.4.3 Material Response Data for Design 400 11.4.4 Ideal Residual Stress Distributions for Composite Open Cylinders 401 Fully Plastic Pressure and Autofrettage 405 Cylinder Solution for Temperature Change Only 409 11.6.1 Steady-StateTemperature Change (Distribution) 409 11.6.2 Stress Components 410 Rotating Disks of Constant Thickness 411 Problems 419 References 422

357

General Theory 357 Infinite Beam Subiected to a Concentrated Load: Boundary Conditions 360 10.2.1 Method of Superposition 363 10.2.2 Beam Supported on Equally Spaced Discrete Elastic Supports 364 Infinite Beam Subjected to a Distributed Load Segment 369 10.3.1 Uniformly Distributed Load 369 10.3.2 P L ' I z 371 10.3.3 PL'+ m 371 10.3.4 Intermediate Values of PL' 371 10.3.5 Triangular Load 371 SemiinfiniteBeam Subjected to Loads at Its End 374

CHAPTER 12 ELASTIC AND INELASTIC STABILITY OF COLUMNS 423

12.1 12.2

12.3

Introduction to the Concept of Column Buckling Deflection Response of Columns to Compressive Loads 425 12.2.1 Elastic Buckling of an Ideal Slender Column 425 12.2.2 Imperfect Slender Columns 427 The Euler Formula for Columns with Pinned Ends 12.3.1 The Equilibrium Method 428 12.3.2 Higher Buckling Loads; n > 1 431 12.3.3 The Imperfection Method 432 12.3.4 The Energy Method 433

424

428

xii 12.4 12.5 12.6

CONTENTS

Euler Buckling of Columns with Linearly Elastic End Constraints 436 Local Buckling of Columns 440 Inelastic Buckling of Columns 442 12.6.1 Inelastic Buckling 442 12.6.2 Two Formulas for Inelastic Buckling of an Ideal Column 443 12.6.3 Tangent-Modulus Formula for an Inelastic Buckling Load 444 12.6.4 Direct Tangent-Modulus Method 446 Problems 450 References 455

13.9.9 13.9.10 13.9.1 1

13.9.12

Problems 500 References 501 CHAPTER 14

CHAPTER 13

13.1 13.2 13.3

13.4 13.5

13.6 13.7 13.8

13.9

FLAT PLATES 457

Introduction 457 Stress Resultants in a Flat Plate 458 Kinematics: Strain-Displacement Relations for Plates 461 13.3.1 Rotation of a Plate Surface Element 464 Equilibrium Equations for Small-Displacement Theory of Flat Plates 466 Stress-Strain-Temperature Relations for Isotropic Elastic Plates 469 13.5.1 Stress Components in Terms of Tractions and Moments 472 13.5.2 Pure Bending of Plates 472 Strain Energy of a Plate 472 Boundary Conditions for Plates 473 Solution of Rectangular Plate Problems 476 Solutionof = g for a Rectangular 13.8.1 Plate 477 D 13.8.2 Westergaard Approximate Solution for Rectangular Plates: Uniform Load 479 Deflection of a Rectangular Plate: 13.8.3 Uniformly Distributed Load 482 Solution of Circular Plate Problems 486 Solution of v 2 v 2 W = g for a Circular 13.9.1 Plate 486 D Circular Plates with Simply Supported 13.9.2 Edges 488 Circular Plates with Fixed Edges 488 13.9.3 Circular Plate with a Circular Hole at the 13.9.4 Center 489 Summary for Circular Plates with Simply 13.9.5 Supported Edges 490 Summary for Circular Plates with Fixed 13.9.6 Edges 491 Summary for Stresses and Deflections in 13.9.7 Flat Circular Plates with Central Holes 492 Summary for Large Elastic Deflections of 13.9.8 Circular Plates: Clamped Edge and Uniformly Distributed Load 492

Significant Stress When Edges Are Clamped 495 Load on a Plate When Edges Are Clamped 496 Summary for Large Elastic Deflections of Circular Plates: Simply Supported Edge and Uniformly Distributed Load 497 Rectangular or Other Shaped Plates with Large Deflections 498

14.1 14.2

14.3

vzvZw

14.4

14.5

STRESS CONCENTRATIONS 502

Nature of a Stress Concentration Problem and the Stress ConcentrationFactor 504 Stress ConcentrationFactors: Theory of Elasticity 507 14.2.1 Circular Hole in an Infinite Plate Under Uniaxial Tension 507 14.2.2 Elliptic Hole in an Infinite Plate Stressed in a Direction Perpendicular to the Major Axis of the Hole 508 14.2.3 Elliptical Hole in an Infinite Plate Stressed in the Direction Perpendicular to the Minor Axis of the Hole 511 14.2.4 Crack in a Plate 512 14.2.5 Ellipsoidal Cavity 512 14.2.6 Grooves and Holes 513 Stress Concentration Factors: Combined Loads 515 14.3.1 Infinite Plate with a Circular Hole 515 14.3.2 Elliptical Hole in an Infinite Plate Uniformly Stressed in Directions of Major and Minor Axes of the Hole 516 14.3.3 Pure Shear Parallel to Major and Minor Axes of the Elliptical Hole 516 14.3.4 Elliptical Hole in an Infinite Plate with Different Loads in Two Perpendicular Directions 517 14.3.5 Stress Concentration at a Groove in a Circular Shaft 520 Stress ConcentrationFactors: Experimental Techniques 522 14.4.1 Photoelastic Method 522 14.4.2 Strain-Gage Method 524 14.4.3 Elastic Torsional Stress Concentration at a Fillet in a Shaft 525 14.4.4 Elastic Membrane Method: Torsional Stress concentration 525 14.4.5 Beams with Rectangular Cross Sections 527 Effective Stress ConcentrationFactors 530 14.5.1 Definition of Effective Stress Concentration Factor 530 14.5.2 Static Loads 532 14.5.3 Repeated Loads 532

CONTENTS

14.5.4 14.5.5

14.6

Residual Stresses 534 Very Abrupt Changes in Section: Stress Gradient 534 14.5.6 Significance of Stress Gradient 535 14.5.7 Impact or Energy Loading 536 Effective Stress Concentration Factors: Inelastic Strains 536 14.6.1 Neuber’s Theorem 537 Problems 539 References 541

CHAPTER 15

15.1

15.2

15.3

15.4

16.2 16.3

16.4

FATIGUE: PROGRESSNE FRACTURE

CHAPTER 17

17.1 17.2 17.3

17.4 17.5 17.6

17.7 17.8

17.9

567

Fracture Resulting from Cyclic Loading 568 16.1.1 Stress Concentrations 573 Effective Stress Concentration Factors: Repeated Loads 575 Effective Stress Concentration Factors: Other Influences 575 16.3.1 Corrosion Fatigue 575 16.3.2 Effect of Range of Stress 577 16.3.3 Methods of Reducing Harmful Effects of Stress Concentrations 577 Low Cycle Fatigue and the E-N Relation 580 16.4.1 Hysteresis Loop 580

Fatigue-Life Curve and the E-N Relation 581

Problems 585 References 588

543

Failure Criteria and Fracture 544 15.1.1 Brittle Fracture of Members Free of Cracks andFlaws 545 15.1.2 Brittle Fracture of Cracked or Flawed Members 545 The Stationary Crack 551 15.2.1 Blunt Crack 553 15.2.2 Sharpcrack 554 Crack Propagation and the Stress Intensity Factor 555 15.3.1 Elastic Stress at the Tip of a Sharp Crack 555 15.3.2 Stress Intensity Factor: Definition and Derivation 556 15.3.3 Derivation of Crack Extension Force G 556 15.3.4 Critical Value of Crack Extension Force 558 Fracture: Other Factors 561 15.4.1 Elastic-Plastic Fracture Mechanics 562 15.4.2 Crack-Growth Analysis 562 15.4.3 Load Spectra and Stress History 562 15.4.4 Testing and Experimental Data Interpretation 563 Problems 564 References 565

CHAPTER 16

16.1

FRACTURE MECHANICS

16.4.2

xiii

CONTACT STRESSES

589

Introduction 589 The Problem of Determining Contact Stresses 590 Geometry of the Contact Surface 591 17.3.1 FundamentalAssumptions 591 17.3.2 Contact Surface Shape After Loading 592 17.3.3 Justification of Eq. 17.1 592 17.3.4 Brief Discussion of the Solution 595 Notation and Meaning of Terms 596 Expressions for Principal Stresses 597 Method of Computing Contact Stresses 598 17.6.1 Principal Stresses 598 17.6.2 Maximum Shear Stress 599 17.6.3 Maximum Octahedral Shear Stress 599 17.6.4 Maximum Orthogonal Shear Stress 599 17.6.5 Curves for Computing Stresses for Any Value of BIA 605 Deflection of Bodies in Point Contact 607 17.7.1 Significance of Stresses 611 Stress for Two Bodies in Line Contact: Loads Normal to Contact Area 611 17.8.1 Maximum Principal Stresses: k = 0 613 17.8.2 Maximum Shear Stress: k = 0 613 17.8.3 Maximum Octahedral Shear Stress: k = O 613 Stresses for Two Bodies in Line Contact: Loads Normal and Tangent to Contact Area 613 17.9.1 Roller on Plane 614 17.9.2 Principal Stresses 616 17.9.3 Maximum Shear Stress 617 17.9.4 Maximum Octahedral Shear Stress 617 17.9.5 Effect of Magnitude of Friction Coefficient 618 17.9.6 Range of Shear Stress for One Load Cycle 619 Problems 622 References 623

CHAPTER 18 CREEP: TIME-DEPENDENT DEFORMATION 624

18.1 18.2 18.3

Definition of Creep and the Creep Curve 624 The Tension Creep Test for Metals 626 One-DimensionalCreep Formulas for Metals Subjected to Constant Stress and Elevated Temperature 626

XiV

18.4

18.5 18.6

18.7 18.8

CONTENTS

One-Dimensional Creep of Metals Subjected to Variable Stress and Temperature 631 18.4.1 Preliminary Concepts 631 18.4.2 Similarity of Creep Curves 633 18.4.3 Temperature Dependency 635 18.4.4 Variable Stress and Temperature 635 Creep Under Multiaxial States of Stress 640 18.5.1 General Discussion 640 Flow Rule for Creep of Metals Subjected to Multiaxial States of stress 643 18.6.1 Steady-State Creep 644 18.6.2 Nonsteady Creep 648 An Application of Creep of Metals 649 18.7.1 Summary 650 Creep of Nonmetals 650 18.8.1 Asphalt 650 18.8.2 Concrete 651 18.8.3 Wood 652 References 654

AVERAGE MECHANICAL PROPERTIES OF SELECTED MATERIALS 657

APPENDIX A

SECOND MOMENT (MOMENT OF INERTIA) OF A PLANE AREA 660

APPENDIX 8

B. 1 B.2 B.3

Moments of Inertia of a Plane Area 660 Parallel Axis Theorem 661 TransformationEquations for Moments and Products of Inertia 664 B.3.1 Principal Axes of Inertia 665 Problems 666

APPENDIX C

SECTIONS

PROPERTIES OF STEEL CROSS 668

AUTHOR tNDEX

673

SUBJECT INDEX

676

CHAPTER

I

INTRODUCTION I I n this chapter, we present general concepts and definitions that are fundamental to many of the topics discussed in this book. The chapter serves also as a brief guide and introduction to the remainder of the book. You may find it fruitful to refer to this chapter, from time to time, in conjunction with the study of topics in other chapters.

1.I REVIEW OF ELEMENTARY MECHANICS OF MATERIALS Engineering structures and machines, such as airplanes, automobiles, bridges, spacecraft, buildings, electric generators, gas turbines, and so forth, are usually formed by connecting various parts or members. In most structures or machines, the primary function of a member is to support or transfer external forces (loads) that act on it, without failing. Failure of a member may occur when it is loaded beyond its capacity to resist fracture, general yielding, excessive deflection, or instability (see Section 1.4). These types of failure depend on the nature of the load and the type of member. In elementary mechanics of materials, members subjected to axial loads, bending moments, and torsional forces are studied. Simple formulas for the stress and deflection of such members are developed (Gere, 2001). Some of these formulas are based on simplifying assumptions and as such must be subjected to certain restrictions when extended to new problems. In this book, many of these formulas are used and extended to applications of more complex problems. But first we review, without derivation, some of the basic formulas from mechanics of materials and highlight the limitations to their application. We include a review of bars under axial load, circular rods subjected to torsion, and beams loaded in shear and bending. In the equations that follow, dimensions are expressed in terms of force [F], length [L], and radians [rad].

1.1.1 Axially Loaded Members Figure 1.1 represents an axially loaded member. It could consist of a rod, bar, or tube,' or it could be a member of more general cross section. For such a member, the following elementary formulas apply:

'A rod or bar is considered to be a straight member with a solid cross section. A tube is a straight, hollow cylinder.

1

2

CHAPTER 1 INTRODUCTION

, , ,Cross-sectional area A

yl

l---L---leL FIGURE 1.1 Axially loaded member.

Axial stress a away from the ends of the member2

a=

A

[F/L2]

Elongation e of the member

Axial strain E in the member

In the above formulas: P [F] is the axial load, A [L2]is the cross-sectional area of the member, L [L] is the length of the member, and E [F/L2]is the modulus of elasticity of the material of the member. Restrictions i. The member must be prismatic (straight and of constant cross section). ii. The material of the member must be homogeneous (constant material properties at all points throughout the member). iii. The load P must be directed axially along the centroidal axis of the member. iv. The stress and strain are restricted to the linearly elastic range (see Figure 1.2).

Strain E

FIGURE 1.2

Linear stress-strain relation.

*At the ends, generally depending on how the load P is applied, a stress concentration may exist.

REVIEW OF ELEMENTARY MECHANICS OF MATERIALS

1.1

3

1.1.2 Torsionally Loaded Members Figure 1.3 represents a straight torsional member with a circular cross section and radius r. Again the member could be a rod, bar, or tube. For such a member, the following elementary formulas apply: Shear stress zin the member T =

2 J

[F/L2]

Rotation (angle of twist) y o f the cross section B relative to cross sectionA

y =

GJ

Shear strain y at a point in the cross section

y = p Y = I L G In the above formulas (see Figure 1.3):

T [FL] is the torque or twisting moment, p [L] is the radial distance from the center 0 of the member to the point of interest, J [L4]is the polar moment of inertia of the cross section, L [L] is the length of the member between A and B, and G [F/L2]is the shear modulus of elasticity (also known as the modulus of rigidity) of the material. Restrictions i. The member must be prismatic and have a circular cross section. ii. The material of the member must be homogeneous and linearly elastic. iii. The torque T is applied at the ends of the member and no additional torque is applied between sections A and B. Also, sections A and B are remote from the member ends. iv. The angle of twist at any cross section of the member is small.

1.I.3 Bending of Beams A beam is a structural member whose length is large compared to its cross-sectional dimensions and is loaded by forces and/or moments that produce deflections perpendicular to its longitudinal axis. Figure 1.4a represents a beam of rectangular cross section

FIGURE 1.3 Circular torsion member.

4

CHAPTER 1 INTRODUCTION

FIGURE 1.4 (a)Rectangular cross-section beam. ( b )Section of length x.

subjected to forces and moments. A free-body diagram of a portion of the beam is shown in Figure 1.4b. For such a member, the following elementary formulas apply: Stress 0acting normal to the cross section of the member at section x (1.7)

The displacement v in the y direction is found from the differential expression d-2-v - M(x) dx2

Ez

Shear stress z in the cross section at x for y = y 1 (see Figure 1.5) (1.9) In the above formulas (see Figures 1.4a, 1.4b, and 1.5): M(x) [FL] is the positive bending moment at section x in the member, y [L] is the vertical coordinate, positive upward, from the centroid to the point of interest, I [L4]is the moment of inertia of the cross section, E [F/L2] is the modulus of elasticity of the material of the member,

V(x) [F] is the shear force at section x in the member, Q [L3] is the first moment of the cross-sectional area (shaded in Figure 1.5) above the level y = y l and is given by y = a12

Q =

5

Y =YI

a/2

y d A = f y b d y = b(a2-4y:) 8

I".[

(1.10)

YI

and b [L] is the width of the beam cross section at the level y = y l . Restrictions i. Equation 1.7 is limited to bending relative to principal axes and to linear elastic material behavior. ii. Equation 1.8 is applicable only to small deflections, since only then is d 2 v / d x 2 a good approximation for the curvature of the beam.

1 9

FIGURE 1.5

METHODS OF ANALYSIS

5

Beam cross section.

iii. Equations 1.9 and 1.10 are restricted to bending of beams of rectangular cross section relative to principal axes.

1.2

METHODS OF ANALYSIS In this book, we derive relations between load and stress or between load and deflection for a system or a component (a member) of a system. Our starting point is a description of the loads on the system, the geometry of the system (including boundary conditions), and the properties of the material in the system. Generally the load-stress relations describe either the distributions of normal and shear stresses on a cross section of the member or the stress components that act at a point in the member. For a given member subjected to prescribed loads, the load-stress relations are based on the following requirements: 1. The equations of equilibrium (or equations of motion for bodies not in equilibrium) 2. The compatibility conditions (continuity conditions) that require deformed volume elements in the member to fit together without overlap or tearing 3. The constitutive relations

Two different methods are used to satisfy requirements 1 and 2: the method of mechanics of materials and the method of general continuum mechanics. Often, load-stress and loaddeflection relations are not derived in this book by general continuum mechanics methods. Instead, the method of mechanics of materials is used to obtain either exact solutions or reliable approximate solutions. In the method of mechanics of materials, the load-stress relations are derived first. They are then used to obtain load-deflectionrelations for the member. A simple member such as a circular shaft of uniform cross section may be subjected to complex loads that produce a multiaxial state of stress. However, such complex loads can be reduced to several simple types of load, such as axial, bending, and torsion. Each type of load, when acting alone, produces mainly one stress component, which is distributed over the cross section of the member. The method of mechanics of materials can be used to obtain load-stress relations for each type of load. If the deformations of the member that result from one type of load do not influence the magnitudes of the other types of loads and if the material remains linearly elastic for the combined loads, the stress components resulting from each type of load can be added together (i.e., the method of superposition may be used). In a complex member, each load may have a significant influence on each component of the state of stress. Then, the method of mechanics of materials becomes cumbersome, and the use of the method of continuum mechanics may be more appropriate.

6

CHAPTER 1 INTRODUCTION

1.2.1

Method of Mechanics of Materials

The method of mechanics of materials is based on simplified assumptions related to the geometry of deformation (requirement 2 ) so that strain distributions for a cross section of the member can be determined. A basic assumption is that plane sections before loading remain plane after loading. The assumption can be shown to be exact for axially loaded members of uniform cross sections, for slender straight torsion members having uniform circular cross sections, and for slender straight beams of uniform cross sections subjected to pure bending. The assumption is approximate for other problems. The method of mechanics of materials is used in this book to treat several advanced beam topics (Chapters 7 to 10). In a similar way, we often assume that lines normal to the middle surface of an undeformed plate remain straight and normal to the middle surface after the load is applied. This assumption is used to simplify the plate problem in Chapter 13. We review the steps used in the derivation of the flexure formula (Eq. 1.7 of Section 1.1) to illustrate the method of mechanics of materials and to show how the three requirements listed previously are used. Consider a symmetrically loaded straight beam of uniform cross section subjected to a moment M that produces pure bending (Figure 1.6~). (Note that the plane of loads lies in a plane of symmetry of every cross section of the beam.) We wish to determine the normal stress distribution o for a specified cross section of the beam. We assume that o i s the major stress component and ignore other effects. Pass a section through the beam at the specified cross section so that the beam is cut into two parts. Consider a free-body diagram of one part (Figure 1.6b). The applied moment M for this part of the beam is in equilibrium with internal forces represented by the sum of the forces that result from the normal stress 0 that acts over the area of the cut section. Equations of equilibrium (requirement l ) relate the applied moment to internal forces. Since no axial force acts, two integrals are obtained: o dA = 0 and o y d A = M , where M is the applied external moment and y is the perpendicular distance from the neutral axis to the element of area dA. Before the two integrals can be evaluated, we must know the distribution of o over the cross section. Since the stress distribution is not known, it is determined indirectly through a strain distribution obtained by requirement 2. The continuity condition is examined by consideration of two cross sections of the undeformed beam separated by an infinitesimal angle do (Figure 1.6~).Under the assumption that plane sections remain plane, the cross sections must rotate with respect to each other as the moment M is applied. There is a straight line in each cross section called the neutral axis along which the strains remain zero. Since plane sections remain plane, the strain distribution must vary linearly with the distance y as measured from this neutral axis.

FIGURE 1.6 Pure bending of a long straight beam. (a) Circular curvature of beam in pure bending. (b)Free-body diagram of cut beam. ( c )Infinitesimal segment of beam.

1.2

METHODS OF ANALYSIS

7

Requirement 3 is now employed to obtain the relation between the assumed strain distribution and the stress distribution. Tension and compression stress-strain diagrams represent the response for the material in the beam. For sufficiently small strains, these diagrams indicate that the stresses and strains are linearly related. Their constant ratio, CJ/E = E , is the modulus of elasticity for the material. In the linear range the modulus of elasticity is the same in tension or compression for many engineering materials. Since other stress components are neglected, o i s the only stress component in the beam. Hence, the stress-strain relation for the beam is o = EE. Therefore, both the stress CT and strain E vary linearly with the distance y as measured from the neutral axis of the beam (Figure 1.6). The equations of equilibrium can be integrated to obtain the flexure formula CT = M y / Z , where M is the applied moment at the given cross section of the beam and I is the moment of inertia of the beam cross section.

1.2.2 Method of Continuum Mechanics and the Theory of Elasticity Many of the problems treated in this book have multiaxial states of stress of such complexity that the mechanics of materials method cannot be employed to derive load-stress and load-deflection relations. Therefore, in such cases, the method of continuum mechanics is used. When we consider small displacements and linear elastic material behavior only, the general method of continuum mechanics reduces to the method of the theory of linear elasticity. In the derivation of load-stress and load-deflection relations by the theory of linear elasticity, an infinitesimal volume element at a point in a body with faces normal to the coordinate axes is often employed. Requirement 1 is represented by the differential equations of equilibrium (Chapter 2). Requirement 2 is represented by the differential equations of compatibility (Chapter 2). The material response (requirement 3) for linearly elastic behavior is determined by one or more experimental tests that define the required elastic coefficients for the material. In this book we consider mainly isotropic materials for which only two elastic coefficients are needed. These coefficients can be obtained from a tension specimen if both axial and lateral strains are measured for every load applied to the specimen. Requirement 3 is represented therefore by the isotropic stress-strain relations developed in Chapter 3. If the differential equations of equilibrium and the differential equations of compatibility can be solved subject to specified stress-strain relations and specified boundary conditions, the states of stress and displacements for every point in the member are obtained.

1.2.3

Deflections by Energy Methods

Certain structures are made up of members whose cross sections remain essentially plane during the deflection of the structures. The deflected position of a cross section of a member of the structure is defined by three orthogonal displacement components of the centroid of the cross section and by three orthogonal rotation components of the cross section. These six components of displacement and rotation of a cross section of a member are readily calculated by energy methods. For small displacements and small rotations and for linearly elastic material behavior, Castigliano’s theorem is effective as a method for the computation of the displacements and rotations. The method is employed in Chapter 5 for structures made up of axially loaded members, beams, and torsion members, and in Chapter 9 for curved beams.

8

CHAPTER I INTRODUCTION

1.3 STRESS-STRAIN RELATIONS To derive load-stress and load-deflection relations for specified structural members, the stress components must be related to the strain components. Consequently, in Chapter 3 we discuss linear stress-strain-temperature relations. These relations may be employed in the study of linearly elastic material behavior. In addition, they are employed in plasticity theories to describe the linearly elastic part of the total response of materials. Because experimental studies are required to determine material properties (e.g., elastic coefficients for linearly elastic materials), the study of stress-strain relations is, in part, empirical. To obtain needed isotropic elastic material properties, we employ a tension specimen (Figure 1.7). If lateral as well as longitudinal strains are measured for linearly elastic behavior of the tension specimen, the resulting stress-strain data represent the material response for obtaining the needed elastic constants for the material. The fundamental elements of the stress-strain-temperature relations, however, are studied theoretically by means of the first law of thermodynamics (Chapter 3). The stress-strain-temperature relations presented in Chapter 3 are limited mainly to small strains and small rotations. The reader interested in large strains and large rotations may refer to Boresi and Chong (2000).

1.3.1 Elastic and Inelastic Response of a Solid Initially, we review the results of a simple tension test of a circular cylindrical bar that is subjected to an axially directed tensile load P (Figure 1.7). It is assumed that the load is monotonically increased slowly (so-called static loading) from its initial value of zero load to its final value, since the material response depends not only on the magnitude of the load but also on other factors, such as the rate of loading, load cycling, etc. It is customary in engineering practice to plot the tensile stress o i n the bar as a function of the strain E of the bar. In engineering practice, it is also customary to assume that the stress CJ is uniformly distributed over the cross-sectional area of the bar and that it is equal in magnitude to PIA,, where A , is the original cross-sectional area of the bar. Similarly, the strain E is assumed to be constant over the gage length L and equal to ALIL = e/L, where AL = e (Figure 1.7b) is the change or elongation in the original gage length L (the

FIGURE 1.7 Circular cross section tension specimen. (a) Undeformed specimen: Gage length L; diameter D. (b)Deformed specimen: Gage length elongation e.

1.3

STRESSSTRAIN RELATIONS

9

distance JK in Figure 1 . 7 ~ )For . these assumptions to be valid, the points J and K must be sufficiently far from the ends of the bar (a distance of one or more diameters D from the ends). According to the definition of stress (Section 2.1), the true stress is 6,= P/A,, where A, is the true cross-sectional area of the bar when the load P acts. (The bar undergoes lateral contraction everywhere as it is loaded, with a corresponding change in cross-sectional area.) The difference between 6 = P/Ao and 6, = P/A, is small, provided that the elongation e and, hence, the strain E are sufficiently small (Section 2.8). If the elongation is large, A, may differ significantly fromAo. In addition, the instantaneous or true gage length when load P acts is L , = L + e (Figure 1.7b). Hence, the true gage length L , also changes with we may define the true strain et as follows: the load P. Corresponding to the true stress o,, In the tension test, assume that the load P is increased from zero (where e = 0) by successive infinitesimal increments dP. With each incremental increase dP in load P, there is a corresponding infinitesimal increase d L , in the instantaneous gage length L , . Hence, the infinitesimal increment d q of the true strain E , resulting from dP is

dE, = dLt Lt

(1.11)

Integration of Eq. 1.11 from L to L , yields the true strain E,. Thus, we have L* E,

= jdEt = I n k ) =

L+e

= ln(1 + E )

(1.12)

L

In contrast to the engineering strain E, the true strain E , is not linearly related to the elongation e of the original gage length L . (Compare Eqs. 1.3 and 1.12.) For many structural metals (e.g., alloy steels), the stress-strain relation of a tension specimen takes the form shown in Figure 1.8. This figure is the tensile stress-strain diagram for the material. The graphical stress-strain relation (the curve OABCF in Figure 1.8) was obtained by drawing a smooth curve through the tension test data for a certain alloy steel. Engineers use stress-strain diagrams to define certain properties of the material that are judged to be significant in the safe design of a statically loaded member. Some of aoo 700

600

-a" 500 Eb

400

In

300

200 100

n -

0

0.05

0.10 0.15 Strain E

0.20

eF 0.25

FIGURE 1.8 Engineering stress-strain diagram for tension specimen of alloy steel.

10

CHAPTER 1 INTRODUCTION

these special properties are discussed briefly in the following section. In addition, certain general material responses are addressed.

1.3.2 Material Properties A tensile stress-strain diagram is used by engineers to determine specific material properties used in design. There are also general characteristic behaviors that are somewhat common to all materials. To describe these properties and characteristics, it is convenient to expand the strain scale of Figure 1.8 in the region O M (Figure 1.9). Recall that Figures 1.8 and 1.9 are based on the following definitions of stress and strain: CT = P/A, and E = e/L, where A, and L are constants. Consider a tensile specimen (bar) subjected to a strain E under the action of a load P. If the strain in the bar returns to zero as the load P goes to zero, the material in the bar is said to have been strained within the elastic limit or the material has remained perfectly elustic. If under loading the strain is linearly proportional to the load P (part OA in Figures 1.8 and 1.9), the material is said to be strained within the limit of linear elasticity. The maximum stress for which the material remains perfectly elastic is frequently referred to simply as the elastic limit GEL, whereas the stress at the limit of linear elasticity is referred to as the proportional limit opL (point A in Figures 1.8 and 1.9). Ordinarily, o E L is larger than oPL. The properties of elastic limit and proportional limit, although important from a theoretical viewpoint, are not of practical significance for materials like alloy steels. This is because the transitions from elastic to inelastic behavior and from linear to nonlinear behavior are so gradual that these limits are very difficult to determine from the stress-strain diagram (part OAB of the curves in Figures 1.8 and 1.9). When the load produces a stress CT that exceeds the elastic limit (e.g., the stress at point J in Figure 1.9), the strain does not disappear upon unloading (curve JK in Figure 1.9). A permanent strain ep remains. For simplicity, it is assumed that the unloading occurs along the straight line JK, with a slope equal to that of the straight line OA. The

Strain c

FIGURE 1.9 Engineering stress-strain diagram for tension specimen of alloy steel (expanded strain scale).

1.3

STRESSSTRAIN RELATIONS

11

strain that is recovered when the load is removed is called the elastic strain E,. Hence, the total strain E at point J is the sum of the permanent strain and elastic strain, or E = ep+ E,. Yield Strength The value of stress associated with point L (Figure 1.9) is called the yield strength and is denoted by bYsor simply by Y. The yield strength is determined as the stress associated with the intersection of the curve OAB and the straight line LM drawn from the offset strain value, with a slope equal to that of line OA (Figure 1.9). The value of the offset strain is arbitrary. However, a commonly agreed upon value of offset is 0.002 or 0.2% strain, as shown in Figure 1.9. Typical values of yield strength for several structural materials are listed in Appendix A, for an offset of 0.2%. For materials with stress-strain curves like that of alloy steels (Figures 1.8 and 1.9), the yield strength is used to predict the load that initiates inelastic behavior (yield) in a member. Ultimate Tensile Strength Another important property determined from the stress-strain diagram is the ultimate tensile strength or ultimate tensile stress 0,.It is defined as the maximum stress attained in the engineering stress-strain diagram, and in Figure 1.8 it is the stress associated with point C. As seen from Figure 1.8, the stress increases continuously beyond the elastic region OA, until point C is reached. As the material is loaded beyond its yield stress, it maintains an ability to resist additional strain with an increase in stress. This response is called strain hardening. At the same time the material loses cross-sectional area owing to its elongation. This area reduction has a softening (strength loss) effect, measured in terms of initial area Ao. Before point C is reached, the strain-hardening effect is greater than the loss resulting from area reduction. At point C, the strain-hardening effect is balanced by the effect of the area reduction. From point C to point F, the weakening effect of the area reduction dominates, and the engineering stress decreases,until the specimen ruptures at point E Modulus of Elasticity In the straight-line region OA of the stress-strain diagram, the stress is proportional to strain; that is, 0= EE.The constant of proportionality E is called the modulus of elasticity. It is also referred to as Young’s modulus. Geometrically, it is equal in magnitude to the slope of the stress-strain relation in the region OA (Figure 1.9). Percent Elongation The value of the elongation eF of the gage length L at rupture (point F, Figure 1.8) divided by the gage length L (in other words, the value of strain at rupture) multiplied by 100 is referred to as the percent elongation of the tensile specimen. The percent elongation is a measure of the ductility of the material. From Figure 1.8, we see that the percent elongation of the alloy steel is approximately 23%.

An important metal for structural applications, mild or structural steel, has a distinct stress-strain curve as shown in Figure 1.1Oa. The portion O A B of the stress-strain diagram is shown expanded in Figure 1.10b. The stress-strain diagram for structural steel usually exhibits a so-called upper yield point, with stress bYu,and a lower yield point, with stress oyLThis is because the stress required to initiate yield in structural steel is larger than the stress required to continue the yielding process. At the lower yield the stress remains essentially constant for increasing strain until strain hardening causes the curve to rise (Figure 1.10a). The constant or flat portion of the stress-strain diagram may extend over a strain range of 10 to 40 times the strain at the yield point. Actual test data indicate that the curve from A to B bounces up and down. However, for simplicity, the data are represented by a horizontal straight line.

12

CHAPTER 1 INTRODUCTION

500

400

-

300

5

Y

b

3 200 i 3 100

n

"0

0.04

0.08

0.12 0.16 Strain E

0.20

0.24

0.28

(4 30C

300

iti 20c

a

E. b In

R loo 0

0.002

0.004 Strain E

0.006

"0

0.002

(b)

0.004 Strain E

0.006

(c)

FIGURE 1.10 Engineering stress-strain diagram for tension specimen of structural steel. (a) Stress-strain diagram. ( b )Diagram for small strain ( E < 0.007). (c) Idealized diagram for small strain

(E

< 0.007).

Yield Point for Structural Steel The upper yield point is usually ignored in design, and it is assumed that the stress initiating yield is the lower yield point stress, on. Consequently, for simplicity, the stressstrain diagram for the region OAB is idealized as shown in Figure 1 . 1 0 ~Also . for simpiicity, we shall refer to the yield point stress as the yield point and denote it by the symbol I: Recall that the yield strength (or yield stress) for alloy steel, and for materials such as aluminum alloys that have similar stress-strain diagrams, was also denoted by Y (Figure 1.9). Modulus of Resilience The modulus of resilience is a measure of energy per unit volume (energy density) absorbed by a material up to the time it yields under load and is represented by the area under the stress-strain diagram to the yield point (the shaded area OAH in Figure 1.10~). In Figure l.lOc, this area is given by D ~ L E ~ LSince . eyL= o y L I E , and with the notation Y = o y L , we may express the modulus of resilience as follows: . I

Y" modulus of resilience = -1 2 E

(1.13)

1.3

STRESS-STRAIN RELATIONS

13

Modulus of resilience is an important property for differentiating among materials for applications in which energy absorption is critical.

Modulus of Toughness The modulus of toughness U, is a measure of the ability of a material to absorb energy prior to fracture. It represents the strain energy per unit volume (strain-energy density) in the material at fracture. The strain-energy density is equal to the area under the stressstrain diagram to fracture (point F on curves OABCF in Figures 1.8 and 1.10~). The larger the modulus of toughness is, the greater is the ability of a material to absorb energy without fracturing. A large modulus of toughness is important if a material is not to fail under impact or seismic loads. Modulus of Rupture The modulus of rupture is the maximum tensile or compressive stress in the extreme fiber of a beam loaded to failure in bending. Hence, modulus of rupture is measured in a bending test, rather than in a tension test. It is analogous to the ultimate strength of a material, but it does not truly represent the maximum bending stress for a material because it is determined with the bending formula o = My/Z, which is valid only in the linearly elastic range for a material. Consequently, modulus of rupture normally overpredicts the actual maximum bending stress at failure in bending. Modulus of rupture is used for materials that do not exhibit large plastic deformation, such as wood or concrete. Poisson’s Ratio Poisson’s ratio is a dimensionless measure of the lateral strain that occurs in a member owing to strain in its loaded direction. It is found by measuring both the axial strain E , and the lateral strain in a uniaxial tension test and is given by the value (1.14) In the elastic range, Poisson’s ratio lies between 0.25 and 0.33 for most engineering materials.

Necking of a Mild Steel Tension Specimen As noted previously, the stress-strain curve for a mild steel tension specimen first reaches a local maximum called the upper yield or plastic limit byu,after which it drops to a local minimum (the lower yield point Y ) and runs approximately (in a wavy fashion) parallel to the strain axis for some range of strain. For mild steel, the lower yield point stress Y is assumed to be the stress at which yield is initiated. After some additional strain, the stress rises gradually; a relatively small change in load causes a significant change in strain. In this region (BC in Figure 1.10a), substantial differences exist in the stress-strain diagrams, depending on whether area A, or A, is used in the definition of stress. With area A,, the curve first rises rapidly and then slowly, turning with its concave side down and attaining a maximum value o,, the ultimate strength, before turning down rapidly to fracture (point F, Figure 1.10~). Physically, after O, is reached, necking of the bar occurs (Figure 1.11). This necking is a drastic reduction of the cross-sectional area of the bar in the region where the fracture ultimately occurs. If the load P is referred to the true cross-sectional area A, and, hence, O, = P/A,, the true stress-strain curve differs considerably from the engineering stress-strain curve in the region BC (Figures 1 . 1 0 ~ and 1.12). In addition, the engineering stress-strain curves for

14

CHAPTER 1 INTRODUCTION

FIGURE 1.11 Necking of tension specimen.

tension and compression differ considerably in the plastic region (Figure 1.12), because of the fact that in tension the cross-sectional area decreases with increasing load, whereas in compression it increases with increasing load. However, as can be seen from Figure 1.12, little differences exist between the curves for small strains < 0.01). Equation 1.12 remains valid until necking of the tension specimen occurs. Once necking beings, the engineering strain E is no longer constant in the gage length (see Figures 1.7 and 1.11). However, a good approximation of the true strain may be obtained from the fact that the volume of the specimen remains nearly constant as necking occurs.

Y

0

0.02

0.04

0.06

0.08

0.10

0.12

True strain E~

FIGURE 1. I 2 Comparison of tension and compression engineering stress-strain diagrams with the true stress-strain diagram for structural steel.

1.3

STRESS-STRAIN RELATIONS

I5

Thus, if the volume of the specimen in the gage length remains constant, before necking we have A,L = A , ( L + e )

(a)

or, afier dividing by A tL, we obtain for a bar of circular cross section and initial diameter Do

where D, is the true diameter of the bar. Substitution of Eq. (b) into Eq. 1.12 yields n

et = In-A0 = In-D; = 2ln-DO At Dt" Dt

(1.15)

By measurement of the true diameter at the minimum cross section of the bar in the necked region (Figure 1.1 l), we obtain a good approximation of the true strain in the necked region up to fracture. Other Materials There are many materials whose tensile specimens do not undergo substantial plastic strain before fracture. These materials are called brittle materials. A stress-strain diagram typical of brittle materials is shown in Figure 1.13. It exhibits little plastic range, and fracture occurs almost immediately at the end of the elastic range. In contrast, there are materials that undergo extensive plastic deformation and little elastic deformation. Lead and clay are such materials. The idealized stress-strain diagram for clay is typical of such materials (Figure 1.14).This response is referred to as rigid-perfectly plastic.

F

m a

E b

!n

2

z

O

Strain E

FIGURE 1.13 Stress-strain diagram for a brittle material.

0

FIGURE 1.14 Stress-strain diagram for clay.

E

16

CHAPTER 1 INTRODUCTION

EXAMPLE 1.1 Material Properties for Alloy and Structural Steel Solution

(a) By Figures 1.8 and 1.9, estimate the yield strength Y and the ultimate strength 0, of a tension rod of alloy steel.

(b) By Figures 1.8 and 1.10u, estimate the modulus of toughness U, for alloy steel and structural steel.

(a) By measurement of Figure 1.8, 1 0,-700+-(100) 6

= 717 MPa

By measurement of Figure 1.9, Y = 450 MPa (b) By Figure 1.8, we estimate the number of squares (a square consists of 100-MPa stress by 0.025 strain) under the curve OABCF to be approximately 62. Hence,

U , = 62( 100)0.025 = 155 x lo6 N m/m

3

Similarly, by Figure l.lOu, we estimate the number of squares (here a square consists of 100-MPa stress by 0.04 strain) under the curve OABCF to be 27. Hence,

U , = 27(100)0.04 = 108 x lo6 N m/m

EXAMPLE 1.2 Tension Rod: Modulus oi Elasticity, Permanent Strain, and Elastic Strain Solution

3

A rod of alloy steel (Figure 1.9) is subjected to an axial tension load that produces a stress of (T=500 MPa and an associated strain of eSOO = 0.0073. Assume that elastic unloading occurs. (a) Determine the modulus of elasticity of the rod.

(b) Determine the permanent strain in the rod and the strain that is recovered as the rod is unloaded.

(a) By inspection of Figure 1.9, the stress and strain at pointA are 0,= 343 MPa and E, = 0.00172. Hence, the modulus of elasticity is

E = -OA = - - 343 - 199GPa 0.00172 (b) By Figure 1.9 and Eq. (a), the elastic strain (recovered strain) is

The strain at (T = 500 MPa is (from Figure 1.9) cSw = 0.0073

Hence, the permanent strain is E~

1.4

= E ~ W - E , = 0.0073-0.0025 = 0.0048

FAILURE AND LIMITS ON DESIGN To design a structural system to perform a given function, the designer must have a clear understanding of the possible ways or modes by which the system may fail to perform its function. The designer must determine the possible modes of failure of the system and then establish suitablefailure criteria that accurately predict the failure modes.

1.4

FAILURE AND LIMITS ON DESIGN

17

In general, the determination of modes of failure requires extensive knowledge of the response of a structural system to loads. In particular, it requires a comprehensive stress analysis of the system. Since the response of a structural system depends strongly on the material used, so does the mode of failure. In turn, the mode of failure of a given material also depends on the manner or history of loading, such as the number of cycles of load applied at a particular temperature. Accordingly, suitable failure criteria must account for different materials, different loading histories, and factors that influence the stress distribution in the member. A major part of this book is concerned with 1. stress analysis, 2. material behavior under load, and 3. the relationship between the mode of failure and a critical parameter associated with failure. The critical parameter that signals the onset of failure might be stress, strain, displacement, load, and number of load cycles or a combination of these. The discussion in this book is restricted to situations in which failure of a system is related to only a single critical parameter. In addition, we will examine the accuracy of the theories presented in the text with regard to their ability to predict system behavior. In particular, limits on design will be introduced utilizing factors of safety or reliability-based concepts that provide a measure of safety against failure. Historically, limits on the design of a system have been established using afactor of safety. A factor of safety SF can be defined as Rn SF = -

(1.16)

Rw where R, is the nominal resistance (the critical parameter associated with failure) and R , is the safe working magnitude of that same parameter. The letter R is used to represent the resistance of the system to failure. Generally, the magnitude of R, is based on theory or experimental observation. The factor of safety is chosen on the basis of experiments or experience with similar systems made of the same material under similar loading conditions. Then the safe working parameter R , is determined from Eq. 1.16. The factor of safety must account for unknowns, including variability of the loads, differences in material properties, deviations from the intended geometry, and our ability to predict the critical parameter. In industrial applications, the magnitude of the factor of safety SF may range from just above 1.0 to 3.0 or more. For example, in aircraft and space vehicle design, where it is critical to reduce the weight of the vehicle as much as possible, the SF may be nearly 1.0. In the nuclear reactor industry, where safety is of prime importance in the face of many unpredictable effects, SF may be as high as 5. Generally, a design inequality is employed to relate load effects to resistance. The design inequality is defined as N R CQi I l l (1.17) SF I

where each Qi represents the effect of a particular working (or service-level) load, such as internal pressure or temperature change, and N denotes the number of load types considered. Design philosophies based on reliability concepts (Harr,1987; Cruse, 1997) have been developed. It has been recognized that a single factor of safety is inadequate to account for all the unknowns mentioned above. Furthermore, each of the particular load types will exhibit its own statistical variability. Consequently, appropriate load and

18

CHAPTER I INTRODUCTION

resistance factors are applied to both sides of the design inequality. So modified, the design inequality of Eq. 1.17 may be reformulated as N

CYjQi

CpRn

(1.18)

i

where the % are the load factors for load effects Qi and Cp is the resistance factor for the nominal capacity Rn. The statistical variation of the individual loads is accounted for in x, whereas the variability in resistance (associated with material properties, geometry, and analysis procedures) is represented by Cp. The use of this approach, known as limit-states design, is more rational than the factor-of-safety approach and produces a more uniform reliability throughout the system. A limit state is a condition in which a system, or component, ceases to fulfill its intended function. This definition is essentially the same as the definition of failure used earlier in this text. However, some prefer the term limit state because the term failure tends to imply only some catastrophic event (brittle fracture), rather than an inability to function properly (excessive elastic deflections or brittle fracture). Nevertheless, the term failure will continue to be used in this book in the more general context.

EXAMPLE 1.3 Design of 8 Tension Roa

A steel rod is used as a tension brace in a structure. The structure is subjected to dead load (the load from the structure itself), live load (the load from the structure’s contents), and wind load. The effect of each of the individual loads on the tension brace is 0 = 25 kN, L = 60 kN, and W = 30 kN. Select a circular rod of appropriate size to carry these loads safely. Use steel with a yield strength of 250 MPa. Make the selection using (a) factor-of-safety design and (b) limit-states design.

Solution

For simplicity in this example, the only limit state that will be considered is yielding of the cross section. Other limit states, including fracture and excessive elongation, are ignored.

(a) In factor-of-safety design (also known as allowable stress or working stress design), the load effects are added without load factors. Thus, the total service-level load is CQi = D + L + W = 115kN = 115,000N

(a)

The nominal resistance (capacity) of the tension rod is

R , = Y A , = (250)A,

(b)

where A, is the gross area of the rod. In the design of tension members for steel structures, a factor of safety of 513 is used (AISC, 1989). Hence, the design inequality is

115,000 5

250A, 5 3

which yields A, 2 767 mm’. A rod of 32 mm in diameter, with a cross-sectional area of 804 mm’, is adequate. (b) In limit-states design, the critical load effect is determined by examination of several possible load combination equations. These equations represent the condition in which a single load quantity is at its maximum lifetime value, whereas the other quantities are taken at an arbitrary point in time. The relevant load combinations for this situation are specified (ASCE, 2000) as

1.40

(4

1.20 + 1.6L

(el

1.20 + 0.5L + 1.6W

(0

For the given load quantities, combination (e) is critical. The total load effect is

1.4

FAILURE AND LIMITS ON DESIGN

19

Eriei= 126 IrN = 126,000 N In the design of tension members for steel structures, a resistance factor of #I = 0.9 is used (AISC, 2001). Hence, the limit-states design inequality is 126,000 I0.9(250Ag)

(h)

which yields A, t 560 mm2. A rod 28 mm in diameter, with a cross-sectional area of 616 mm2, is adequate.

Discussion The objective of this example has been to demonstrate the use of different design philosophies through their respective design inequalities, Eqs. 1.17 and 1.18. For the conditions posed, the limit-states approach produces a more economical design than the factor-of-safety approach. This can be attributed to the recognition in the load factor equations (d-f) that it is highly unlikely both live load and wind load would reach their maximum lifetime values at the same time. Different combinations of dead load, live load, and wind load, which still give a total service-level load of 115 IcN, could produce different factored loads and thus different area requirements for the rod under limit-states design.

1.4.1 Modes of Failure When a structural member is subjected to loads, its response depends not only on the type of material from which it is made but also on the environmental conditions and the manner of loading. Depending on how the member is loaded, it may fail by excessive dejection, which results in the member being unable to perform its design function; it may fail by plastic deformation (general yielding), which may cause a permanent, undesirable change in shape; it may fail because of afracture (break), which depending on the material and the nature of loading may be of a ductile type preceded by appreciable plastic deformation or of a brittle type with little or no prior plastic deformation. Fatigue failure, which is the progressive growth of one or more cracks in a member subjected to repeated loads, often culminates in a brittle fracture type of failure. Another manner in which a structural member may fail is by elastic or plastic instability. In this failure mode, the structural member may undergo large displacements from its design configuration when the applied load reaches a critical value, the buckling load (or instability load). This type of failure may result in excessive displacement or loss of ability (because of yielding or fracture) to carry the design load. In addition to the failure modes already mentioned, a structural member may fail because of environmental corrosion (chemical action). To elaborate on the modes of failure of structural members, we discuss more fully the following categories of failure modes: 1. Failure by excessive deflection

a. Elastic deflection b. Deflection caused by creep 2. Failure by general yielding 3. Failure by fracture

a. Sudden fracture of brittle materials b. Fracture of cracked or flawed members c. Progressive fracture (fatigue)

4. Failure by instability

20

CHAPTER 1 INTRODUCTION

These failure modes and their associated failure criteria are most meaningful for simple structural members (e.g., tension members, columns, beams, circular cross section torsion members). For more complicated two- and three-dimensional problems, the significance of such simple failure modes is open to question. Many of these modes of failure for simple structural members are well known to engineers. However, under unusual conditions of load or environment, other types of failure may occur. For example, in nuclear reactor systems, cracks in pipe loops have been attributed to stress-assisted corrosion cracking, with possible side effects attributable to residual welding stresses (Clarke and Gordon, 1973; Hakala et al., 1990; Scott and Tice, 1990). The physical action in a structural member leading to failure is usually a complicated phenomenon, and in the following discussion the phenomena are necessarily oversimplified, but they nevertheless retain the essential features of the failures.

1. Failure b y Excessive Elastic Deflection The maximum load that may be applied to a member without causing it to cease to function properly may be limited by the permissible elastic strain or deflection of the member. Elastic deflection that may cause damage to a member can occur under these different conditions:

a. Deflection under conditions of stable equilibrium, such as the stretch of a tension member, the angle of twist of a shaft, and the deflection of an end-loaded cantilever beam. Elastic deflections, under conditions of equilibrium, are computed in Chapter 5. b. Buckling, or the rather sudden deflection associated with unstable equilibrium and often resulting in total collapse of the member. This occurs, for example, when an axial load, applied gradually to a slender column, exceeds the Euler load. See Chapter 12. c. Elastic deflections that are the amplitudes of the vibration of a member sometimes associated with failure of the member resulting from objectionable noise, shaking forces, collision of moving parts with stationary parts, etc., which result from the vibrations. When a member fails by elastic deformation, the significant equations for design are those that relate loads and elastic deflection. For example, the elementary mechanics of materials equations, for the three members mentioned under condition (a), are e = PL/AE, 8 = TLIGJ, and v = PL3/3EI.It is noted that these equations contain the significant property of the material involved in the elastic deflection, namely, the modulus of elasticity E (sometimes called the stiffness) or the shear modulus G = E/[2(1 + v)], where v is Poisson’s ratio. The stresses caused by the loads are not the significantquantities; that is, the stresses do not limit the loads that can be applied to the member. In other words, if a member of given dimensions fails to perform its load-resisting function because of excessive elastic deflection, its load-carrying capacity is not increased by making the member of stronger material. As a rule, the most effective method of decreasing the deflection of a member is by changing the shape or increasing the dimensions of its cross section, rather than by making the member of a stiffer material. 2. Failure b y General Yielding Another condition that may cause a member to fail is general yielding. General yielding is inelastic deformation of a considerable portion of the member, distinguishing it from localized yielding of a relatively small portion of the member. The following discussion of

1.4

FAILURE AND LIMITS O N DESIGN

21

yielding addresses the behavior of metals at ordinary temperatures, that is, at temperatures that do not exceed the recrystallization temperature. Yielding at elevated temperatures (creep) is discussed in Chapter 18. Polycrystalline metals are composed of extremely large numbers of very small units called crystals or grains. The crystals have slip planes on which the resistance to shear stress is relatively small. Under elastic loading, before slip occurs, the crystal itself is distorted owing to stretching or compressing of the atomic bonds from their equilibrium state. If the load is removed, the crystal returns to its undistorted shape and no permanent deformation exists. When a load is applied that causes the yield strength to be reached, the crystals are again distorted but, in addition, defects in the crystal, known as dislocations (Eisenstadt, 1971), move in the slip planes by breaking and reforming atomic bonds. After removal of the load, only the distortion of the crystal (resulting from bond stretching) is recovered. The movement of the dislocations remains as permanent deformation. After sufficient yielding has occurred in some crystals at a given load, these crystals will not yield further without an increase in load. This is due to the formation of dislocation entanglements that make motion of the dislocations more and more difficult. A higher and higher stress will be needed to push new dislocations through these entanglements. This increased resistance that develops after yielding is known as strain hardening or work hardening. Strain hardening is permanent. Hence, for strain-hardening metals, the plastic deformation and increase in yield strength are both retained after the load is removed. When failure occurs by general yielding, stress concentrations usually are not significant because of the interaction and adjustments that take place between crystals in the regions of the stress concentrations. Slip in a few highly stressed crystals does not limit the general load-carrying capacity of the member but merely causes readjustment of stresses that permit the more lightly stressed crystals to take higher stresses. The stress distribution approaches that which occurs in a member free from stress concentrations. Thus, the member as a whole acts substantially as an ideal homogeneous member, free from abrupt changes of section. It is important to observe that, if a member that fails by yielding is replaced by one with a material of a higher yield stress, the mode of failure may change to that of elastic deflection, buckling, or excessive mechanical vibrations. Hence, the entire basis of design may be changed when conditions are altered to prevent a given mode of failure. 3. Failure b y Fracture Some members cease to function satisfactorily because they break (fracture) before either excessive elastic deflection or general yielding occurs. Three rather different modes or mechanisms of fracture that occur especially in metals are now discussed briefly.

a. Sudden Fracture of Brittle Material. Some materials-so-called brittle materials-function satisfactorily in resisting loads under static conditions until the material breaks rather suddenly with little or no evidence of plastic deformation. Ordinarily, the tensile stress in members made of such materials is considered to be the significant quantity associated with the failure, and the ultimate strength 0,is taken as the measure of the maximum utilizable strength of the material (Figure l . 13). b. Fracture of Flawed Members. A member made of a ductile metal and subjected to static tensile loads will not fracture in a brittle manner as long as the member is free of flaws (cracks, notches, or other stress concentrations) and the temperature is not unusually low. However, in the presence of flaws, ductile materials may experience brittle fracture at normal temperatures. Plastic deformation may be small or nonexistent even though fracture is impending. Thus, yield strength is not the critical

22

CHAPTER 1 INTRODUCTION

material parameter when failure occurs by brittle fracture. Instead, notch toughness, the ability of a material to absorb energy in the presence of a notch (or sharp crack), is the parameter that governs the failure mode. Dynamic loading and low temperatures also increase the tendency of a material to fracture in a brittle manner. Failure by brittle fracture is discussed in Chapter 15. C.

Progressive Fracture (Fatigue). If a metal that ordinarily fails by general yielding under a static load is subjected to repeated cycles of stress, it may fail by fracture without visual evidence of yielding, provided that the repeated stress is greater than a value called the fatigue strength. Under such conditions, minute cracks start at one or more points in the member, usually at points of high localized stress such as at abrupt changes in section, and gradually spread by fracture of the material at the edges of the cracks where the stress is highly concentrated. The progressive fracture continues until the member finally breaks. This mode of failure is usually called a fatigue failure, but it is better designated as failure by progressive fracture resulting from repeated loads. (See Chapter 16.)

4. Failure by Instability (Buckling) Some members may fail by a sudden, catastrophic, lateral deflection (instability or buckling), rather than by yielding or crushing (Chapter 12). Consider an ideal pin-ended slender column (or strut) subjected to an axial compressive load P. Elastic buckling of the member occurs when the load P reaches a critical value P,, = z2EIJL2,where E is the modulus of elasticity, I is the moment of inertia of the cross section, and L is the member length.

PROBLEMS 1.1. What requirements control the derivation of load-stress relations? 1.2. Describe the method of mechanics of materials. 1.3. How are stress-strain-temperature relations for a material established? 1.4. Explain the differences between elastic response and inelastic response of a solid. 1.5. What is a stress-strain diagram? 1.6. Explain the difference between elastic limit and proportional limit. 1.7. Explain the difference between the concepts of yield point and yield stress. 1.8. What is offset strain? 1.9. How does the engineering stress-strain diagram differ from the true stress-strain diagram? 1.10. What are modes of failure? 1.11. What are failure criteria? How are they related to modes of failure? 1.12. What is meant by the term factor of safety? How are factors of safety used in design? 1.13. What is a design inequality?

1.14. How is the usual design inequality modified to account for statistical variability? 1.15. What is a load factor? A load effect? A resistance factor? 1.16. What is a limit-states design? 1.17. What is meant by the phrase “failure by excessive deflection”? 1.18. What is meant by the phrase “failure by yielding”? 1.19. What is meant by the phrase “failure by fracture”? 1.20. Discuss the various ways that a structural member may fail. 1.21. Discuss the failure modes, critical parameters, and failure criteria that may apply to the design of a downhill snow ski. 1.22. For the steels whose stress-strain diagrams are represented by Figures 1.8 to 1.10, determine the following properties as appropriate: the yield point, the yield strength, the upper yield point, the lower yield point, the modulus of resilience, the ultimate tensile strength, the strain at fracture, the percent elongation. 1.23. Use the mechanics of materials method to derive the load-stress and load-displacementrelations for a solid circular rod of constant radius r and length L subjected to a torsional moment T as shown in Figure P1.23.

PROBLEMS

23

T

FIGURE P1.23 Solid circular rod in torsion.

1.24. Use the mechanics of materials method to derive the load-stress and load-displacement relations for a bar of constant width b, linearly varying depth d, and length L subjected to an axial tensile force P as shown in Figure P1.24.

A

Longitudinal section (rods not shown)

End plate

Pipe: OD = 100 m m ID = 90 m m

P

-Steel rod (typical) Diameter = 15 m m Section A-A

FIGURE P I .25 Pressurized cylinder. FIGURE P1.24

Tapered bar in tension.

1.25. A pressure vessel consists of two flat plates clamped to the ends of a pipe using four rods, each 15 mm in diameter, to form a cylinder that is to be subjected to internal pressure p (Figure P1.25). The pipe has an outside diameter of 100 mm and an inside diameter of 90 mm. Steel is used throughout (E = 200 GPa). During assembly of the cylinder (before pressurization), the joints between the plates and ends of the pipe are sealed with a thin mastic and the rods are each pretensioned to 65 IcN. Using the mechanics of materials method, determine the internal pressure that will cause leaking. Leaking is defined as a state of zero bearing pressure between the pipe ends and the plates. Also determine the change in stress in the rods. Ignore bending in the plates and radial deformation of the pipe. 1.26. A steel bar and an aluminum bar are joined end to end and fixed between two rigid walls as shown in Figure P1.26. The cross-sectional area of the steel bar is A, and that of the aluminum bar is A,. Initially, the two bars are stress free. Derive general expressions for the deflection of point A, the stress in the steel bar, and the stress in the aluminum bar for the following conditions: a. A load P is applied at point A.

b. The left wall is displaced an amount 6 to the right.

1.27. In South African gold mines, cables are used to lower worker cages down mine shafts. Ordinarily, the cables are made of steel. To save weight, an engineer decides to use cables made of aluminum. A design requirement is that the stress in the cable resulting from self-weight must not exceed one-tenth of the ultimate strength o, of the cable. A steel cable has a mass density p = 7.92 Mg/m3 and o, = 1030 MPa. For an aluminum cable, p = 2.77 Mg/m3 and o,= 570 MPa.

Steel

Aluminum

FIGURE P1.26 Bi-metallic rod.

a. Determine the lengths of two cables, one of steel and the other of aluminum, for which the stress resulting from the selfweight of each cable equals one-tenth of the ultimate strength of the material. Assume that the cross-sectional area A of a cable is constant over the length of the cable. b. Assuming that A is constant, determine the elongation of each cable when the maximum stress in the cable is 0.100,. The steel cable has a modulus of elasticity E = 193 GPa and for the aluminum cable E = 72 GPa. c. The cables are used to lower a cage to a mine depth of 1 km. Each cable has a cross section with diameter D = 75 mm. Determine the maximum allowable weight of the cage (including workers and equipment), if the stress in a cable is not to exceed 0.200,.

1.28. A steel shaft of circular cross section is subjected to a twisting moment T.The controlling factor in the design of the shaft is the angle of twist per unit length (y/L;see Eq. 1S).The maximum allowable twist is 0.005 rad/m, and the maximum , , ,z = 30 MPa. Determine the diameter at which shear stress is the maximum allowable twist, and not the maximum shear stress, is the controlling factor. For steel, G = 77 GPa. 1.29. An elastic T-beam is loaded and supported as shown in Figure P1.29~.The cross section of the beam is shown in Figure P1.296.

24

CHAPTER 1 INTRODUCTION

IP

t I

10 kNlm

P1.31. Convert these data to engineering stress-strain data and determine the magnitudes of the toughness U , and the ultimate strength 0,. TABLE P1.31

X

&A

FIGURE P1.29 T-beam.

Elongation (mm)

Elongation (mm)

0 3.1 6.2 9.3 12.4 15.5 18.6 21.7 24.7 25.8 26.1 29.2 31.0 34.0

0 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09 0.10 0.15 0.20 0.30

36.3 38.8 41.2 44.1 48.1 50.4 51.4 52.0 52.2 52.0 50.6 45.1 43.2 -

0.40 0.50 0.60 1.25 2.50 3.75 5.00 6.25 7.50 8.75 10.00 11.25 11.66 -

a. Determine the location j of the neutral axis (the horizontal centroidal axis) of the cross section. b. Draw shear and moment diagrams for the beam. c. Determine the maximum tensile stress and the maximum compressive stress in the beam and their locations.

1.30. Determine the maximum and minimum shear stresses in the web of the beam of Problem 1.29 and their locations.Assume that the distributions of shear stresses in the web, as in rectangular cross sections, are directed parallel to the shear force V and are uniformly distributed across the thickness (t = 6.5 mm) of the web. Hence, Eq. 1.9 can be used to calculate the shear stresses. 1.31. A steel tensile test specimen has a diameter of 10 mm and a gage length of 50 mm. Test data for axial load and corresponding data for the gage-length elongation are listed in Table

AISC (2001). Manual of Steel Construction-Load and Resistance Factor Design, 3rd ed. Chicago, IL: American Institute of Steel Construction. AISC (1989). Specification for Structural Steel Buildings-Allowable Stress Design and Plastic Design. Chicago, IL:June 1. AMERICAN SOCIETYOF CIVILENGINEERS (ASCE) (2000). Minimum Design Loads for Buildings and Other Structures, ASCE Std. 7-98. New York. BORES, A. P., and CHONG,K. P. (2000). Elasticity in Engineering Mechanics, 2nd ed. New York: Wiley-Interscience. G. M. (1973). Investigation of Stress CLARKE, W. L., and GORDON, Corrosion Cracking Susceptibility of Fe-Ni-Cr Alloys in Nuclear Reactor Water Environments. Corrosion, 29(1): 1-12.

CRUSE,T. A. (1997). Reliability-Based Mechanical Design. New York: Marcel Dekker, Inc. EISENSTADT, M. M. (1 97 1). Introduction to Mechanical Properties of Metals. New York Macmillan. GERE,J. (2001). Mechanics of Materials, 5th ed. Pacific Grove, CA: Brooks/Cole, Thomson Learning. HAKALA, J., HANNINEN, H., and ASLTONEN, P. (1990). Stress Corrosion and Thermal Fatigue. Nucl. Eng. Design, 119(2,3): 389-398. HARR,M. E. (1987). Reliability-Based Design in Civil Engineering. New York: McGraw-Hill. SCo'lT, P. M., and TICE,D. R. (1990). Stress Corrosion in Low-Alloy Steels. Nucl. Eng. Design, 119(2,3): 399414.

CHAPTER

2

THEORIES OF STRESS AND STRAIN I

In Chapter 1, we presented general concepts and definitions that are fundamental to many of the topics discussed in this book. In this chapter, we develop theories of stress and strain that are essential for the analysis of a structural or mechanical system subjected to loads. The relations developed are used throughout the remainder of the book.

2.1

DEFINITION OF STRESS AT A POINT Consider a general body subjected to forces acting on its surface (Figure 2.1). Pass a fictitious plane Q through the body, cutting the body along surface A (Figure 2.2). Designate one side of plane Q as positive and the other side as negative. The portion of the body on the positive side of Q exerts a force on the portion of the body on the negative side. This force is transmitted through the plane Q by direct contact of the parts of the body on the two sides of Q. Let the force that is transmitted through an incremental area AA of A by the part on the positive side of Q be denoted by AF. In accordance with Newton’s third law, the portion of the body on the negative side of Q transmits through area AA a force -AF. The force A F may be resolved into components AFN and AFs, along unit normal N and unit tangent S, respectively, to the plane Q. The force AF, is called the normal force

FIGURE 2.1 A general loaded body cut by plane 0.

25

26

CHAPTER 2 THEORIES OF STRESS AND STRAIN

FIGURE 2.2

Force transmitted through incremental area of cut body.

on area AA and AFs is called the shear force on AA. The forces AF, AFN,and AFs depend on the location of area AA and the orientation of plane Q. The magnitudes of the average forces per unit area are AFIAA, AFNJAA, and AFs/AA. These ratios are called the average stress, average normal stress, and average shear stress, respectively, acting on area AA. The concept of stress at a point is obtained by letting AA become an infinitesimal. Then the forces AF, AFN,and AFs approach zero, but usually the ratios AFJAA, AFN/AA, and AFsIAA approach limits different from zero. The limiting ratio of AFIAA as AA goes to zero defines the stress vector u.Thus, the stress vector Q is given by F u = lim A AA+OM

The stress vector Q (also called the traction vector) always lies along the limiting direction of the force vector AF,which in general is neither normal nor tangent to the plane Q. Similarly, the limiting ratios of AFNJAA and AFs/AA define the normal stress vector u, and the shear stress vector us that act at a point in the plane Q. These stress vectors are defined by the relations

uN = lim AFN AA+O

M

us =

lim AFS -

AA+O

The unit vectors associated with uN and us are normal and tangent, respectively, to the plane Q.

2.2

STRESS NOTATION Consider now a free-body diagram of a box-shaped volume element at a point 0 in a member, with sides parallel to the (x,y, z) axes (Figure 2.3). For simplicity, we show the volume element with one corner at point 0 and assume that the stress components are uniform (constant) throughout the volume element. The surface forces are given by the product of the stress components (Figure 2.3) and the areas' on which they act. 'You must remember to multiply each stress component by an appropriate area before applying equations of force equilibrium. For example, 0, must be multiplied by the area dy dz.

2.2

+

d

x

STRESS NOTATION

27

4

FIGURE 2.3 Stress components at a point in loaded body.

FIGURE 2.4

Body forces.

Body forces? given by the product of the components (Bx, By, B,) and the volume of the element (product of the three infinitesimal lengths of the sides of the element), are higher-order terms and are not shown on the free-body diagram in Figure 2.3. Consider the two faces perpendicular to the x axis. The face from which the positive x axis is extended is taken to be the positive face; the other face perpendicular to the x axis is taken to be the negative face. The stress components o ,, oxy, and ox,acting on the positive face are taken to be in the positive sense as shown when they are directed in the positive x, y, and z directions. By Newton’s third law, the positive stress components o,, oxy, and o,,shown acting on the negative face in Figure 2.3 are in the negative (x, y, z) directions, respectively. In effect, a positive stress component o , exerts a tension (pull) parallel to the x axis. Equivalent sign conventions hold for the planes perpendicular to the y and z axes. Hence, associated with the concept of the state of stress at a point 0, nine components of stress exist:

In the next section we show that the nine stress components may be reduced to six for most practical problems. ’We use the notation B or (Bx,By, B,) for body force per unit volume, where B stands for body and subscripts (x, y, z) denote components in the (x. y, z ) directions, respectively, of the rectangular coordinate system (x, y, z ) (see Figure 2.4).

28

CHAPTER 2 THEORIES OF STRESS AND STRAIN

2.3 SYMMETRY OF THE STRESS ARRAY AND STRESS ON AN ARBITRARILY ORIENTED PLANE 2.3.1 Symmetry of Stress Components The nine stress components relative to rectangular coordinate axes (x,y, z ) may be tabulated in array form as follows:

(2.3)

where T symbolically represents the stress array called the stress tensor. In this array, the stress components in the first, second, and third rows act on planes perpendicular to the (x,y, z ) axes, respectively. Seemingly, nine stress components are required to describe the state of stress at a point in a member. However, if the only forces that act on the free body in Figure 2.3 are surface forces and body forces, we can demonstrate from the equilibrium of the volume element in Figure 2.3 that the three pairs of the shear stresses are equal. Summation of moments leads to the result

Thus, with Eq. 2.4, Eq. 2.3 may be written in the symmetric form r

1

Hence, for this type of stress theory, only six components of stress are required to describe the state of stress at a point in a member. Although we do not consider body couples or surface couples in this book (instead see Boresi and Chong, 2000), it is possible for them to be acting on the free body in Figure 2.3. This means that Eqs. 2.4 are no longer true and that nine stress components are required to represent the unsymmetrical state of stress. The stress notation just described is widely used in engineering practice. It is the notation used in this book3 (see row I of Table 2.1). Two other frequently used symmetric stress notations are also listed in Table 2.1. The symbolism indicated in row I11 is employed where index notation is used (Boresi and Chong, 2000). TABLE 2.1

Stress Notations (Symmetric Stress Components)

I ll

0xx

111

0 11

0YY

OX

022

022

0xy

02

zxy

033

= 0yx = zyx

O12 = O21

0x2

= 0zx

=yz

= 0zy

7x2 = zzx

zyz = Tzy

013 = 4 1

023 = 032

3Equivalent notations are used for other orthogonal coordinate systems (see Section 2.5).

2.3

SYMMETRY OF THE STRESS ARRAY AND STRESS O N A N ARBITRARILY ORIENTED PLANE

29

2.3.2 Stresses Acting on Arbitrary Planes The stress vectors a,,uy, and a,on planes that are perpendicular, respectively, to the x,y, and z axes are ax =

oXxi+ oxyj + oxzk

a, =

Q

YX

i + o,, j + oyzk

uz = a,\$

+ a,, j + ozzk

where i, j, and k are unit vectors relative to the (x, y, z ) axes (see Figure 2.5 for u,). Now consider the stress vector upon an arbitrary oblique plane P that cuts the volume element into a tetrahedron (Figure 2.6). The unit normal vector to plane P is

N = li+mj+nk

(2.7)

where (I, m,n) are the direction cosines of unit vector N. Therefore, vectorial summation offorces acting on the tetrahedral element OABC yields the following (note that the ratios of areas OBC, OAC, OBA to area ABC are equal to I , m, and n, respectively):

up = l u x + m u y + n u ,

(2.8)

Also, in terms of the projections (apx, opy, opz) of the stress vector upalong axes (x,y, z), we may write

up = opxi+ opyj + opzk

FIGURE 2.5

(2.9)

Stress vector and its components acting on a plane perpendicular to the x axis.

FIGURE 2.6 Stress vector on arbitrary plane having a normal N.

30

CHAPTER 2 THEORIES OF STRESS AND STRAIN

Comparison of Eqs. 2.8 and 2.9 yields, with Eqs. 2.6,

opx= loxx+ m o y , + n o z x opy= loX Y + m o y , + n o z y

(2.10)

opz= lox,+ m o y , + no,, Equations 2.10 allow the computation of the components of stress on any oblique plane defined by unit normal N:(l, m, n), provided that the six components of stress

at point 0 are known.

2.3.3 Normal Stress and Shear Stress on an Oblique Plane The normal stress oPN on the plane P is the projection of the vector upin the direction of N; that is, oPN = up N. Hence, by Eqs. 2.7, 2.9, and 2.10

opN= I 2 o x x + m2 CTYY + n2 o z , + 2 mn oY Z +21nox,+21moxy

(2.1 1)

Often, the maximum value of oPN at a point is of importance in design (see Section 4.1). Of the infinite number of planes through point 0, oPN attains a maximum value called the maximum principal stress on one of these planes. The method of determining this stress and the orientation of the plane on which it acts is developed in Section 2.4. To compute the magnitude of the shear stress opson plane P, we note by geometry (Figure 2.7) that

oYy, oZz, oXy, Substitution of Eqs. 2.10 and 2.1 1 into Eq. 2.12 yields oPsin terms of (on, o,,,oyz) and (1, m, n). In certain criteria of failure, the maximum value of upsat a point in the body plays an important role (see Section 4.4). The maximum value of opp~can be expressed in terms of the maximum and minimum principal stresses (see Eq. 2.39, Section 2.4).

Plane P

FIGURE 2.7

Normal and shear stress components of stress vector on an arbitrary plane,

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

31

2.4 TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES 2.4.1 Transformation of Stress Let (x, y, z) and (X, U, Z) denote two rectangular coordinate systems with a common origin (Figure 2.8). The cosines of the angles between the coordinate axes (x, y, z) and the coordinate axes (X, 2 ) are listed in Table 2.2. Each entry in Table 2.2 is the cosine of the angle between the two coordinate axes designated at the top of its column and to the left of its row. The angles are measured from the (x, y, z) axes to the (X, U, 2 ) axes. For example, 1, = cos 6, l2 = cos6xy, ... (see Figure 2.8.). Since the axes (x, y, z) and axes (X, Y, 2 ) are orthogonal, the direction cosines of Table 2.2 must satisfy the following relations: For the row elements 2

2

2

1,. + m i + n i = 1, i = 1 , 2 , 3

l1l2+ m l m 2 + n1n2 = 0

1113 + m l m 3 + n l n 3 = 0

(2.13)

1213+m2m3+n2n3 = 0 For the column elements 2

2

2

11+12+13 = 1, 2

2

Elml +12m2+13m3 = 0

2

ml + m 2 + m3 = 1, l l n l + E2n2 + 13n3 = 0 2

2

2

n l + n 2 + n 3 = 1,

(2.14)

m l n l + m 2 n 2 + m 3 n 3= 0

The stress components,,a a ,oxz,... are defined with reference to the (X, U, 2 ) axes in the same manner as , a,'a a,,, ... are defined relative to the axes (x, y, z). Hence,

FIGURE 2.8

Stress components on plane perpendicular to transformed X axis.

TABLE 2.2 Direction Cosines

32

CHAPTER 2 THEORIES OF STRESS AND STRAIN

om is the normal stress component on a plane perpendicular to axis X , , o and oxzare shear stress components on this same plane (Figure 2.8), and so on. By Eq. 2.1 1 , oxx= l2I o x x + m2 l o y y +2 n l o z z + 2 m l n l o y z + 2 n 1 1 1 ~ z x + ~ ~ 1 ~ , o , y 2

2

2

2

2

2

oyy= l 2 o X x+ m 2 0 y y+ n 2 0 Z Z+ 2m2n20yz+ 2n2120zx+ 212m20xy

(2.15)

ozz = 130xx + m 3 0 y y+ n 3 o Z z+ 2m3n3oYz+ 2n3130zx+ 2 l 3 m 3 o X y The shear stress component on is the component of the stress vector in the Y direction on a plane perpendicular to the X axis; that is, it is the Y component of the stress vector oxacting on the plane perpendicular to the X axis. Thus, om may be evaluated by forming the scalar product of the vector ax(determined by Eqs. 2.9 and 2.10 with I, = I, ml = m, n1 = n) with a unit vector parallel to the Y axis, that is, with the unit vector (Table 2.2)

N, = 1 2 i + m 2 j + n 2 k

(2.16)

Equations 2.15 and 2.17 determine the stress components relative to rectangular axes ( X , Y, Z ) in terms of the stress components relative to rectangular axes (x, y, z); that is, they determine how the stress components transform under a rotation of rectangular axes. A set of quantities that transform according to this rule is called a second-order symmetrical tensor. Later it will be shown that strain components (see Section 2.7) and moments and products of inertia (see Section B.3) also transform under rotation of axes by similar relationships; hence, they too are second-order symmetrical tensors.

2.4.2

Principal Stresses

For any general state of stress at any point 0 in a body, there exist three mutually perpendicular planes at point 0 on which the shear stresses vanish. The remaining normal stress components on these three planes are called principal stresses. Correspondingly,the three planes are called principal planes, and the three mutually perpendicular axes that are normal to the three planes (hence, that coincide with the three principal stress directions) are called principal axes. Thus, by definition, principal stresses are directed along principal axes that are perpendicular to the principal planes. A cubic element subjected to principal stresses is easily visualized, since the forces on the surface of the cube are normal to the faces of the cube. More complete discussions of principal stress theory are presented elsewhere (Boresi and Chong, 2000). Here we merely sketch the main results.

2.4

2.4.3

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

33

Principal Values and Directions

Since the shear stresses vanish on principal planes, the stress vector on principal planes is given by up= ON,where o i s the magnitude of the stress vector upand N is the unit normal to a principal plane. Let N = li + mj + n k relative to rectangular axes (x,y, z ) with associated unit vectors i, j , k. Thus, (1, m, n) are the direction cosines of the unit normal N.Projections of upalong (x, y, z ) axes are opx = ol, opy= o m , opz= on. Hence, by Eq. 2.10, we obtain

l ( o x x - o ) + m o x y + n o x z= 0 l o + m ( o -o)+noyz = 0

(2.18)

YY

XY

l o x z + m o y z + n ( o z z - o )= 0 Since Eqs. 2.18 are linear homogeneous equations in (1, m, n) and the trivial solution 1 = m = n = 0 is impossible because l2 + m2 + n2 = 1 (law of direction cosines, Eq. 2.13), it follows from the theory of linear algebraic equations that Eqs. 2.18 are consistent if and only if the determinant of the coefficients of (1,m, n) vanishes identically. Thus, we have oxy

=xz

oYY - 0

OY Z

oxx-

oxy

OY Z

OXZ

=o

(2.19)

ozz -

or, expanding the determinant, we obtain 3

2

o - I , o +120-13= 0

(2.20)

where

I , = oxx+oYY + ozz I, =

oxx

oxy

OXY

OYY

+

ox,

=xz

oxz

ozz

+

oyy

oyz

oyz

ozz

(2.21) oxx

I, = oxz

oxy

oxz

OYY

OYZ

oyz

=zz

The three roots (q, 02,03) of Eq. 2.20 are the three principal stresses at point 0.4 The magnitudes and directions of o,,02,and 0,for a given member depend only on the loads being applied to the member and cannot be influenced by the choice of coordinate axes (x,y, z ) used to specify the state of stress at point 0. This means that I , , I,, and Z, given by Eqs. 2.21 are invariants of stress and must have the same magnitudes for all choices of coordinate axes (x,y, z). The stress invariants may be written in terms of the principal stresses as

4Equation2.18 matches the form for the standard eigenvalue problem in which the principal stress o i s an eigenvalue and the direction cosines ( I , m,n) define the associated eigenvector. Likewise, Eq. 2.20 is known as the characteristic polynomial for the eigenvalue problem. Solution methods for eigenvalue problems are presented in many books on numerical methods.

34

CHAPTER 2 THEORIES OF STRESS AND STRAIN

I , = 6,+ o2+ o3

When (q, o,,03) have been determined, the direction cosines of the three principal axes are obtained from Eqs. 2.18 by setting d in turn equal to ( c ~9, , g), respectively, and observing the direction cosine condition l2 + m2 + n2 = 1 for each of the three values of 0.See Example 2.1. In special cases, two principal stresses may be numerically equal. Then, Eqs. 2.18 show that the associated principal directions are not unique. In these cases, any two mutually perpendicular axes that are perpendicular to the unique third principal axis will serve as principal axes with corresponding principal planes. If all three principal stresses are equal, then o,= 0,= 0,at point 0, and all planes passing through point 0 are principal planes. In this case, any set of three mutually perpendicular axes at point 0 will serve as principal axes. This stress condition is known as a state of hydrostatic stress, since it is the condition that exists in a fluid in static equilibrium.

EXAMPLE 2.1 Principal Stresses and Principal Directions

The state of stress at a point in a machine part is given by o , = - 10, oyr = 3 0 , ~= 15, and o, = o,,= oyz = 0; see Figure E2. la. Determine the principal stresses and orientation of the pnncipal axes at the point.

a

I

fN1

#35

FIGURE EZ.1

Solution

By Eq. 2.21 the three stress invariants are

Substituting the invariants into Eq. 2.20 and solving for the three roots of this equation, we obtain the principal stresses 0,=

o2=O0’and

35,

o3 = -15

To find the orientation of the first principal axis in terms of its direction cosines l,, m,, and n,, we substitute o,= 35 into Eq. 2.18 for 0.The direction cosines must also satisfy Eq. 2.13. Thus, we have

-451,

+ 15ml

=0

151, -5ml = 0

-359 = 0 2

2

2

ll+ml+nl = 1

(a>

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

35

Only two of the first three of these equations are independent. Equation (c) gives nl = 0

Simultaneous solution of Eqs. (b) and (d) yields the result 1; = 0.10 ~

~

i '

Or

Z,

I

= k0.3162

I

Substituting into Eq. (b) for Z,, we obtain

m 1 = k0.9487 where the order of the + and - signs corresponds to those of I , . Note also that Eq. (a) is satisfied with these values of Z,, ml,and nl.Thus, the first principal axis is directed along unit vector N1,where

N, = 0.3162i + 0.9487j ; Ox= 71.6"

(el

or

N, = -0.31623 - 0.9487j where i and j are unit vectors along the x and y axes, respectively. The orientation of the second principal axis is found by substitution of o = 9 = 0 into Eq. 2.18, which yields 1, = 0 and m2 = 0 Proceeding as for 0, ,we then obtain

n2 = f 1 from which

N2 = fk where k is a unit vector along the z axis. The orientation of the third principal axis is found in a similar manner:

I , = k0.9487

m3 = ~0.3162 n, = 0

To establish a definite sign convention for the principal axes, we require them to form a right-handed triad. EN, and N, are unit vectors that define the directions of the first two principal axes, then the unit vector N, for the third principal axis is determined by the right-hand rule of vector multiplication. Thus, we have

N, = N , x N , or

N, = (mln2-m2nl)i+(12nl-lln2)j+(11m2-12ml)k

(8)

In our example, if we arbitrarily select N, from Eq. (e) and N2 = +k, we obtain N, from Eq. (9) as N, = 0.94871 - 0.3162j The principal stresses 0,= 35 and 6,= -15 and their orientations (the corresponding principal axes) are illustrated in Figure E2.lb. The third principal axis is normal to the x-y plane shown and is directed outward from the page. The corresponding principal stress is 0,= 0. Since all the stress comox,,and (T ) are zero, this stress state is said to be a state ponents associated with the z direction (c,,, yz. of plane stress in the x-y plane (see the discussion later in this section on plane stress).

36

CHAPTER z THEORIES

EXAMPLE 2.2 Stress Invariants

OF STRESS AND STRAIN

The known stress components at a point in a body, relative to the (x, y, z ) axes, are o , = 20 MPa, ow = 10 MPa, oXy = 30 MPa, ox, = -10 MPa, and oyz = 80 MPa. Also, the second stress invariant is I , = -7800 (a) Determine the stress component ozz. Then determine the stress invariants I, and I, and the three principal stresses.

(b) Show that I,,I,, and I , are the same relative to (x, y , z) axes and relative to principal axes (1,2,3).

Solution

OXX

I3 =

oxy

0x2

cXycry oZy = -163,000 0x2

oyz

ozz

Octahedral Stress

2.4.4

r:

Let (X, Z) be principal axes. Consider the family of planes whose unit normals satisfy the relation Z2 = m = n = with respect to the principal axes (X, Y; Z). There are eight such planes (the octahedral planes, Figure 2.9) that make equal angles with respect to the (X, X Z) directions. Therefore, the normal and shear stress components associated with these planes are called the octahedral normal stress ooct and octahedral shear stress t&. By Eqs. 2.1G2.12, we obtain

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

37

yl

2

FIGURE 2.9

Octahedral plane for I= rn = n = I / & ,

relative t o principal axes (X, K Z).

since for the principal axes oxx= ol,ow = 02,ozz= 03, and om = oyz= om = 0. (See Eqs. 2.21.) It follows that since ( I I , Z2, Z3) are invariants under rotation of axes, we may refer Eqs. 2.22 to arbitrary (x, y, z) axes by replacing I,, Z2, Z3 by their general forms as given by Eqs. 2.21. Thus, for arbitrary (x, y, z) axes, ooct=

1 ADxx + oyy+ ozz)

3

- 1

2

2

2

(2.23)

The octahedral normal and shear stresses play a role in yield criteria for ductile metals (Section 4.4).

2.4.5

Mean and Deviator Stresses

Experiments indicate that yielding and plastic deformation of ductile metals are essentially independent of the mean normal stress om, where (2.24) Comparing Eqs. 2.22-2.24, we note that the mean normal stress omis equal to o,,,. Most plasticity theories postulate that plastic behavior of materials is related primarily to that part of the stress tensor that is independent of om.Therefore, the stress array (Eq. 2.5) is rewritten in the following form:

T = Tm+Td

(2.25)

where T symbolically represents the stress array, Eq. 2.5, and

om T, =

0 (2.26a)

and

T, =

(2.26b)

38

CHAPTER 2 THEORIES OF STRESS AND STRAIN

The array T, is called the mean stress tensor. The array Td is called the deviutoric stress tensor, since it is a measure of the deviation of the state of stress from a hydrostatic stress state, that is, from the state of stress that exists in an ideal (frictionless) fluid. Let (x, y, z) be the transformed axes that are in the principal stress directions. Then, Oxx = 6,'

oyy= 0 2 ,

Ozz = 03,

oxy-

ox. = oyz= 0

and Eq. 2.25 is simplified accordingly. Application of Eqs. 2.21 to Eq. 2.26b yields the following stress invariants for Td:

J, = 0 J , = i 2 - 1- i2, = 3

J , = i 3 - -1i , i 3 =

-1[(01-02)2 + ( 0 2 - 0 3 )

2

+(4-0,)~]

6

+ 22i3 7'

(01-6m)(62--~)(03--m)

The principal directions for T, are the same as those for T. It can be shown that since J , = 0, T, represents a state ofpure shear. The principal values of the deviatoric tensor Tdare

s,

= ol-om =

s,

=

0,- om=

s3=

O3 - om=

3

3

Since S, + S, + S, = 0, only two of the principal stresses (values) of T, are independent. Many of the formulas of the mathematical theory of plasticity are often written in terms of the invariants of the deviatoric stress tensor T,.

2.4.6

Plane Stress

In a large class of important problems, certain approximations may be applied to simplify the three-dimensional stress array (see Eq. 2.3). For example, simplifying approximations can be made in analyzing the deformations that occur in a thin flat plate subjected to inplane forces. We define a thin plate to be a prismatic member of a very small length or thickness h. The middle surface of the plate, located halfway between its ends (faces) and parallel to them, may be taken as the (x, y) plane. The thickness direction is then coincident with the direction of the z axis. If the plate is not loaded on its faces, a,, = o,,= oZr= 0 on its lateral surfaces (z = fh/2). Consequently, since the plate is thin, as a first approximation, it may be assumed that Ozz = Ozx = Ozy =

throughout the plate thickness.

0

(2.29)

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

39

We also assume that the remaining stress components o,, oyy,and ov are independent of z . With these approximations, the stress array reduces to a function of the two variables (x, y). It is called a plane stress array or the tensor of plane stress. Consider a transformation from the (x,y, z ) coordinate axes to the (X, Y, Z) coordinate axes for the condition that the z axis and 2 axis remain coincident under the transformation. For a state of plane stress in the (x,y) plane, Table 2.3 gives the direction cosines between the corresponding axes (Figure 2.10). Hence, with Table 2.3 and Figure 2.10, Eqs. 2.15 and 2.17 yield 2

2

oxx = o,,COS e + oyYsine + 2oXysin e cos e oyy= oxxsin2 8 + oyycos2 8- 2oXysin8cos 8

(2.30)

2 2 oxY= -( oxx- oyy ) sin 8 cos 8 + oxy( cos 8 - sin 8 )

By means of trigonometric double angle formulas, Eq. 2.30 may be written in the form

+ o ) + -(1 oxx- oyy)cos2B + oxysin28 2 yy 2 oyy= -1( o x x + o) - -1( o x x - o )cos28-oxysin28 2 yy 2 YY oXx=

-( 1 oxx

(2.31)

oxy= --(1 oxx- oyy) sin28 + oxycos2B 2

Equations 2.30 or 2.31 express the stress components om,o , and om in the (X, Y) coordinate system in terms of the corresponding stress components o ,, oyy, and oxrin the (x,y ) coordinate system for the plane transformation defined by Figure 2.10 and Table 2.3. Note that the addition of the first two of Eqs. 2.30 yields

and by the three equations of Eqs. 2.30, 2

2

oxxoyv - O X Y = TABLE 2.3

X Y

Z

oxxoyy -oxy

Plane Stress Direction Cosines X

Y

z

1, = case l2 = -sin6 l3 = 0

m, = sin6 m2 = cose m3=0

n1= 0

0

X

FIGURE 2.10 Location of transformed axes for plane stress.

n2 = 0 n3 = 1

40

CHAPTER 2 THEORIES OF STRESS AND STRAIN

Hence, the stress invariants for a state of plane stress are

2.4.7

Mohr’s Circle in Two Dimensions

In the form of Eq. 2.31, the plane transformation of stress components is particularly suited for graphical interpretation. Stress components oxxand om act on face BE in Figure 2.11 that is located at a positive (counterclockwise) angle 8 from face BC on which stress components o , and o act. The variation of the stress components om and om xr with 8 may be depicted graphically by constructing a diagram in which oxxand om are coordinates. For each plane BE, there is a point on the diagram whose coordinates correspond to values of oxxand om Rewriting the first of Eqs. 2.31 by moving the first term on the right side to the left side and squaring both sides of the resulting equation, squaring both sides of the last of Eq. 2.3 1, and adding, we obtain (2.32) Equation 2.32 is the equation of a circle in the om,om plane whose center C has coordinates r

1

(2.33) and whose radius R is given by the relation R =

l m y

(2.34)

Consequently, the geometrical representation of the first and third of Eqs. 2.31 is a circle (Figure 2.12). This stress circle is frequently called Mohr’s circle after Otto Mohr, who employed it to study plane stress problems. It is necessary to take the positive direction of the oxuaxis downward so that the positive direction of 8 in both Figures 2.1 1 and 2.12 is counterclockwise.

FIGURE 2.1 1 Stress components on a plane perpendicular to the transformed Xaxis for plane stress.

2.4

FIGURE 2.12

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

41

Mohr‘s circle for plane stress.

Since o,, oyy, and oxy are known quantities,the circle in Figure 2.12 can be constructed using Eqs. 2.33 and 2.34. The interpretation of Mohr’s circle of stress requires that one known point be located on the circle. When 8= 0 (Figure 2.lo), the first and third of Eqs. 2.31 give

oXx= oXxand oxY= oXy

(2.35)

which are coordinates of point P in Figure 2.12. Principal stresses ol and o.are located at points Q and Q’ in Figure 2.12 and occur when 6 = and 6,+ ~ 1 2measured , counterclockwise from line CP. The two magnitudes of 8 are given by the third of Eqs. 2.31 since o , = 0 when 8 = and 8, + ~ 1 2Note . that, in Figure 2.12, we must rotate through angle 28from line CP, which corresponds to a rotation of 8 from plane BC in Figure 2.11. (See also Eqs. 2.31.) Thus, by Eqs. 2.31, for ox, = 0, we obtain (see also Figure 2.12) tan28 =

2o.y *xx - oyy

(2.36)

Solution of Eq. 2.36 yields the values 8 = 8, and 8, + ~ 1 2 . The magnitudes of the principal stresses ol,o2and the maximum shear stress, , ,z in the (x, y) plane from Mohr’s circle are

(2.37)

and are in agreement with the values predicted by the procedure outliied earlier in this section. Another known point on Mohr’s circle of stress can be located, although it is not needed for the interpretation of the circle. When 8= ~ 1 2the , first and third of Eqs. 2.31 give oXX =

oYY and oxy=-oXy

(2.38)

These coordinates locate point P’ in Figure 2.12, which is on the opposite end of the diameter from point P. Note that Example 2.1 could also have been solved by means of Mohr’s circle.

42

CHAPTER 2 THEORIES OF STRESS AND STRAIN

EXAMPLE 2.3 Mohr's Circle in Two Dimensions

A piece of chalk is subjected to combined loading consisting of a tensile load P and a torque T (Figure E2.3~).The chalk has an ultimate strength 0,as determined in a simple tensile test. The load P remains constant at such a value that it produces a tensile stress 0.510, on any cross section. The torque T is increased gradually until fracture occurs on some inclined surface. Assuming that fracture takes place when the maximum principal stress 0,reaches the ultimate strength o,,determine the magnitude of the torsional shear stress produced by torque T at fracture and determine the orientation of the fracture surface.

Solution

Take the x and y axes with their origin at a point on the surface of the chalk as shown in Figure E2.32. Then a volume element taken from the chalk at the origin of the axes will be in plane stress (Figure E2.27) with ou = 0.5 1o,,oyy = 0, and 0- unknown. The magnitude of the shear stress 0- can be determined from the thus, condition that the maximum principal stress 0,(given by Eq. 2.37) is equal to 0,; 0, =

0.2550,

+

ox. = 0.7000,

,,/wv

Since the torque acting on the right end of the piece of chalk is counterclockwise, the shear stress the volume element (Figure E2.3b) and is therefore negative. Thus,

0- acts down on the front face of

Oxy =

-0.7000"

In other words, 0- actually acts downward on the right face of Figure E2.3b and upward on the left face. We determine the location of the fracture surface first using Mohr's circle of stress and then using Eq. 2.36. As indicated in Figure E2.3c, the center C of Mohr's circle of stress lies on the oXxaxis at distance 0.2550, from the origin 0 (see Eq.2.33). The radius R of the circle is given by Eq. 2.34; R = 0.7450,. When 6 = 0, the stress components Oxx(6 = o) = 0 , = 0.5 l o, and ox,, = o) = oq = -0.7000, locate point

t ax,

FIGURE E2.3

.70mu

C - - - u a l = u " 4

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

43

P on the circle. Point Q representing the maximum principal stress is located by rotating clockwise through angle 28, from point P; therefore, the fracture plane is perpendicular to the X axis, which is located at an angle 8,clockwise from the x axis. The angle 8,can also be obtained from Q.2.36,as the solution of

- 2oxY I - - - -

tan 28

oxx

- 2(0.7000u)= -2.7451 0.5 1 o,

Thus,

8, = -0.6107 rad Since 8,is negative, the X axis is located clockwise through angle 8,from the x axis. The fracture plane is at angle @ from the x axis. It is given as 7T

@ = --/8,1 = 0.9601 rad

2

The magnitude of @ depends on the magnitude of P. If P = 0, the chalk is subjected to pure torsion and @ = n/4. If P / A = o,(whereA is the cross-sectional area), the chalk is subjected to pure tension (T = 0) and 4 = ~ / 2 .

2.4.8

Mohr‘s Circles in Three Dimensions5

As discussed in Chapter 4,the failure of load-carrying members is often associated with either the maximum normal stress or the maximum shear stress at the point in the member where failure is initiated. The maximum normal stress is equal to the maximum of the three principal stresses o,,02,and 0,.In general, we will order the principal stresses so that o,> o2> 0,.Then, o,is the maximum (signed) principal stress and 0,is the minimum principal stress (see Figure 2.13.) Procedures have been presented for determining the values of the principal stresses for either the general state of stress or for plane stress. For plane stress states, two of the principal stresses are given by Eqs. 2.37; the third is o, = 0. Even though the construction of Mohr’s circle of stress was presented for plane stress (ozz= 0), the transformation equations given by either Eqs. 2.30 or 2.31 are not influenced by the magnitude of o,,but require only that ozx= ozy= 0. Therefore, in terms

uNS

FIGURE 2.13

Mohr’s circles in three dimensions.

’In the early history of stress analysis, Mohr’scircles in three dimensions were used extensively. However, today they are used principally as a heuristic device.

44

CHAPTER 2 THEORIES OF STRESS AND STRAIN

of the principal stresses, Mohr's circle of stress can be constructed by using any two of the principal stresses, thus giving three Mohr's circles for any given state of stress. Consider any point in a stressed body for which values of ol,02,and o3are known. For any plane through the point, let the N axis be normal to the plane and the S axis coincide with the shear component of the stress for the plane. If we choose " 0 and oNS as coordinate axes in Figure 2.13, three Mohr's circles of stress can be constructed. As will be shown later, the stress components " 0 and oNS for any plane passing through the point locate a point either on one of the three circles in Figure 2.13 or in one of the two shaded areas. The and is equal maximum shear stress,,z for the point is equal to the maximum value of oNS in magnitude to the radius of the largest of the three Mohr's circles of stress. Hence, (2.39) where, , a = oland omin = o3(Figure 2.13). Once the state of stress at a point is expressed in terms of the principal stresses, three Mohr's circles of stress can be constructed as indicated in Figure 2.13. Consider plane P whose normal relative to the principal axes has direction cosines 1, m, and n. The normal stress oNN on plane P is, by Eq. 2.11,

oNN= 12 o l + m2 0 2 + n2 o3

(2.40)

Similarly, the square of the shear stress oNS on plane P is, by Eqs. 2.10 and 2.12, 2

2 2

2 2

2 2 2 03-0"

oNs= 1 o l + m 0 2 + n

(2.41)

For known values of the principal stresses ol, 02,and o3and of the direction cosines 1, m, and n for plane P, graphical techniques can be developed to locate the point in the shaded area of Figure 2.13 whose coordinates (o", oNS) are the normal and shear stress components acting on plane P. However, we recommend the procedure in Section 2.3 to determine magnitudes for " 0 and oNS. In the discussion to follow, we show that the coordinates (0". oNS) locate a point in the shaded area of Figure 2.13. Since 2

2

2

1 +m +n = 1

(2.42)

Eqs. 2.40-2.42 comprise three simultaneous equations in 12, m2, and n2. Solving for 12, m2, and n2 and noting that l2 2 0, m2 2 0, and n2 2 0, we obtain 2

I =

2 ON,\$ + ( O N N

- O 2 ) ( O N N - O3) 2 0 (01- q ( o 1- 0 3 ) (2.43)

Ordering the principal stresses such that ol > o2> 0 3 , we may write Eqs. 2.43 in the form

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

45

These inequalities may be rewritten in the form

(2.44)

1

9- O,I , 7,= 10, - O,I , = 1 10, - 0,I are the maximum (extreme) magwhere 7,= \$ 1 o,,03)are nitudes of the shear stresses in three-dimensional principal stress space and (o~, the signed principal stresses (see Figure 2.13). The inequalities of Eqs. 2.44 may be interdenote the abscissa and ordinate, respectively, preted graphically as follows: Let (o“, oNS) on a graph (Figure 2.13). Then, an admissible state of stress must lie within a region bounded by three circles obtained from Eqs. 2.44 where the equalities are taken (the shaded region in Figure 2.13). EXAMPLE 2.4 Mohr‘s Circles in Three Dimensions

Solution

The state of stress at a point in a machine component is given by , a = 120 MPa, oYY = 55 MPa, o,,= -85 MPa, a- = -55 MPa, ox,= -75 MPa, and oY2 = 33 MPa. Construct the Mohr’s circles of stress for this stress state and locate the coordinates of points A: (““I, aNSl) and B: (““2, “NS2) for normal and shear stress acting on the cutting planes with outward normal vectors given by N, : ( 1 / b , l / & , 1b)and N2 : ( l / , h , l / & , 0) relative to the principal axes of stress. Substituting the given stress components into Eq. 2.20, we obtain 0~-900‘-18,014~~+471,680= 0 The three principal stresses are the three roots of this equation. They are

c1= 176.80 MPa, o2= 24.06 MPa,

0,= -110.86

MPa

The center and radius of each circle is found directly from the principal stresses as “2

C2:(“1i“3,0)

= (32.97MPa,O),

- “3

R, = “1 - “3 = 143.83 MPa

“1 C, :( 9 . 0 ) = (100.43 MPa, 0), R, =

- “2

= 76.37 MPa

Figure E2.4 illustrates the corresponding circles with the shaded area indicating the region of admissible stress states. The normal and shear stresses acting on the planes with normal vectors N, and N2 are found from Eqs. 2.40 and 2.41: oNs,= 117.51 MPa Point A, oNN1 = 30 MPa,

oNN2 = 100.43 MPa, oNs2= 76.37 MPa

Point €3;

46

CHAPTER 2 THEORIES OF STRESS AND STRAIN

These points are also shown in Figure E2.4. By this method, the correct signs of oNsl and oNs2 are indeand oNs2 are positive or negative. They are terminate. That is, this method does not determine if oNs, plotted in Figure E2.4 as positive values. Note that, since N2 : (l/.&, 1/.&, 0),the third direction cosine is zero and point B lies on the circle with center C3 and radius R,.

ONS

FIGURE E2.4

EXAMPLE 2.5 Three Dimensional Stress Quantities

At a certain point in a drive shaft coupling, the stress components relative to axes (x, y, z) are o , = 80 MPa, oyy= 60 MPa, o,,= 20 MPa, oxy= 20 MPa, ox,= 40 MPa, and oyz= 10 MPa.

(a) Determine the stress vector on a plane normal to the vector R = i + 2j + k.

(b) Determine the principal stresses o,,02,and o3and the maximum shear stress .,,,z (e) Determine the octahedral shear stress T,,, and compare it to the maximum shear stress.

Solution

(a) The direction cosines of the normal to the plane are

By Eqs. 2.10, the projections of the stress vector are

+ opx=[i) (4+ (4

= 65.320 MPa

opy= ( i ) ( 2 0 ) + ( 2 ) ( 6 O ) + [ i ) ( l O )

= 61.237 MPa

(80)

- (20)

- (40)

(20) = 32.660 MPa Hence,

up = 65.3203 + 61.2371 + 32.660k (b) For the given stress state, the stress invariants are (by Eq. 2.21) I , = ~ x x x + ~ y=y160 +bzz

2.4

TRANSFORMATION OF STRESS, PRINCIPAL STRESSES, AND OTHER PROPERTIES

Oxx I3

=

Oxz

Ox)) Oyy OY2 0x2

Comparing,,z,

%y

0yz

47

=0

022

and z ~we~see ~ that,

zmax= 1 . 2 2 3 ~ ~ ~ ~

EXAMPLE 2.6 Stress in a Torsion Bar

The stress array for the torsion problem of a circular cross section bar of radius u and with longitudinal axis coincident with the z axis of rectangular Cartesian axes (x, y, z) is

T=[

0 0

0 0

-GYP

GxP

-Gyp GiP]

where G and pare constants (see Figure E2.6).

(a) Determine the principal stresses at a point x = y on the lateral surface of the bar. (b) Determine the principal stress axes for a point on the lateral surface of the bar.

FIGURE E2.6

Solution

(a) For a point on the lateral surface of the bar, u2 = x 2 + y2 (Figure E2.6). Then, by Eq. (a), I,=O,

2 2 2

12=-Gpa,

I3=0

(a>

48

CHAPTER 2 THEORIES OF STRESS AND STRAIN

Hence, the principal stresses are the roots of

o3+ I , O = o3- G2p2a20 =

o

So the principal stresses are o1 = Gpa,

o3=&pa

0 2 =0,

(b) For the principal axis with direction cosines I, m, and n corresponding to o,,we substitute o,= Cpa into Eq. 2.18 for o.Hence, the direction cosines are the roots of the following equations:

I l ( a x x - o l ) + m1 oX Y + n l o x z = 0 I 1 (TXY + m l ( o y y - ~ l ) + n l o y y=r 0 1, OXZ+ m1 oyz + n1 (oz7 - 0,) = 0 2

2

2

I l + m l + n l = 1.0 where, since x = y = a f A is a point on the lateral surface,

oyy= ozz= oxy= 0

OXX=

0x2

= -GyPIy=

oYZ

=

- --CPa

A a/A

Gx’lx=

- -CPa

A

By Eqs. (b), (c), and 2.13, we obtain

-I1--

=o

“1

j

1 1 = -n2

A

A

- m l + - n=l O

j

A

=0

A A 2

nl

l-3

--‘1 +?-n, 2

-

m

2

2

I I + m l + n l = 2nl = 1.0 Therefore,

nl =

1 _+-

A’

I, =

1

T ~ ,m1 =

1

kZ

So, the unit vector in the direction of ol is

N = T-i1 l

2

_+

2

1 -j -k1 2 / 2

(4

where i, j, k are the unit vectors in the positive senses of axes (x, y, z), respectively. Similarly, for o2 and 03, we find N2 = +-i1 k -j1

&

-- +l. - Z ~T

A

1. 1 z~ k -k

A

(e)

2.4

TRANSFORMATION OF STRESS,PRINCIPAL STRESSES, AND OTHER PROPERTIES

49

The unit vectors N,,N,, N, determine the principal stress axes on the lateral surface for x = y = a/ f i . Note: Since axes x, y may be any mutually perpendicular axes in the cross section, Eqs. (d) and (e) apply to any point on the lateral surface of the bar.

EXAMPLE 2.7 Design Specifications for an Airplane Wing Member

In a test of a model of a short rectangular airplane wing member (Figure E2.7a), the member is subjected to a uniform compressive load that produces a compressive stress with magnitude 0,.Design specifications require that the stresses in the member not exceed a tensile stress of 400 MPa, a compressive stress of 560 MPa, and a shear stress of 160 MPa. The compressive stress 0,is increased until one of these values is reached.

(a) Which value is first attained and what is the corresponding value of GO? (b) Assume that 0,is less than 560 MPa. Show that 0,can be increased by applying uniform lateral stresses to the member (Figure E2.7b), without exceeding the design requirements. Determine the to allow 0,to be increased to 560 MPa. values of 0, and oyy

(4 FIGURE E2.7

Solution

(a) Since the stress state of the member is uniform axial compression in the z direction, the tensile stress limit will not be reached. However, the shear stress limit might control the design. By Eq. 2.39, the maximum shear stress is given by

1

zmax=

(a)

+Omax-Omin)

By Figure E2.7a. 0 , = oyy = oXy = oxz= oyz= 0, and ozz = -ow Hence, om, = 0 and omi, = -00. Therefore, with, ,z = 160 MPa, Eq. (a) yields 0, =

320MPa

Thus, the shear stress limit is reached for 0,= 320 MPa. (b) By Figure E2.7b, the member is subjected to uniform uniaxial stresses in thex, y, and z directions. Hence, the principal stresses are

o1 =

OXX, 0,

= Ory,

0, =

o,, =

-0,

Then, by Eqs. (b) and 2.44 and Figure 2.13, the extreme values of the shear stresses are given by 1

71

=

2(02-03)

72

=

2(0' - 03)

73

=

1 p1

1

-02)

(b)

50

CHAPER 2 THEORIES OF STRESS AND STRAIN

For shear stress to control the design, one of these shear stresses must be equal to 160 MPa. We first consider the possibility that 7, = 160 MPa. Since o,, = -0,and o0is a positive number, Eqs. (b) and the first of Eqs. (c) yield 00

= 320 - 02

(4

Next we consider the possibility that z2 = 160 MPa. By Eqs. (b) and the second of Eqs. (c), we find 00

= 320 - 01

(el

For 6,= 0,= 0, Eqs. (d) and (e) yield o0= 320 MPa, as in part (a).Also note that, for O, and o2negative (compression),Eqs. (d) and (e) show that o0can be increased (to a larger compressive stress) without exceeding the requirement that, , ,z not be larger than 160 MPa. Finally note that, for o0= 560 MPa (560 MPa compression), Eqs. (d) and (e) yield

o1= a2= -240 MPa

2.5 DIFFERENTIAL EQUATIONS OF MOTION OF A DEFORMABLE BODY In this section, we derive differential equations of motion for a deformable solid body (differential equations of equilibrium if the deformed body has zero acceleration). These equations are needed when the theory of elasticity is used to derive load-stress and loaddeflection relations for a member. We consider a general deformed body and choose a differential volume element at point 0 in the body as indicated in Figure 2.14. The form of the differential equations of motion depends on the type of orthogonal coordinate axes employed. We choose rectangular coordinate axes (x, y, z) whose directions are parallel to the edges of the volume element. In this book, we restrict our consideration mainly to small displacements and, therefore, do not distinguish between coordinate axes in the deformed state and in the undeformed state (Boresi and Chong, 2000). Six cutting planes bound the volume element shown in the free-body diagram of Figure 2.15. In general, the state of stress changes with the location of point 0. In particular, the stress components undergo changes from one face of the volume element to another face. Body forces (Bx,By, B,) are included in the free-body diagram. Body forces include the force of gravity, electromagnetic effects, and inertial forces for accelerating bodies.

FIGURE 2.14

General deformed body.

t

DIFFERENTIALEQUATIONS OF MOTION OF A DEFORMABLEBODY

2.5

51

FIGURE 2.15

Stress components showing changes from face to face along with body force per unit volume including inertial forces.

To write the differential equations of motion, each stress component must be multiplied by the area on which it acts and each body force must be multiplied by the volume of the element since (B,, By, B,) have dimensions of force per unit volume. The equations of motion for the volume element in Figure 2.15 are then obtained by summation of these forces and summation of moments. In Section 2.3 we have already used summation of moments to obtain the stress symmetry conditions (Eqs. 2.4). Summation of forces in the x direction gives6

do,, Joy, do,, + B, = 0 ++dx ay m where on,or,= oxr, and ox, = 0, are stress components in the x direction and B, is the body force per unit volume in the x direction including inertial (acceleration) forces. Summation of forces in the y and z directions yields similar results. The three equations of motion are thus

-do+,,- + -day,

do,, + B , = 0 &

oxy -d & + - + -do,, ay

dozy

dx

ay

A

+BY=o

do,, + Joy. do,, + B , +dx ay m

(2.45)

=0

As noted earlier, the form of the differential equations of motion depends on the coordinate axes; Eqs. 2.45 were derived for rectangular coordinate axes. In this book we also need differential equations of motion in terms of cylindrical coordinates and plane 6Note that a, on the left face of the element goes to o , + do, = o, + (aa,/dx)d* on the right face of the element, with similar changes for the other stress components (Figure 2.15).

Next Page

52

CHAPTER 2 THEORIES OF STRESS AND STRAIN

polar coordinates. These are not derived here; instead, we present the most general form from the literature (Boresi and Chong, 2000, pp. 204-206) and show how the general form can be reduced to desired forms. The equations of motion relative to orthogonal curvilinear coordinates (x,y, z) (see Figure 2.16) are

d(P.yoxx>+ J ( Y a o y x > d(aPo,,) da + YOyxdX dr dZ dr +

(2.46)

ao d p + a P y B , = 0 yy

dz

where (a,P, y ) are metric coefficients that are functions of the coordinates (x,y, z). They are defined by 2

2

ds = a d x

2

+P 2d y 2 + y2d z 2

(2.47)

where ds is the differential arc length representing the diagonal of a volume element (Figure 2.16) with edge lengths a &, P dy, and ydz, and where (Bx,By, B,) are the components of body force per unit volume including inertial forces. For rectangular coordinates, a = P = y= 1 and Eqs. 2.46 reduce to Eqs. 2.45.

2.5.1

Specialization of Equations 2.46

Commonly employed orthogonal curvilinear systems in three-dimensional problems are the cylindrical coordinate system (r, 8, z ) and spherical coordinate system (r, 8, \$); in plane problems, the plane polar coordinate system (r, 8) is frequently used. We will now specialize Eqs. 2.46 for these systems.

(a) Cylindrical Coordinate System (r, 6, z). In Eqs. 2.46, we let x = r, y = 8, and z = z. Then the differential length ds is defined by the relation

ds2 = dr2 + r 2 d 8 + dz2

a&

FIGURE 2.16

Orthogonal curvilinear coordinates.

(2.48)

Previous Page 2.5

DIFFERENTIAL EQUATIONSOF MOTION OF A DEFORMABLE BODY

53

A comparison of Eqs. 2.47 and 2.48 yields

a=l, P = r , y = l

(2.49)

Substituting Eq. 2.49 into Eqs. 2.46, we obtain the differential equations of motion 'or, I'o~, -+--+-+

dr

rd8

dozy

orr-088

dz

r

+B, = 0 (2.50)

where (err, 060, o,,,Ore, o,, GOz) represent stress components defined relative to cylindrical coordinates (r, 8, z). We use Eqs. 2.50 in Chapter 1 1 to derive load-stress and loaddeflection relations for thick-wall cylinders. (b) Spherical Coordinate System (48, @). In Eqs. 2.46, we let x = r, y = 8, and z = @, where r is the radial coordinate, 8 is the colatitude, and Cp is the longitude. Since the differential length ds is defined by ds2 = dr2 + r2d82+ [email protected]

(2.51)

comparison of Eqs. 2.47 and 2.51 yields

a = 1,

p

= r,

y = rsin8

(2.52)

Substituting Eq. 2.52 into Eqs. 2.46, we obtain the differential equations of motion

3 + 1 8 0 d, -o- + - ( 3 1a , ga*,+, 2 0 1 dr r d8 rsin8 dCp r

ee

cote)+Bo =

o

where (err, oee, oocOre, or+oe4)are defined relative to spherical coordinates (r, 8, @).

(c) Plane Polar Coordinate System (r, 8). In plane-stress problems relative to (x,y) coordinates, o,,= ox,= oyz= 0, and the remaining stress components are functions of (x,y) only (Section 2.4). Letting x = r, y = 8, and z = z in Eqs. 2.50 and noting that o,,= or,= o, = (d/aZ)= 0, we obtain from Eq. 2.50, with a = 1, p = r, and y= 1,

(2.54)

54

2.6

CHAPTER 2 THEORIES OF STRESS AND STRAIN

DEFORMATION OF A DEFORMABLE BODY In this and the next section we consider the geometry of deformation of a body. First we examine the change in length of an infinitesimal line segment in the body. From that, finite strain-displacement relations are derived. These are then simplified according to the assumptions of small-displacement theory. Additionally, differential equations of compatibility, needed in the theory of elasticity, are derived in Section 2.8. In the derivation of strain-displacement relations for a member, we consider the member first to be unloaded (undeformed and unstressed) and next to be loaded (stressed and deformed). We let R represent the closed region occupied by the undeformed member and R* the closed region occupied by the deformed member. Asterisks are used to designate quantities associated with the deformed state of members throughout the book. Let (x,y, z) be rectangular coordinates (Figure 2.17). A particle P is located at the general coordinate point (x,y, z ) in the undeformed body. Under a deformation, the particle moves to a point (x*,y*, z*) in the deformed state defined by the equations

x* = x*(x, y, z) Y* = Y*(X, y, z ) z* = z*(x, y, 2 )

(2.55)

where the values of (x,y, z ) are restricted to region R and (x*, y*, z*) are restricted to region R*. Equations 2.55 define the final location of a particle P that lies at a given point (x,y, z) in the undeformed member. It is assumed that the functions (x*,y*, z*) are continuous and differentiable in the independent variables (x,y, z), since a discontinuity of these functions would imply a rupture of the member. Mathematically, this means that Eqs. 2.55 may be solved for single-valued solutions of (x,y, z); that is,

x = x(x*,y*,z*) y = Y(X*, Y*, 2") z = z(x*,y*,z*)

(2.56)

Equations 2.56 define the initial location of a particle P that lies at point (x*,y*, z*) in the deformed member. Functions (x,y, z ) are continuous and differentiable in the independent variables (x*,y*, z*).

q,. .,,

y3

FIGURE 2.17

-*;

Location of general point Pin undeformed and deformed body.

2.7

STRAIN THEORY, TRANSFORMATIONOF STRAIN, AND PRINCIPALSTRAINS

55

2.7 STRAIN THEORY, TRANSFORMATION OF STRAIN, AND PRINCIPAL STRAINS’ The theory of stress of a continuous medium rests solely on Newton’s laws. As is shown in this section, the theory of strain rests solely on geometric concepts. Both the theories of stress and strain are, therefore, independent of material behavior and, as such, are applicable to the study of all materials. Furthermore, although the theories of stress and strain are based on different physical concepts, mathematically, they are equivalent, as will become evident in the following discussion.

2.7.1

Strain of a Line Element

When a body is deformed, the particle at point P : (x, y, z) passes to the point P* :(x*, y*, z*) (Figure 2.18). Also, the particle at point Q : ( x + dx,y + dy, z + dz) passes to the point Q* :(x* + dx*, y* + dy*, z* + dz*), and the infinitesimal line element PQ = ds passes into the line element P*Q* = ds*. We define the engineering strain eEof the line element PQ = ds as EE

dS* - d s ds

(2.57)

= -

Therefore, by this definition, eE> -1. Equation 2.57 is employed widely in engineering. The definition of strain given in Eq. 2.57 is not unique. That is, other, equally valid definitions of strain have been proposed. Here we also develop an alternative definition of strain, known as Green strain. By Eqs. 2.55, we obtain the total differential

ax*

dX* = -dX dx

/I Y

/ /

FIGURE 2.18

ax* + -dy

dy

ax* + -dz

dz

(2.58)

.

,-------R*

\

\

‘.

Line segment PO in undeformed and deformed body.

7Thetheory presented in this section includes quadratic terms in the displacement components (u, v, w)and in the engineering strain cE One may discard all quadratic terms in u, v, w,and cEand directly obtain the theory of strain for small deformations. (See Section 2.8.)

56

CHAPTER 2 THEORIES OF STRESS AND STRAIN

with similar expressions for dy* and dz*. Noting that x* = x + u (2.59)

y* = y + v

z* = z + w where (u, v, w ) denote the (x, y, z ) components of the displacement of P to P*, and also noting that (ds)" = (dx)'

+ (dy)' + (dz)' 2

2

(2.60)

2

(ds*)2 = (dx*) + ( d y * ) + ( d z * )

we find' [retaining quadratic terms in derivatives of (u, v, w ) ]

2

2

+ m kY X + m E YY + m nYZ~ + n l ~ , , + n r n e z y + ne Z Z = 12 e X x + m2 E + n2 ~ , , + 2 1 m ~+ 2 1 n ~ , ~ + 2 r n n ~ ~ , YY

(2.61)

XY

where M is called the magnification factor. The magnification factor M is a measure of the strain of a line in the body with direction cosines (I, m, n). This quantity is also known as the total Green strain. The components of Green strain, from Eq. 2.61, are

(2.62)

EXZ

-

EZX

=

1 & -+ ax

2

(

-I

du ad& dVay+&& -+--+-dz ax& ax& ax dz

where (2.63) 'Although one may compute eEdirectly from Eq. 2.57, it is mathematically simpler to form the quantity M = [(ds*/ds)* - 11 = f [(I + eE)*- I] = eE+ f e t . Then one may compute eEfrom Eq. 2.61. For small E E (Section 2.8), eE= M . A more detailed derivation of Eq. 2.61 is given by Boresi and Chong (2000, Section 2-6).

1

2.7

STRAIN THEORY, TRANSFORMATIONOF STRAIN, AND PRINCIPALSTRAINS

57

are the direction cosines of line element ds. These are the finite strain-displacement relations. They are valid for any magnitude of displacement (u, v, w)of the body? We may interpret the quantities E,, eyU,and ezz physically, by considering line elements ds that lie parallel to the (x, y, z ) axes, respectively. For example, let the line element ds (Figure 2.18) lie parallel to the x axis. Then I = 1, m = n = 0, and Eq. 2.61 yields (2.61a) where M, and eExdenote the magnification factor and the engineering strain of the element ds (parallel to the x direction). Hence, E,, physically, is the magnification factor of the line element at P that lies initially in the x direction. In particular, if the engineering ~ , E>\$. By geometry of the circle, the strain quantities are by points S ( E ' ~ E\$) , ;€

= OC+ R Cos(2w-2e) = 329p

Eiy

= O C - R C O S ( ~ I Y - ~=~2) 7 i p

E;,,

= -Rsin(28'-28)

= 295p

In Figure E2.10b, the deformed shape of an element in the reference orientation is shown. Also illustrated is the deformed shape in the principal orientation, which is at an angle of 8 = -14.87" with respect to the x axis. Notice that in this orientation, the deformed element is not distorted, since the shear strain is zero. Finally, the deformed shape at 8' = 25" with respect to the reference orientation is shown.

0Deformed r-

-1 Undeformed

4-

= 461p

I FIGURE E2.10 orientations.

(0)

2-

orientation

(h)

(a) Mohr's circle for plane strain. ( b ) Deformed element in three different

~

2.8

EXAMPLE 2.1 1 Integration ot the StrainDisplacement Relations for SmallDisplacemeni Theory

SMALL-DISPLACEMENTTHEORY

69

For small-displacement plane strain, the strain components in the plate ABCD (Figure E2.1 I), in terms of the coordinate system (x, y ) , are

where A, C, and D are known constants. The displacement components (u. v) at x = y = 0 are

u(0,O) = 0,

v(0,O) = 0

(b)

and the slope &/dy at x = y = 0 is

=o

(c)

Determine u and v as functions of (x, y ) .

FIGURE E2.11

Solution

By Eqs. 2.81 and (a), we have

EX. = C y ( L - x ) = a4 dX Eyy

= Dy(L-x) =

yXY = 2eXy= -(C

av

&

+ D ) ( A2 - y 2 )

=

a-4+av dy ax

(f)

Integration of Eqs. (d) and (e) yields u = cy(Lx-;x*)+Y(y)

1

2

v = -Dy (L-x)+X(x)

2

where X and Y are functions of x and y, respectively. Substituting Eqs. (g) and (h) into Eq. (f) and regrouping terms, we obtain dY 1 d x + c L x - 5 = --+-Dy dx 2’) dy 2

(

2

2

2

-(C+D)(A -y )

70

CHAPTER 2 THEORIES

OFSTRESS AND STRAIN

For Eq. (i) to be satisfied, both sides of the equation must be equal to the same constant. That is, =E

"dx+ C ( L x - i x 2 )

dY 1 --+-Dy dY 2

2

(i) 2

2

-(C+D)(A -y ) = E

(k)

where E is a constant. Then integrations of Eqs. (j) and (k) yield

X(x) =

-c 1

:

(1

-Lx ---x

3,

+Ex+./

3

Y ( y ) = -Dy -(C+D) 6 where J and K are constants. By Eqs. (g), (h), (l), and (m), we find

I' 1

y+F

(n)

2

v = -Dy ( L - x ) - C 2

(0)

By Eqs. (b), (n), and (o),F = 0 and J = 0. Then by Eqs. (c) and (n), E is determined as

E = (c+D)A~ Equations (n) and (0)are modified accordingly.

2.9

STRAIN MEASUREMENT AND STRAIN ROSElTES For members of complex shape subjected to loads, it may be mathematically impractical or impossible to derive analytical load-stress relations. Then, either numerical or experimental methods are used to obtain approximate results. Several experimental methods are used, the most common one being the use of strain gages. Strain gages are used to measure extensional strains on the free surface of a member or the axial extension/contraction of a bar. They cannot be used to measure the strain at an interior point of a member. To measure interior strains (or stresses),other techniques such as photoelashcity may be used, although this method has been largely superseded by modem numerical techniques. Nevertheless, photoelastic methods are still useful when augmented with modem computer data-acquisition techniques (Kobayashi, 1987). Additional experimental procedures are also available. They include holographic, Moirk, and laser speckle interferometry techniques. These specialized methods lie outside of the scope of this text (see Kobayashi, 1987). We shall discuss only the use of electrical resistance (bonded) strain gages. Electric strain gages are used to obtain average extensional strain over a given gage length. These gages are made of very fine wire or metal foil and are glued to the surface of the member being tested. When forces are applied to the member, the gage elongates or contracts with the member. The change in length of the gage alters its electrical resistance. The change in resistance can be measured and calibrated to indicate the average extensional strain that occurs over the gage length. To meet various requirements, gages are made in a variety of gage lengths, varying from 4 to 150 mm (approximately 0.15 to 6 in.), and are designed for different environmental conditions.

2.9

FIGURE 2.20

STRAIN MEASUREMENT AND STRAIN ROSETTES

b

b

(a)

(b)

71

Rosette strain gages. ( a )Delta rosette. ( b ) Rectangular rosette.

Three extensional strain measurements in three different directions at a point on the surface of a member are required to determine the average state of strain at that point. Consequently, it is customary to cluster together three gages to form a strain rosette that may be cemented to the free surface of a member. Two common forms of rosettes are the delta rosette (with three gages spaced at 60" angles) and the rectangular rosette (with three gages spaced at 45" angles), as shown in Figure 2.20. From the measurement of extensional strains along the gage arm directions (directions a, b, c in Figure 2.20), one can determine the strain components (en, eYy,E ) at the point, relative to the (x, y) axes. xy Usually, one of the axes is taken to be aligned with one arm of the rosette, say, the arm a. For instance, we might mount the rosette such that = E,, the average extensional strain in the direction a . Then, the components (eYy,eXy)may be expressed in terms of the measured extensional strains E,, Eb, and E, in the directions of the three rosette arms a, b, and c, respectively. (See Example 2.12.)

EXAMPLE 2.12 Measurement oi Strain on a Surface of a Member

A strain rosette with gages spaced at an angle 8 is cemented to the free surface (eZz= eXZ= eYz= 0) of a member (Figure E2.12). Under a deformation of the member, the extensional strains measured by gages a, b, c are E,, q,, E,, respectively.

(a) Derive equations that determine the strain components E,, eYy,E~ in terms of E,,

Eb, E,,

and 8.

(b) Specialize the results for the delta rosette (8= 60")and rectangular rosette (8= 45"). c

FIGURE E2.12

Solution

(a) The direction cosines of arms a, b, and c are, respectively, ( l a ,ma, nu) = (1 ,O,O), (lb, mb, nb) = (cos 8, sine, 0), ( l , , m,, n,) = (cos 28, sin 2 8 , O ) The extensional strain of a line element in the direction (1, m, n) is given by Eq. 2.61. Hence, by Eq. 2.61, the extensional strains in the directions of arms a, b, c are Ea

=

EXX

2

2

eb = E ~ ~ ( C8) O+ S eyY(sin 8) + 2exy(cos 8)(sine) E,

2

2

= E,,(COS 28) + Eyy(sin 28) + ~E,..(cos %)(sin 28)

72

CHAPTER 2 THEORIES OF STRESS AND STRAIN

Equations (a) are three equations that may be solved for eXx, eYy,and E~ in terms of E,, eb, and ec for a given angle 8. The solution is 'xx

= a'

E

=

(E,

YY

- 2eb) sin 40 + 2ec sin 28

4 [email protected] B 2

e

XY

=

2

2ea(sin Bcos 28-sin

2

2

2

2

B c o s 8)+2(ebsin 2f3-Ecsin 8)

4sin2e sin20

(b) For 8 = 60",cos 8 = 112, sin 8 = &/2, cos 28= -112, and sin 2 8 = &/2. Therefore, for 8 = 60", Fqs. (b) yield 'xx

For8=45",cos 8 = I/,&, yield

- 'a1

'yy

-

2(Eb + E c ) - E,

,

Exy

=

Eb - E C

-

3

J3

(c)

s i n @ =1/&, c o s 2 8 = 0 , a n d s i n 2 8 = I.Therefore,for8=45",Eqs. (b)

exx = Ea>

Eyy

-

Ec,

Exy

=

Eb-

1 pa +

(4

EC)

PROBLEMS Sections 2.1-2.4 Many of the problems for Sections 2.1-2.4 require the determination of principal stresses and maximum shear stress, as well as the location of the planes on which they act. These quantities are required input in design and failure criteria for structural and mechanical systems.

2.1. The state of stress at a point in a body is given by the following components: on = 50 MPa, oyY= -30 MPa, o,, = 20 MPa, ov = 5 MPa, ox,= -30 MPa, and oyz= 0. Find o,,, opy, o,,,and opsfor point P on a cutting plane Q with normal I/ vectorN: (11 A, 1/ 2.2. The thin, flat plate shown in Figure P2.2 is subjected to uniform shear stress. Find the normal and shear stress acting on the cutting plane A-A.

a, a).

rlA FIGURE PZ.2

2.3. At a point in a beam, the stress components are o , = 20 MPa, ox,= lo& MPa, and oYY= o,,= oq = oy,= 0.

a. Determine the principal stresses ol2 oz2 0,.

b. Determine the direction cosines of the normal to the plane on which ol acts.

2.4. The stress components at a point in a plate are qrx= -100 MPa, oYY = o,,= 20 MPa, oq = oY, = 0, and ox, = -80 MPa. a. Determine the principal stresses ol 2 oz2 0,. b. Determine the octahedral shear stress. c. Determine the maximum shear stress and compare it to the octahedral shear stress. d. Determine the direction cosines of the normal to one of the planes on which the maximum shear stress acts. 2.5. The stress components at a point in a plate are q, = 80 MPa, oYy= 60 MPa, o,,= oxY = 20 MPa, o,,= 40 MPa, and oYz= 10 MPa. a. Determine the stress vector on a plane normal to the vector i + 2j + k. b. Determine the principal stresses o,2 o22 0,. c. Determine the maximum shear stress. d. Determine the octahedral shear stress. 2.6. The stress array (Eq. 2.5) relative to axes (x,y , z ) is given by

.=[I

a]

where the stress components are in [MPa].

PROBLEMS

a. Determine the stress invariants of T b. Consider a rotation of the (x, y) axes by 45" counterclockwise in the (x, y) plane to form axes (X, Y). Let the Z axis and the z axis coincide. Calculate the stress components relative to axes (X, r, Z). Note that the direction cosines between axes (x,y, z) and (X, r, Z) are given by Table 2.2, where the rotation of 45" determines l,, m I , n I , . . . . c. With the results of part (b), determine the stress invariants relative to axes (X, Y, Z)and show that they are the same as the invariants of part (a).

2.7. Relative to axes (x, y, z), body A is loaded so that o , = oo and the other stress components are zero. A second body B is loaded so that q, = 7, and the other stress components are zero. The octahedral shear stress roc,has the same value for both bodies. Determine the ratio odzo. 2.8. The stress components at a point in a flywheel are O, = oYy= o,,= 0 and oq = o,,= oY,= 70. a. In terms of ,z, calculate the principal stresses. b. Determine the directions of the principal stress axes, insofar as they are determinate. 2.9. The principal stresses ol and 0,are known, and o,2 o22 q.Determine the value of o2for which the octahedral shear stress roc,attains an extreme value. 2.10. The nonzero stress components relative to axes (x, y, z) are o,,= -90 MPa, ayy = 50 MPa, and oq = 6 MPa. a. Determine the principal stresses, o,2 9I 0,. b. Calculate the maximum shear stress. c. Calculate the octahedral shear stress. d. Determine the angle between the x axis and the X axis, where X is in the direction of the principal stress 0,. 2.11. Let (ax, ay,a,)be stress vectors on planes perpendicular, respectively, to the (x. y, z) axes. Show that the sum of the squares of the magnitudes of these stress vectors is an invariant, expressible in terms of the stress invariants I, and IF 2.12. Determine the principal stresses and their directions for each of the sets of stress components listed in Table P2.12. Also calculate the maximum shear stress and the octahedral shear stress. The units of stress are [MPa]. TABLE P2.12 *xx

oyz

oyy

022

*xy

0x2

(a) (b) (c)

15

-4

-3

0

1

10 -10

-5

10

0 3 2

0

(d)

-5 -5 -5

10 0 10 -5

(el

10

0

0

0

0

2 2 0

4 0

2.13. The state of stress at a point is specified by the following , = oyy = o,,= 0, oq = -75 MPa, oyz= stress components: 0

73

65 MPa, and 0 , = -55 MPa. Determine the principal stresses, direction cosines for the three principal stress directions, and maximum shear stress.

2.14. Consider a state of stress in which the nonzero stress com,, oyy, o,,,and o Note that this is not a state of ponents are o ": plane stress since o,,# 0. Consider another set of coordinate axes (X, r, Z),with the Z axis coinciding with the z axis and the X axis located counterclockwise through angle 8 from the x axis. Show that the transformation equations for this state of stress are identical to Eq. 2.30 or 2.31 for plane stress. 2.15. The state of stress at a point is specified by the following , = 110 MPa, oyy= -86 MPa, o,,= stress components: o 55 MPa, oq = 60 MPa, and cry, = 0, = 0. Determine the principal stresses, direction cosines of the principal stress directions, and maximum shear stress. 2.16. Solve Problem 2.15 using the transformation equations for plane stress (Eq. 2.30 or 2.31). 2.17. The state of plane stress is specified by the following stress components: o , = 90 MPa, oyy = -10 MPa, and oq = 40 MPa. Let the X axis lie in the (x,y) plane and be located at 8= n;/6clockwise from the x axis. Determine the normal and shear stresses on a plane perpendicular to the X axis; use Eqs. 2.10-2.12. In Problems 2.18 through 2.21, the Z axis for the transformed axes coincides with the z axis for the volume element on which the known stress components act.

2.18. The nonzero stress components are ox,= 200 MPa, oyy= 100 MPa, and oq = -50 MPa. Determine the principal stresses and maximum shear stress. Determine the angle between the X axis and the x axis when the X axis is in the direction of the principal stress with largest absolute magnitude. 2.19. The nonzero stress components are 0 , = -90 MPa, oyy= 50 MPa, and ov = 60 MPa. Determine the principal stresses and maximum shear stress. Determine the angle between the X axis and the x axis when the X axis is in the direction of the principal stress with largest absolute magnitude. 2.20. The nonzero stress components are o,, = 80 MPa, ozz= -60 MPa, and oq = 30 MPa. Determine the principal stresses and maximum shear stress. Determine the angle between the X axis and the x axis when the X axis is in the direction of the principal stress with largest absolute magnitude. 2.21. The nonzero stress components are o , = 150 MPa, oyy= 70 MPa, o,,= -80 MPa, and q,,= -45 MPa. Determine the principal stresses and maximum shear stress. Determine the angle between the X axis and the x axis when the X axis is in the direction of the principal stress with largest absolute magnitude. 2.22. Using transformation equations of plane stress, determine oxxand ox, for the X axis located 0.50 rad clockwise from the x axis. The nonzero stress components are given in Problem 2.18.

74

CHAPTER 2 THEORIES OF STRESS AND STRAIN

2.23. Using transformation equations of plane stress, determine oxxand ox,for the X axis located 0.15 rad counterclockwise from the x axis. The nonzero stress components are given in Problem 2.19. 2.24. Using transformation equations of plane stress (see Problem 2.14), determine oxxand oxyfor the X axis located 1.00 rad clockwise from the x axis. The nonzero stress components are given in Problem 2.20. 2.25. Using transformation equations of plane stress (see Problem 2.14), determine oxxand ox,for the X axis located 0.70 rad counterclockwise from the x axis. The nonzero stress components are given in Problem 2.21. 2.26. Using Mohr's circle of stress, determine oxxand oxyfor the X axis located 0.50 rad clockwise from the x axis. The non, = 200 MPa, oyV= 100 MPa, zero components of stress are o and oxy= -50 MPa. 2.27. Using Mohr's circle of stress, determine oxxand oxyfor the X axis located 0.15 rad counterclockwise from the x axis. The nonzero components of stress are cr, = -90 MPa, aYy= 50 MPa, and oq = 60 MPa. 2.28. Using Mohr's circle of stress, determine oxxand oxyfor the X axis located 1.OO rad clockwise from the x axis. The nonzero components of stress are o , = 80 MPa, o,,= -60 MPa, and oq = 30 MPa. 2.29. Using Mohr's circle of stress, determine oxxand ox,for the X axis located 0.70 rad counterclockwise from the x axis. , = 150 MPa, oyy= The nonzero components of stress are 0 70 MPa, o,, = -80 MPa, and oxr = -45 MPa. 2.30. A volume element at the free surface is shown in Figure P2.30. The state of stress is plane stress with o , = 100 MPa. Determine the other stress components.

uxx= 120 MPa

%x

= 01

-3

X

FIGURE P2.31

X

FIGURE P2.32

F'

uv

uXx = 80 MPa

FIGURE P2.30

2.31. Determine the unknown stress components for the volume element in Figure P2.31. 2.32. Determine the unknown stress components for the volume element in Figure P2.32. 2.33. Determine the unknown stress components for the volume element in Figure P2.33.

FIGURE p2-33

PROBLEMS

75

In Problems 2.34 through 2.38, determine the principal stresses, maximum shear stress, and octahedral shear stress.

2.42. The state of stress at a point is given by o , = -90 MPa, oyy= -60 MPa, o,,= 40 MPa, oxy = 70 MPa, oy,= -40 MPa,

2-34. The nonzero stress components are

= -100 MPa,

, = -55 MPa. Determine the three principal stresses and and 0 maximum shear stress.

2.35. The nonzero stress components are ,0 = 180 MPa, oyy= 90 MPa, and oxy = 50 MPa. 2.36. The nonzero stress components are o , = -150 MPa, oyy= -70 MPa, o,,= 40 MPa, and oxy = -60 MPa. 2.37. The nonzero stress components are oxx= 80 MPa, oyy=

2-43. The state of Stress at a point is given by oxx= -150 MPa, oyy= 0, o,,= 80 MPa, oxy= -40 MPa, oy,= 0, and o, =

,0

oyy = 60 MPa, and oxy = -50 MPa.

-35 MPa, o,,= -50 MPa, and oxy = 45 MPa.

2.38. The nonzero stress components are o , = 95 MPa, oyy= 0,

o,,= 60 MPa, and oq = -55 MPa. 2.39. The state of stress at a point is given by , a = -120 MPa, oyy= 140 MPa, o,,= 66 MPa, oxy = 45 MPa, oy,= -65 MPa, and o , = 25 MPa. Determine the three principal stresses and directions associated with the three principal stresses.

2.40. The state of stress at a point is given by o , = 0, oyy= 100 MPa, o, = 0, oxy= -60 MPa, oyz= 35 MPa, and 0, = 50 MPa. Determine the three principal stresses.

2.41*The state Of stress at a point is given by = 120 MPa, oyy= -55 MPa, o,,= -85 MPa, oq = -55 MPa, oyz= 33 MPa, and o, = -75 MPa. Determine the three principal stresses and maximum shear stress.

50 MPa. Determine the three principal stresses and maximum shear stress.

2.44. a. Solve Example 2.1 using Mohr's circle and show the orientation of the volume element on which the principal stresses act. b. Determine the maximum shear stress and show the orientation of the volume element on which it acts.

2.45. At a point on the flat surface of a member, load-stress relations give the following stress components relative to the (x, y, z) axes, where the z axis is perpendicular to the surface: o , = 240 MPa, oyy= 100 MPa, oxy = -80 MPa, and o,,= ox,= oy, = 0. a. Determine the principal stresses using Eq. 2.20 and then again using Eqs. 2.36 and 2.37. b. Determine the principal stresses using Mohr's circle and show the orientation of the volume element on which these principal stresses act. c. Determine the maximum shear stress and maximum octahedral shear stress.

Sections 2.5-2.8 The problems for Sections 2.5-2.8 involve displacements, deformations, and strain states at a point in a structural or machine member. These quantities, as with their stress counterparts, are important in design and failure criteria.

2.46. Verify the reduction of Eqs. 2.46 to Eqs. 2.50. 2.47. Verify the reduction of Eqs. 2.46 to Eqs. 2.53. 2.48. Verify the reduction of Eqs. 2.50 to Eqs. 2.54. 2.49. Show that Eqs. 2.65-2.67 yield Eqs. 2.68. 2.50. By the procedure outlined in the text, derive Eq. 2.7 1. 2.51. By the procedure outlined in the text, derive Eq. 2.76d. 2.52. By the procedure outlined in the text, derive Eqs. 2.76e and 2.76f.

2.53. The tension member in Figure P2.53 has the following dimensions: L = 5 m, b = 100 mm, and h = 200 111111. The (x, y , z) coordinate axes are parallel to the edges of the member, with origin 0 located at the centroid of the left end. Under the deformation produced by load P, the origin 0 remains located at the centroid of the left end and the coordinate axes remain parallel to the edges of the deformed member. Under the action of load P, the bar elongates 20 mm. Assume that the volume of the bar remains constant with E, = eYy. a. Determine the displacements for the member and the state of strain at point Q, assuming that the smd-displacement theory holds.

FIGURE P2.53

b. Determine E,, at point Q based on the assumption that disPlacements are not

2-54. mmY Practical Problems, the State of strain is approximated by the condition that the normal and shear strains for some direction,say, the z direction,are zero; that is, E,, = eZx= E , ~= 0 (plane strain). Assume that E, ~ y v ,and exyfor the (x, y ) coordinate axes shown in Figure P2.54 are known. Let the (X,Y) coordinate axes be defined by a counterclockwise rotation through angle

X

FIGURE P2.54

76

CHAPTER 2 THEORIES OF STRESS AND STRAIN

6 as indicated in Figure P2.54. Analogous to the transformation for plane stress, show that the transformation equations of plane strain are

2.58. A rectangular airplane wing spar (Figure P2.58) is loaded so that a state of plane strain (eZz= eZx= ezY= 0) exists. a. Determine the displacements for the spar for the deforma-

e x x = e , ~ ~ s 2 e + ~ ~ i n 2 e + ~ ~ , ~ i n e ~tions ~ ~shown ~ and the strain components at point B. b. Let the X axis extend from point 0 through point B. DetereW = sin2e+ eYYcos2e- 2~, sin ecos e exx at point B. e x y = - ~ , ~ i n e c o ~ e + ~ ~ ~ei + nE e c, ,o( c~ o s ~ ~ - s ~ ~ ~ Bmine ) (See Eq. 2.30.) Y

2.55. A square panel in the side of a ship (Figure P2.55) is loaded so that the panel is in a state of plane strain (ezz= ezx= ezy= 0).

A

a. Determine the displacements for the panel given the deformations shown and the strain components for the (?c, y) coordi-

lines

nate axes. b. Determine the strain components for the (X, Y) axes.

yv 1 mm

0

FIGURE P2.58

Straight lines

O 0"

2.59. The nonzero strain components at a point in a machine member are eXx = 0.00180, eyy= -0.00108, and yxy = 2eXy= -0.00220. Using the transformation equations for plane strain (see Problem 2.54), determine the principal strain directions and principal strains.

C

FIGURE P2.55

2.60. Solve for the principal strains in Problem 2.59 by using 2.56. A square glass block in the side of a skyscraper (Figure Eqs. 2.77b and 2.78. P2.56) is loaded so that the block is in a state of plane strain 2.61. Determine the principal strains at point E for the (ezz= e2.,= EZY = 0). deformed parallelepiped in Example 2.8. a. Determine the displacements for the block for the deformations 2.62. When solid circular torsion members are used to obtain shown and the strain components for the (x, y) coordinate axes. b. Determine the strain components for the ( X , Y) axes.

2mm--

material properties for finite strain applications, an expression for the engineering shear strain xx is needed, where the (x, z ) plane is a tangent plane and the z axis is parallel to the axis of the member as indicated in Figure P2.62. Consider an element ABCD in Figure P2.62 for the undeformed member. Assume that the member deforms such that the volume remains constant and the diameter remains unchanged. (This is an approximation of the real behavior of many metals.) Thus, for the deformed element A*B*C*D*, A*B* = AB, C*D* = CD, and the distance along the z axis of the member between the parallel curved

+'

FIGURE P2.56

2.57. Determine the orientation of the ( X , Y) coordinate axes for principal directions in Problem 2.56. What are the principal strains?

FIGURE P2.62

PROBLEMS

lines A*B* and C*D* remains unchanged. Show that Eq. 2.71 gives the result ya = tan a, where a is the angle between AC and A*C*, where yu = 26, is defined to be the engineering shear strain.

2.63. A state of plane strain exists at a point in a beam, with the nonzero strain components en = -2000 p, en = 400 p, and Exy = -900 a. Determine the principal strains in the (x,y ) plane and the orientation of the rectangular element on which they act. (See Example 2.10.) b. Determine the maximum shear strain in the (x, y ) plane and the orientation of the rectangular element on which it acts. c. Show schematically the deformed shape of a rectangular element in the reference orientation, along with the original undeformed element. (See Example 2.10.)

2.64. A square plate, 1 m long on a side, is loaded in a state of plane strain and is deformed as shown in Figure P2.64.

77

2.66. Show that the strain components of Example 2.11 are compatible. 2.67. For a problem of small-displacement plane strain, the strain components in a machine part, relative to axes (x, y, z), are

Determine the (x, y ) displacement components (u. v), for the case where the displacement components (u, v) vanish at x = y = 0 and the slopes (&I&, &I&) are equal at x = y = 0. That is, ul x=y, o = VI x = y = o

\$1

=o

x=y=o

-21

(b) (c)

x=y=o

2.68. Show that Eqs. 2.84 reduce to Eqs. 2.85 for cylindrical coordinates. 2.69. Show that Eqs. 2.84 reduce to Eqs. 2.86 for spherical coordinates.

12.5

2.70. Show that Eqs. 2.84 reduce to Eqs. 2.87 for plane polar coordinates. 2.71. Assume that the machine part shown in Figure E2.8 undergoes the (x, y, z ) displacements u =

25 rnrn

FIGURE P2.64 a. Write expressions for the u and v displacements for any point

on the plate.

b. Determine the components of Green strain (Eq. 2.62) in the plate. c. Determine the total Green strain (Eq. 2.61) at point B for a line element in the direction of line OB. d. For point B, compare the components of strain from part b to the components of strain for small-displacementtheory (Eq. 2.81). e. Compare the strain determined in part c to the corresponding strain using small-displacement theory.

2.65. Determine whether the following statements are true orfalse. a. Strain theory depends on the material being considered. b. Stress theory depends on strain theory. c. The mathematical theories of stress and strain are equivalent. d. The correct strains of a strained material must be compatible.

C1XZ,

v=c2yz,

w = c3z

where the meter is the unit of length for (u, v, w) and (x, y, z). Use small-displacement theory to: a. Determine the components of strain at point E, in terms of cl,

c2, and c3. b. Determine the normal strain at E in the direction of the line EC, in terms of cl, c2, and c3. c. Determine the shear strain at E for the lines EF and ED, in terms of cl, c2, and c3. d. Obtain numerical values for parts a, b, and c, for c1 = 0.002 m-', c2 = 0.004 m-', and c3 = -0.004 m-'.

2.72. The small-displacement strain components in a cam lobe are

where A , B, C, D, E, and F are small constants. Determine whether or not these strain components can be compatible.

Section 2.9 The problems for Section 2.9 involve the determination of principal strains and maximum shear strain from measurements by strain rosettes.

2.73. Show that for Example 2.12, when 6 = 45", the principal strains are given by

78

CHAPTER 2 THEORIES OF STRESSAND STRAIN

= ~(E,+E,)+R

and the maximum strain el is located at angle 9, counterclockwise from the x axis, where tan243 =

2Eb - E , 'a

c. Construct the corresponding Mohr's circle for the rectangular rosette.

2.76. For the delta strain rosette (Figure 2.2Oa), let arm a be

-E,

directed along the positive x axis of axes (x, y).

- 'C

a. Show that the maximum principal strain is located at angle 6, counterclockwise to the x axis, where

2.74. Show that for Example 2.12, when 6 = 60", the principal strains are given by

tan 26 =

= -1( E , 3

h( E b -

Ec)

2Ea - Eb - E,

+ + E,) + R b. Show that the two principal surface strains el and e2 are given by

= -1( E , + E ~ + E , ) - R

3

E,

EL

and the maximum strain is located at angle wise from the x axis, where tan 29 =

9, counterclock-

+ E b -k E , 3

Ea

+R, € 2 ~

+ Eb + E 3

2Ea - Eb - E,

,-R

where

R = i [ ( 2 e a - E b - E , ) 2 + 3(eb-E,f]

ID

h ( € b

c. Construct the corresponding Mohr's circle for the delta

2.75. For the rectangular strain rosette (Figure 2.20b), let arm a be directed along the positive x axis of axes (x, y).

a. Show that the maximum principal strain is located at angle 0, counterclockwise to the x axis, where tan 26 =

=

2Eb-Ea E

-E,

-E,

b. Show that the two principal surface strains

and e2 are

rosette.

2.77. Let the arm a of a delta rosette (Figure 2.204 be directed along the positive x axis of axes (x, y). From measurements, = 2450 p, eb = 1360 p,and Ec = -1310 p. Determine the two principal surface strains, the direction of the principal axes, and the associated maximum shear strain E ~ .

2.78. Let the arm a of a rectangular rosette (Figure 2.20b) be directed along the positive x axis of axes (x, y). Using Mohr's circle of strain, show that 2eq = y, = 26, - E, - Ec.

given by

REFERENCES BORESI,A. P., and CHONG,K . P. (2000). Elasticity in Engineering Mechanics, 2nd ed. New York: Wiley-Interscience. KOBAYASHI, A. S . (Ed.) (1987). Handbook on Experimental Mechanics. Englewood Cliffs, NJ: Prentice Hall.

MURNAHAN, F. D. (1951). Finire Deformation of an Elastic Solid. New York Wiley.

CHAPTER

3

LINEAR STRESS-STRAINTEMPERATURE RELATIONS

I I n Chapter 2, we presented separate theories for stress and strain. These theories are based on the concept of a general continuum. Consequently, they are applicable to all continua. In particular, the theory of stress is based solely on the concept of force and the associated concept of force per unit area. Similarly, the theory of strain is based on geometrical concepts of infinitesimal line extensions and rotations between two infinitesimal lines. However, to relate the stress at a point in a material to the corresponding strain at that point, knowledge of material properties is required. These properties enter into the stress-strain-temperature relations as material coefficients. The theoretical basis for these relations is the first law of thermodynamics, but the material properties themselves must be determined experimentally. In this chapter, we employ the first law of thermodynamics to derive linear stressstrain-temperature relations. In addition, certain concepts, such as complementary strain energy, that have application to nonlinear problems are introduced. These relations and concepts are utilized in many applications presented in subsequent chapters of this book.

3.1 FIRST LAW OF THERMODYNAMICS, INTERNAL-ENERGY DENSITY, AND COMPLEMENTARY INTERNAL-ENERGY DENSITY The derivation of load-stress and load-deflection relations requires stress-strain relations that relate the components of the strain tensor to components of the stress tensor. The form of the stress-strain relations depends on material behavior. In this book, we treat mainly materials that are isotropic; that is, at any point they have the same properties in all directions. Stress-strain relations for linearly elastic isotropic materials are well known and are presented in Section 3.4. Stress-strain relations may be derived with the first law of thermodynamics, a precise statement of the law of conservation of energy. The total amount of internal energy in a system is generally indeterminate. Hence, only changes of internal energy are measurable. If electromagnetic effects are disregarded, this law is described as follows: The work performed on a mechanical system by externalforces plus the heat that flaws into the system from the outside equals the increase in internal energy plus the increase in kinetic energy.

79

80

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE

RELATIONS

Symbolically, the first law of thermodynamics is expressed by the equation

6W+6H=6U+6K

(3.1)

where 6W is the work performed on the system by external forces, 6H is the heat that flows into the system, 6U is the increase in internal energy, and 6K is the increase in kinetic energy. To apply the first law of thermodynamics, we consider a loaded member in equilibrium. The deflections are assumed to be known. They are specified by known displacement components (u, v, w) for each point in the deflected member. We allow each point to undergo infinitesimal increments (variations) in the displacement components (u, v, w) indicated by (6,&, 6w). The stress components at every point of the member are considered to be unchanged under variations of the displacements. These displacement variations are arbitrary, except that two or more particles cannot occupy the same point in space, nor can a single particle occupy more than one position (the member does not tear). In addition, displacements of certain points in the member may be specified (e.g., at a fixed support); such specified displacements are referred to as forced boundary conditions (Langhaar, 1989). By Eq. 2.81, the variations of the strain components resulting from variations (6, &, 6w)are

66 = -1 - a(&) xy 2 dx

6€ =-,d6U xx dX SE

d6V = -, - d6W

SEZZ

6€

&

yy

-

yz

,

[ -I dy a(6 w ) a(6v) = -1 2 [ dy -1 1 a( 6 w ) a(6u) =- -1 2 [ ax +

d(6u)

+

a2

(3.2)

+

dZ

To introduce force quantities, consider an arbitrary volume V of the deformed member enclosed by a closed surface S. We assume that the member is in static equilibrium following the displacement variations (6u, &, 6w). Therefore, the part of the member considered in volume V is in equilibrium under the action of surface forces (represented by stress distributions on surface S) and body forces (represented by distributions of body forces per unit volume B,, By, and B, in volume V). For adiabatic conditions (no net heat flow into V 6H = 0) and static equilibrium(6K= 0), the first law of thermodynamics states that, during the displacement variations (6, &, &), the variation in work of the external forces 6W is equal to the variation of internal energy 6U for each volume element. Hence, for r!we have

6 W = 6U

(3.la)

It is convenient to divide 6W into two parts: the work of the surface forces 6Ws and the work of the body forces 6 W p At point P of surface S, consider an increment of area dS. The stress vector upacting on dS has components opx, opy,and opzdefined by Eqs. 2.10. The surface force is equal to the product of these stress components and dS. The work is equal to the sum of the work of these forces over the surface S. Thus,

3.1

FIRST LAW OF THERMODYNAMICS, INTERNAL-ENERGY DENSITY, AND COMPLEMENTARY INTERNAL-ENERGY DENSITY

81

For a volume element dV in volume V, the body forces are given by products of dV and the body force components per unit volume (Bx,By,Bz).The work mnJ, of the body forces that act throughout V is

The variation of work c%V of the external forces that act on volume V with surface S is equal to the sum of and SWB. The surface integral in Eq. 3.3 may be converted into a volume integral by use of the divergence theorem (Boresi and Chong, 2000). Thus,

m

=

ms+ 6wB =

j [ - (dG x x 6 U

V

dX

+ -(a d

dr

+ axy6v+ ox,6w)

6u + oyy6v+ OYZ6W) yx

+ -(ozx6u d + OZY6V+ 0 , , 6 W )

(3.5)

dZ

I

+ Bx6u +By& + B,6w]dv With Eqs. 3.2 and 2.45, Eq. 3.5 reduces to

The internal energy U for volume V is expressed in terms of the internal energy per unit volume, that is, in terms of the internal-energy density UO.Thus,

u=juodv V

and the variation of internal energy becomes

6U = j 6 U o dV

(3.7)

V

Substitution of Eqs. 3.6 and 3.7 into Eq. 3.la gives the variation of the internal-energy density 6Uo in terms of the stress components and the variation in strain components. Thus,

6U0 = 0 ,

+ oyy6EYY + ozz + 2Oq 6Eq + 2OX26Exz + 2oy26Eyz

(3.8)

This equation is used later in the derivation of expressions that relate the stress components to the strain-energy density UO(see Eqs. 3.11).

3.1.1

Elasticity and Internal-Energy Density

The strain-energy density Uo is a function of certain variables; we need to determine these variables. For elastic material behavior, the total internal energy U in a loaded member is equal to the potential energy of the internal forces (called the elastic strain energy). Each

82

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE RELATIONS

stress component is related to the strain components; therefore, the internal-energy density UOat a given point in the member can be expressed in terms of the six components of the strain tensor. If the material is nonhomogeneous (has different properties at different points in the member), the function UOdepends on location (x, y, z) in the member as well. The strain-energy density UOalso depends on the temperature T (see Section 3.4). Since the strain-energy density function UOgenerally depends on the strain components, the coordinates, and the temperature, we may express it as function of these variables. Thus,

uo = uo (en, eYy,ezZ,eq9 exZ, cYztX, Y,Z, T )

(3.9)

Then, if the displacements (u, v, w)undergo a variation (au, &, &), the strain components take variations 6en, 6eYy,a ~ ~ ~ and , and the function U , takes on the variation

a ~a ~~ , ~a ~~ , ~ ~ ,

6Uo =

duo 6exn+ duo JEXX

dfy

+ yy

duo

+ duo

dEzz

dExy

+

duo dfz

dU +2 SeYz

(3.10)

d'yz

Therefore, since Eqs. 3.8 and 3.10 are valid for arbitrary variations (au, &, &), comparison yields for rectangular coordinate axes (x, y, z)

(3.11)

duo , oxy- -1 JExy

1 duo , oxz= --

0

= -1-duo

yz

JEXZ

2dEy,,

3.1.2 Elasticity and Complementary Internal-Energy Density In many members of engineering structures, there may be one dominant component of the stress tensor; call it o.This situation may arise in axially loaded members, simple columns, beams, or torsional members. Then the strain-energy density Uo (Eq. 3.9) depends mainly on the associated strain component E; consequently, for a given temperature T, o depends mainly on E. By Eq. 3.1 1, o = dUo/dE and, therefore, U, = o d e . It follows that UOis represented by the area under the stress-strain diagram (Figure 3.1). The rectangular area (0, 0), (0, E ) , (0, E), ( 4 0 ) is represented by the product CTE. Hence, this area is given by

oE=Uo+Co

0)

pI

Y

I I

-0

A

I

-I

i (0,E ) FIGURE 3.1 Strain-energy densities.

(3.12)

3.1

FIRST LAW OF THERMODYNAMICS, INTERNAL-ENERGY DENSITY, AND COMPLEMENTARY INTERNAL-ENERGY DENSITY

83

where Co is called the complementary internal-energy density or complementary strainenergy density. COis represented by the area above the stress-strain curve and below the horizontal line from (0, 0) to (0, E ) . Hence, by Figure 3.1, Co = I E d o

(3.13)

€ = dC0

(3.14)

or do

This graphical interpretation of the complementary strain energy is applicable only for the case of a single nonzero component of stress. However, it can be generalized for several nonzero components of stress as follows. We assume that Eqs. 3.11 may be integrated to obtain the strain components as functions of the stress components. Thus, we obtain

(3.15)

wherefl,f2, ..., f 6 denote functions of the stress components. Substitution of Eqs. 3.15 into Eqs. 3.9 yields UOas a function of the six stress components. Then direct extension of Eq. 3.12 yields

co = - u, + O,E, + oyyEYy + o z z E z z + 2oxr€xr+ 2oxzExZ+ 2oyz€yz

(3.16)

By Eqs. 3.15 and 3.16, the complementary energy density Co may be expressed in terms of the six stress components. Hence, differentiating Eq. 3.16 with respect to o , , noting by the chain rule of differentiation that

(3.17)

and employing Eq. 3.1 1, we find (3.18) Similarly, taking derivatives of Eq. 3.16 with respect to the other stress components (o,,, ozz,oq,ox,, o,,),we obtain the generalization of Eq. 3.14:

- dC0

Ex,--,

do,,

E

yy

= -JCO , do,,

Ezz

- JCO

-do,,

(3.19)

84

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE

RELATIONS

Because of their relationship to Eqs. 3.1 1, Eqs. 3.19 are said to be conjugate to Eqs. 3.11. Equations 3.19 are known also as the Legendre transform of Eqs. 3.11 (Boresi and Chong, 2000).

3.2

HOOKE’S LAW ANISOTROPIC ELASTICITY In the one-dimensional case, for a linear elastic material the stress CJ is proportional to the strain E; that is, CJ=EE,where the proportionality factor E is called the modulus of elasticity. The modulus of elasticity is a property of the material. Thus, for the one-dimensional case, only one material property is required to relate stress and strain for linear elastic behavior. The relation CJ=EEis known as Hooke’s law.More generally, in the three-dimensional case, Hooke’s law asserts that each of the stress components is a linear function of the components of the strain tensor; that is (with yq, yxz,yyz;see Eq. 2.73),

(3.20)

where the 36 coefficients, C l l , ..., c66, are called elastic coefficients. Materials that exhibit such stress-strain relations involving a number of independent elastic coefficients are said to be anisotropic. (See also Section 3.5.) In reality, Eq. 3.20 is not a law but merely an assumption that is reasonably accurate for many materials subjected to small strains. For a given temperature, time, and location in the body, the coefficients Cii are constants that are characteristics of the material. Equations 3.1 1 and 3.20 yield

(3.21)

Hence, the appropriate differentiations of Eqs. 3.21 yield

d2U0 JExx

dfy

=

c,, = c2, (3.22)

HOOKE'S LAW ISOTROPIC ELASTICITY

3.3

85

These equations show that the elastic coefficients CQ = Cjj are symmetrical in the subscripts i,j. Therefore, there are only 21 distinct C's. In other words, the general anisotropic linear elastic material has 21 elastic coefficients. In view of the preceding relation, the strain-energy density of a general anisotropic material is (by integration of Eqs. 3.21; see Boresi and Chong, 2000)

1

1

2c13ExxE~z

2c23EyyEzz

1 "'

2 -C36EzzYyz

(3.23)

3.3 HOOKE'S LAW ISOTROPIC ELASTICITY

3.3.1

Isotropic and Homogeneous Materials

If the constituents of the material of a solid member are distributed sufficiently randomly, any part of the member will display essentially the same material properties in all directions. If a solid member is composed of such randomly oriented constituents, it is said to be isotropic. Accordingly, if a material is isotropic, its physical properties at a point are invariant under a rotation of axes. A material is said to be elastically isotropic if its characteristic elastic coefficients are invariant under any rotation of coordinates. If the material properties are identical for every point in a member, the member is said to be homogeneous. In other words, homogeneity implies that the physical properties of a member are invariant under a translation. Alternatively, a member whose material properties change from point to point is said to be nonhomogeneous. If an elastic member is composed of isotropic materials, the strain-energy density depends only on the principal strains, since for isotropic materials the elastic coefficients are invariant under arbitrary rotations (see Eq. 3.25).

3.3.2 Strain-Energy Density of Isotropic Elastic Materials The strain-energy density of an elastic isotropic material depends only on the principal strains (el, e2, e3).Accordingly, if the elasticity is linear, Eq. 3.23 yields

By symmetry, the naming of the principal axes is arbitrary. Hence, Cll = C22 = C33 = C1, and C12 = C23 = C13 = C2. Consequently, Eq. 3.24 contains only two distinct coefficients. For linear elastic isotropic materials, the strain-energy density may be expressed in the form

86

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE

RELATIONS

+ e2 +

U -

O-2

E,Y

+ G (e: + e2 + E

(3.25)

where A = C2 and G = (C, - C2)/2 are elastic coefficients called LamC’s elastic coefficients. If the material is homogeneous and temperature is constant everywhere, A and G are constants at all points. In terms of the strain invariants (see Eq. 2.78), Eq. 3.25 may be written in the following form:

U o = (iA+G)T;-2Gf2

(3.26)

Returning to orthogonal curvilinear coordinates (x,y, z) and introducing the general definitions of and 7, from Eq. 2.78, we obtain

’)

O-2

(3.27)

where ( E ~ eYy, , eZz,eXy,E,,, eYz)are strain components relative to orthogonal coordinates (x,y , z); see Eqs. 2.84. Equations 3.1 1 and 3.27 now yield Hooke’s law for a linear elastic isotropic material in the form (for orthogonal curvilinear coordinates x,y, z) oxx= Ae + ~GE,,, dxY= ~GE,,,

oyy= Ae + ~GE,,,

ozz= Ae + ~ G E , ,

0,. = ~GE,,,

= 2Gey,

(3.28)

where e = E= + eYy+ E,, = 7, is the classical small-displacement volumetric strain (also called cubical strain; see Boresi and Chong, 2000). Thus, we have shown that for isotropic linear elastic materials, the stress-strain relations involve only two elastic constants. An analytic proof of the fact that no further reduction is possible on a theoretical basis can be constructed (Jeffreys, 1957). By means of Eqs. 3.28, we find (with Eqs. 2.21 and 2.78) I, = ( 3 ~ . + 2 ~ ) i ~

I, =

4x1+ 4 ~ ) i :+ 4

~ ~ i ,

(3.29)

2- -

I , = A2(d+2 G ) f i + 4AG I ,I 2 + 8G3i3 which relate the stress invariants 11,I,, I3to the strain invariants TI, 72,73. Inverting Eqs. 3.28, we obtain ex, = E

YY

EZZ

1 E( ox, - voyy- vozz)

1 E

= -(d

YY

- voxx-

vozz)

1

=E -(ozz-voxx-V dYY )

(3.30)

3.3

HOOKE’S LAW ISOTROPIC ELASTICITY

87

where G(3A + 2G), A+G

E =

v=

a

2(a+G)

(3.31a)

are elastic coefficients called Young’s modulus and Poisson’s ratio, respectively. Also, inverting Eqs. 3.31a, we obtain the Lam6 coefficients A and G in terms of E and v as (see also Example 3.2) - 3 VK G = - E VE (3.31b) A= 1 + v’ ( 1 + v)( 1 - 2v) 2 ( 1 + v)

--

where

K =

E 3(1-2~)

(3.31~)

is the bulk modulus. The bulk modulus relates the mean stress om = 11/3 to the volumetric strain e by om = Ke. Alternatively, Eqs. 3.28 may be written in terms of E and v as follows:

(3.32)

For the case of plane stress, o,,= ox, = oyz= 0, Eqs. 3.32 reduce to

(3.32a)

-

OXY-

E l+VXY

-€

For the case of plane strain, E , ~= ex, = eY’ = 0, Eqs. 3.32 reduce to OXX

= (1 + v ) ( l- 2 v ) [( 1 - V b X X + VEyy1 E - (1 + v ) ( l- 2 v ) [VEXX+ (1 - V)EyyI

-

oxy-

-€

1

E

+v

Xy’

ox, = oyz= 0

(3.32 b)

88

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE

RELATIONS

Substitution of Eqs. 3.30 into Eq. 3.21 yields the strain-energy density U, in terms of stress quantities. Thus, we obtain

u,

1

2

2

2

= -2E [Oxx+d + d z z - 2 V ( 0xx dYY + d x x d z z + d d ) YY YY zz 2

2

2

(3.33)

+ 2 ( 1 + V ) ( d X Y + cxxz + oyz)l 1

= -[Z, 2E

2

-2( 1 + V)Z2]

If the (x, y, z ) axes are directed along the principal axes of strain, then eq = E,, = cYz= 0. Hence, by Eq. 3.32, oq = ox- = oyz= 0. Therefore, the (x, y, z ) axes must also lie along the principal axes of stress. Consequently, for an isotropic material, the principal axes of stress are coincident with the principal axes of strain. When we deal with isotropic materials, no distinction need be made between principal axes of stress and principal axes of strain. Such axes are called simply principal axes.

EXAMPLE 3.1 Flat Plate Bent Around a Circular Cylinder

A flat rectangular plate lies in the (x, y) plane (Figure E3. la).The plate, of uniform thickness h = 2.00 mm, is bent around a circular cylinder (Figure E3. lb) with the y axis parallel to the axis of the cylinder. The plate is made of an isotropic aluminum alloy (E = 72.0 GPa and v = 0.33). The radius of the cylinder is 600 mm.

(a) Assuming that plane sections for the undeformed plate remain plane after deformation, determine the plate ~ ~ for) linearly elastic behavior. the maximum circumferential stress a e ~in ~ (b) The reciprocal of the radius of curvature R for a beam subject to pure bending is the curvature K = 1/R = M/EZ. For the plate, derive a formula for the curvature K = 1/R in terms of the applied moment M per unit width.

YI

a 600 m m

R= 601 m m

(4

(a)

FIGURE E3.1

Solution

(a) We assume that the middle surface of the plate remains unstressed and that the stress through the thickness is negligible. Hence, the flexure formula is valid for the bending of the plate. Therefore, oee=0, = 0 for the middle surface and 0, = 0 throughout the plate thickness h. Equations 3.30 = = 0 in the middle surface of the plate. Since the length of the plate in yield the results err= they direction is large compared to the thickness h, the plate deforms approximately under conditions of plane strain; that is, eYy= 0 throughout the plate thickness. Equations 3.30 give 1 V E y y = 0 = -0 --Gee E YY E throughout the plate thickness. Thus, for plane strain relative to the (r, 0) plane OYy

= vOee

3.3

HOOKE‘S LAWISOTROPIC ELASTICITY

89

With Eqs. 3.30, Eq. (a) yields

The relation between the radius of curvature R of the deformed plate and ~ e may e be determined by the geometry of deformation of a plate segment (Figure E3.k). By similar triangles, we find from Figure E 3 . k that

or Eee(max)

--

h

Equations (b) and (c) yield the result

(b) In plate problems, it is convenient to consider a unit width of the plate (in they direction) and let M be the moment per unit width. The moment of inertia for this unit width is I = bh3/12 = h3/12. Since oee(max) = M(h/2)/1,this relation may be used with Eq. (d) to give

where Eh3

D =

2

12(1-v ) is called theflexure rigidity of the plate. (See Chapter 13.)

EXAMPLE 3.2 The Simple Tension Test

In Section 1.3, the axial tension test and its role in the determination of material properties were discussed. The axial tension test in the linear elastic range of stress-strain may be used to interpret the Lam6 coefficients A and G . For example, consider a prismatic bar subjected to the following state of stress relative to the (x,y, z ) axes, with the z axis directed along the longitudinal axis of the bar:

For this state of stress to exist, the stresses on the lateral surface of the bar must be zero. On the ends of the bar, the normal stress is cr and the shear stress is zero. In other words, the state of stress in the bar is one of simple tension. Equations 3.28 yield k + ~ G E =, k + 2Geyy= = eXz= ey,= 0. Solving these equations for the strain components, we obtain

=

a0 - [2G(32+2G)J’

(a + G I G Ezz

= [G(32+2G)J

It follows from Eqs. (b) that

where the quantities E =

G ( 3 A+ 2 G ) (A+G) ’

a = [2(A+G)1

90

CHAPTER 3 LINEAR STRESSSTRAINTEMPERATURE RELATIONS

are Young’s modulus of elasticity and Poisson‘s ratio, respectively. In terms of E and v, Eq. (b) becomes Exx

=

Eyy

- VO - -E’

Ezz

=

O

a

Solving Eqs. (d) for the Lam6 coefficients and G, in terms of E and v, we obtain

a=

VE [ ( l + v)(l-2v)]’

G =

E + v)l

The Lam6 coefficient G is also called the shear modulus of elasticity. It may be given a direct physical interpretation (see Example 3.3). The Lam6 coefficient A has no direct physical interpretation. However, if the first of Eqs. 3.32 is written in the form Ox,

E(1-V) VE = ( 1 + v)( 1 - 2 v p x + ( 1 + v) ( 1 - 2 v) ( f y y

+

Ez,)

the coefficient E(l - v)/[(l + v)(l - 2v)] can be called the axial modulus, since it relates the axial , . strain component en to its associated axial stress 0 Similarly, the Lam6 coefficient 1 = vE/[(l + v)(l - 2v)l may be called the transverse modulus, since it relates the strain components eYyand E,, (which act transversely to o,) to the axial stress 0 , . The second and third equations of Eqs. 3.32 may be written in a form similar to Eq. (g), with the same interpretation.

EXAMPLE 3.3 The Pure Shear Test and the Shear Modulus

= o,,= o-\y = ox,= 0 and (TY Z = The pure shear test may be characterized by the stress state O, = oYy z= constant. For this state of stress, Eqs. 3.28 yield the strain components

where yis used to represent engineering shear strain because of its convenient geometric interpretation (see Eq. 2.73). These formulas show that a rectangular parallelepiped ABCD (Figure E3.3) whose faces are parallel to the coordinate planes is sheared in the yz plane so that the right angle between the edges of the parallelepiped parallel to the y and z axes decreases by the amount yyz. For this reason, the coefficient G is called the shear modulus of elasticity. A pure shear state of stress can be obtained quite accurately by the torsion of a hollow circular cylinder with thin walls (see Chapter 6).

FIGURE E3.3

3.4

EXAMPLE 3.4 Elimination of Friction Effect in the Uniaxial Compression Test

EQUATIONS OF THERMOELASTICITY FOR ISOTROPIC MATERIALS

91

In a uniaxial compression test, the effect of friction between the test specimen and the testing machine platens restrains the ends of the specimen from expanding freely in the lateral directions. This restraint may lead to erroneous measurement of the specimen strain. One way to eliminate this effect is to design the specimen and machine platens so that 1. the specimen and the end of the platens in contact with the specimen have the same cross sections and 2. a certain relation exists between the material properties of the specimen and the platens. To illustrate this point, let quantities associated with the specimen be denoted by subscript s and those associated with the platens be denoted by subscript p. Let P be the load applied to the specimen through the end platens. Because the cross-sectional shapes of the specimen and the platens are the same, we denote the areas by A . Let coordinate z be taken along the longitudinal axis of the specimen and coordinate x be perpendicular to axis z. Then, under a machine load P, the longitudinal strains in the specimen and platens are, respectively,

The associated lateral strains are (EXX)\$

= -v s ( E 2 2 )s =

V P

-s EsA, ( E

XX

) P

=-v

p

(E

)

zz P

V P

= -E J L pA

If the lateral strains in the specimen and platens are equal, they will expand laterally the same amount, thus eliminating friction that might be induced by the tendency of the specimen to move lat= erally relative to the platens. By Eq. (b), the requirement for friction to be nonexistent is that (E,)p, or

In addition to identical cross sections of specimen and platens, the moduli of elasticity and Poisson's ratios must satisfy Eq. (c). To reduce or eliminate the effect of friction on the tests results, it is essential to select the material properties of the platens to satisfy Eq. (c) as closely as possible.

3.4 EQUATIONS OF THERMOELASTICITY FOR ISOTROPIC MATERIALS Consider an unconstrained member made of an isotropic elastic material in an arbitrary zero configuration. Let the uniform temperature of the member be increased by a small amount AT. Experimental observation has shown that, for a homogeneous and isotropic material, all infinitesimal line elements in the volume undergo equal expansions. Furthermore, all line elements maintain their initial directions. Therefore, the strain components resulting from the temperature change AT are, with respect to rectangular Cartesian coordinates (x, y, z),

where a denotes the coefficient of thermal expansion of the material. ,, oyy,..., oyzat Now let the member be subjected to forces that induce stresses o point 0 in the member. Accordingly, if E ~ eYy, , ..., eYzdenote the strain components at point 0 after the application of the forces, the change in strain produced by the forces is represented by the equations E : ~ = eXx- a AT,

eGY = eYy- a AT,

=

E,, - a AT

(3.35)

92

CHAPTER 3 LINEAR STRESS-STRAIN-TEMPERATURE

RELATIONS

In general, AT may depend on the location of point 0 and time t. Hence AT = AT (x, y, z, t). Substitution of Eq. 3.35 into Eqs. 3.28 yields

oxx= ile + ~GE,,- CAT, oYy =

ile + ~ G E , ,- CAT

ozz= ile + 2GeZZ- CAT

oXy= ~GE,,,

(3.36)

ox, = 2Gex,,

oYz = 2Gcy,

where (3.37) Similarly, substitution of Eqs. 3.36 into Eqs. 3.30 yields

(3.38)

Finally, substituting Eqs. 3.38 into Eqs. 3.26 or 3.27, we find that

u,

=

(;

2 3 il+G I -2Gi2-ci1 AT+-ca(AT) 2

)-:

(3.39)

In terms of the strain components (see Eqs. 2.78), we obtain

u,

=

1 -a(Exx + 2

YY

2 2 + Ez,) 2 + G ( E 2, ~ + E2y y + E2z z + 2E2 + 2Exz + 2Eyz) XY

3 2 - C( eXx+ gYy+ eZZ)AT+ - c a ( A T ) 2

(3.40)

Equations 3.36 and 3.38 are the basic stress-strain relations of classical thermoelasticity for isotropic materials. For temperature changes AT, the strain-energy density is modified by a temperature-dependentterm that is proportional to the volumetric strain e = T1= E, + erY+ eZzand by a term proportional to (AT)2(Eqs. 3.39 and 3.40). We find by Eqs. 3.38 and 3.40 (3.41) 2E and 2

2

2

2

2

’1

(3.42)

+ 2(1 + waxy + ox, + oyz> in terms of stress components. Equation 3.42 does not contain AT explicitly. However, the temperature distribution may affect the stresses. Note that Eqs. 3.41 and 3.42 are identical to the results in Eq. 3.33.

HOOKE‘S LAW ORTHOTROPIC MATERIALS

3.5

3.5

93

HOOKE’S L A W ORTHOTROPIC MATERIALS An important class of materials, called orthotropic materials, is discussed in this section. Materials such as wood, laminated plastics, cold rolled steels, reinforced concrete, various composite materials, and even forgings can be treated as orthotropic. Orthotropic materials possess three orthogonal planes of material symmetry and three corresponding orthogonal axes called the orthotropic axes. In some materials, for example, forged materials, these axes may vary from point to point. In other materials, for example, fiber-reinforced plastics and concrete reinforced with steel bars, the orthotropic directions remain constant as long as the fibers and steel reinforcing bars maintain constant directions. In any case, for an elastic orthotropic material, the elastic coefficients Cij(Eq. 3.20) remain unchanged at a point under a rotation of 180”about any of the orthotropic axes. Let the (x, y, z ) axes denote the orthotropic axes for an orthotropic material and let the (x, y) plane be a plane of material symmetry. Then, under the coordinate transformation x +x, y +y, and z + - z , called a reflection with respect to the (x, y) plane, the elastic coefficients Cij remain invariant. The direction cosines for this transformation (see Table 2.2) are defined by

1, = rn2 = 1,

n3 = -1,

1, = 1, = rnl = rn3 = n l = n2 = 0

(3.43)

Substitution of Eqs. 3.43 into Eqs. 2.15, 2.17, and 2.76 reveals that, for a reflection with respect to the (x, y) plane,

on = o ,,

oyy = oyy, 0.z = ozz, o x y = 0-,

oxz = - a,,,

o y z = -oyz

(3.44)

and Exx = E X x E W

Ezz = EZZ’ ”/xu =

= Eyy.

”/xz= - YKZ? rYz = - Yyz

Y-9

(3.45)

Since the Cij are constant under the transformation of Eq. 3.43, the first of Eqs. 3.20 yields

= 1‘

lEXX 4- c12EYY

‘13€ZZ

‘14fiY

+ ‘15%Z

‘16YyZ

(3.46)

Substitution of Eqs. 3.44 and 3.45 into Eq. 3.46 yields %= %X=c11E.xx+c12Eyy +c13Ezz

c14Y~-c15~z-c16’&z

(3.47)

Comparison of the first of Eqs. 3.20 with Eq. 3.47 yields the conditions CIS = -C1s and ‘16 = 4 1 6 , or ‘15 = ‘16 = 0. Similarly, considering o ,ozz, OXF OXZ, and OYZ, we find that ‘25 = ‘26 = C35 = c 3 6 = ‘45 = ‘46 = 0. Thus, the coefficients for a material whose elastic properties are invariant under a reflection with respect to the (x, y) plane (i.e., for a material that possesses a plane of elasticity symmetry) are summarized by the matrix -

‘11

‘12

‘13

‘14

‘12

‘22

‘23

‘24

‘13

‘23

‘33

‘34

‘14

‘24

‘34

‘44

0

0

0

0

0

0

0

0

(3.48)

‘55

‘56

‘56

‘66

-

94

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE RELATIONS

A general orthotropic material has two additional planes of elastic material symmetry, in this case, the (x,z) and (y, z) planes. Consider the (x, z) plane. Let x + x,y + -y, z + z. Then, proceeding as before, noting that 11 = n 3 = 1, m 2 = -1, and 12 = l3 = ml = m3 = n1 = n2 = 0, we find ‘14 = C24 = C34 = ‘56 = 0. Then, the matrix of Eq. 3.48 reduces to ‘I1

‘12

‘I3

‘12

‘22

‘23

‘13

‘23

‘33

0

0

0

0

o c , o 0 o o c , , o

0

0

0

0

(3.49)

0‘6

A reflection with respect to the (y, z) plane does not result in further reduction in the number of elastic coefficients Cij The matrix of coefficients in Eq. 3.49 contains nine elastic coefficients. Consequently, the stress-strain relations for the most general orthotropic material contain nine independent elastic coefficients relative to the orthotropic axes (x,y, z). Equations 3.20 are simplified accordingly. It should be noted, however, that this simplification occurs only when the orthotropic axes are used as the coordinate axes for which the Cij are defined. The resulting equations are O n = ‘ I l E x x + ‘12€yy

‘13€zz

Oyy = c12Exx + ‘22€yy + ‘ 2 3 % ~ *zz = c13En + ‘23€yy + ‘33€zz -iy

(3.50)

= ‘44Yq

*xz = ‘55Yxz

= ‘66’&z The stress-strain relations for orthotropic materials in terms of orthotropic moduli of elasticity and orthotropic Poisson’s ratios may be written in the form *yz

(3.51) Yxy

- 1 - --xy GxY

Yxz

Yyz

1 = --xz

Gxz

- 1

-

--yz

GYZ

3.5

HOOKE'S LAW: ORTHOTROPIC MATERIALS

95

where Ex,Ey,Ez denote the orthotropic moduli of elasticity and Gxy,G,, ,Gyzdenote the orthotropic shear moduli for shear deformation in the x-y, x-z, and y-z planes, respectively. The term vxyis a Poisson ratio that characterizes the strain in the y direction produced by the stress in the x direction, with similar interpretations for the other Poisson ratios, vyx,vzx,vxz,vyz, and vzy..For example, by Eq. 3.5 1, for a tension specimen of orthotropic material subjected to a unimal stress o,,= o,the axial strain is eZz= o/E, and the laterial strains are ex. = -vZxo/Ez and eYr= -vzyo/Ez. (See Example 3.2 for the analogous isotropic tension test.) Because of the symmetry of the coefficients in the stress-strain relations, we have by Eqs. 3.51 the identities

xV y = -vyx , -vxz- -- vzx Ex E, Ex E,' EXAMPLE 3.5 Stress-Strain Relations for Orthotropic Materials: The Plane Stress Case

vyz =

vzy

(3.52)

E,

A wood panel with orthotropic axes (x, y , z ) is subjected to a plane stress state relative to its face in the (x, y ) plane. Let a rectangular region in the body be subjected to extensional stress om (Figure E3.5a). By Eq. 3.51, the strain components are Exx

-

= oxx E X

EYY

=

oxx -

= - "xy

-VxyExx

EX

where vxyand v,, are orthotropic Poisson ratios.

Contraction

Extension

0Deformed shape -1

-] Undeformed shape

Orthotropic material axes

FIGURE E3.5 Orthotropic material. ( a )Applied stress oxx.( b )Applied stress uyr (c) Applied stress oxy.

96

CHAPTER 3 LINEAR STRESS-STRAIN-TEMPERATURE RELATIONS

Consider next the case where the rectangular region is subjected to an extensional stress oyy(Figure E3.5b). By Eqs. 3.51, the strain components are f Y

- OYY - EY

= -v YX EYY - --vYx'YY

Exx

EY VY z o y y

€2,

= -v YZ t2YY = --

EY

where vyxand vyzare orthotropic Poisson ratios. the addition of Eqs. (a) and (b) yields For a combination of stresses (on,oyy), EXX

=

ox, - v y x o y y -

Ex E

YY

E y

=--+Vxy% Ex

oyy E y

vxzoxx

€2,

= - --

E x

vyzoyy

E y

Solving the first two of Eqs. (c) for (om, oyy) in terms of the in-plane strains (en, eYy),we obtain EX (Exx + V y x E y y )

(d) OYY

=

EY

1- v x y v y x

(VxyExx + Eyy)

Finally, consider the element subjected to shear stress oxy(Figure E3.5~).By Eqs. 3.51, we have oxy

=

(el

GxyYxy

where Gxyis the orthotropic shear modulus in the (x, y) plane and y, is the engineering shear strain in the (x, y) plane. Thus, for the orthotropic material in a state of plane stress, we have the stress-strain relations [by Eqs. (d) and (e)l ox, =

EX (Ex, 1- vxyvyx EY

I

I

1

+

OYY

= 1 - vxyvyx(Vxy%

Oxy

=

VyxEy)

+ Eyy)

GxyYxy

(D

. With these stress-strain relations, the theory for plane stress orthotropic problems of wood panels follows in the same manner as for plane stress problems for isotropic materials.

3.5

EXAMPLE 3.6 Stress-Strain Relations of a Fiber-Resin Lamina

HOOKE‘S LAW. ORTHOTROPIC MATERIALS

97

A lamina (a thin plate, sheet, or layer of material) of a section of an airplane wing is composed of unidirectional fibers and a resin matrix that bonds the fibers. Let the volume fraction (the proportion of fiber volume to the total volume of the composite) bef Determine the effective linear stress-strain relations of the lamina.

(b)

(a)

FIGURE E3.6 Lamina: fiber volume fraction = f, resin volume fraction = 1 - f.

Solution

Let the modulus of elasticity and the Poisson ratio of the fibers be denoted EF and VF, respectively, and the modulus of elasticity and the Poisson ratio of the resin be ER and VR. Since the lamina is thin, the effective state of stress in the lamina is approximately one of plane stress in the x-y plane of the . the stress-strain relations for the fibers and the resin are lamina (see Figure E 3 . 6 ~ )Hence,

where (CT,F, Gyy~),(0,~.uyy~), (e,~, e Y y ~and ) , (E,R, e y y ~denote ) stress and strain components in the fiber (F) and resin (R), respectively. ) the same as Since the fibers and resin are bonded, the effective lamina strain ex (Figure E 3 . 6 ~ is that in the fibers and in the resin; that is, in the x direction, ‘XX

= ‘xxF = ‘xxR

(b)

In the y direction, the effective lamina strain eYyis proportional to the amount of fiber per unit length in the y direction and the amount of resin per unit length in they direction. Hence, Eyy =fEyyF

(1 --f)€yyR

(c)

Also, by equilibrium of the lamina in the x direction, the effective lamina stress 0 , is 0 , = f D , F + (1 - f ) G x R

(4

In the y direction, the effective lamina stress oyy is the same as in the fibers and in the resin, that is, Oyy = OyyF = OyyR

(4

Solving Eqs. (a) through (e) for e, and eYyin terms of u, and uyy,we obtain the effective stressstrain relations for the lamina as

98

CHAPTER 3 LINEAR STRESSSTRAIN-TEMPERATURE

RELATIONS

where E = fEF+(l-f)ER

To determine the shear stress-strain relation, we apply a shear stress o , to a rectangular element of the lamina (Figure E3.6b), and we calculate the angle change y, of the rectangle. By Figure E3.6b, the relative displacement b of the top of the element is

b =fyF where % and

(1 - f b R

(h)

are the angle changes attributed to the fibers and the resin, respectively; that is,

and GF and GR are the shear moduli of elasticity of the fiber and resin, respectively. Hence, the change y, in angle of the element (the shear strain) is, with Eqs. (h) and (i),

By Eq.

o), the shear stress-strain relation is 0 , = Gy,

= 2G€,

where

Thus, by Eqs. (f), (g), (k), and (l), we obtain the stress-strain relations of the lamina, in the form of Eqs. 3.50, as

where VE P E 2 , c,, = c,, = 2

P- v

c,,

EXAMPLE 3.7 Composite ThinWall Cylinder Subjected to Pressure and Temperature Increase

=

E

2’ c,, = P- v

P-v G

Consider a composite cylinder of length L formed from an inner cylinder of aluminum with outer radius R and thickness tA and an outer cylinder of steel with inner radius R and thickness ts (Figure E3.7a); tA Y. If 0,is negative (compressive),the maximum value of olthat can be applied without causing yielding is less than Y. The maximum principal strain criterion does not accurately predict yielding of ductile metals but may improve our ability, relative to the maximum principal stress criterion, to predict fracture of brittle materials. Even though the maximum principal strain criterion predicts yielding in terms of strain magnitudes, we still express its yield function in terms of stress. Writing the first of Eqs. 3.30 in terms of principal stresses, we have El

1 = -(01-v02-v03) E

(4.3)

Assuming that is the principal strain with the largest magnitude, we equate jell with eY and obtain the yield function f l = lo1- va, - vo3J- Y = 0

or

o1- vo2- vo3 = f Y

(4.4a)

If we assume that the principal strains are unordered, either E, or e3 may have the largest magnitude. Then we obtain the additional possibilities =

~ o , - v o l - v o 3 ~ - =Y 0 or

O ~ - V ~ ~ - V= C fT Y~

(4.4b)

f3 =

[ O ~ - V C T ~ - V O ~= ~0- Yor

0 3 - v 0 1 - v 0 2= +Y

(4.4c)

f2

Hence, the effective stress 0,may be defined as oe =i #max loj- v 0J. - v0kl j#k

(4.5)

and the yield function as

f = 0,-Y

(4.6)

The yield surface for the maximum principal strain criterion for a biaxial stress state (03= 0) is shown in Figure 4.8. The yield surface ABCD illustrates that under biaxial tension (or biaxial compression), individual principal stresses greater than Y can occur without causing yielding.

4.3.3

Strain-Energy Density Criterion

The strain-energy density criterion, proposed by Beltrami (Mendelson, 1983), states that yielding at a point begins when the strain-energy density at the point equals the strainenergy density at yield in uniaxial tension (or compression). Written in terms of principal stresses, strain-energy density is found from Eq. 3.33 as 2E

(4.7)

4.4

u21

YIELDING OF DUCTILE METALS

117

u2-vu1 = Y

=Y

FIGURE 4.8

Maximum principal strain yield surface for biaxial stress state (a,= 0).

By Eq. 4.7, the strain-energydensity at yield in a uniaxial tension test (0, = Y,

= 0,= 0) is

*

u,,

=

Y” 2E

(4.8)

Thus, the strain-energy density criterion states that yield is initiated when the strainenergy density U,, Eq. 4.7, for any stress state equals U , , Eq. 4.8. We again consider the stress states depicted in Figure 4.6, but we now apply the strain-energy density criterion for yielding Uo = UOy.For uniaxial tension (Figure 4.6a), yielding is predicted to occur when 0,= Y, as it should. For a biaxial stress state in which 0,= 0,= 0 (Figure 4.6b), yielding is predicted to occur when 202(1 - V ) = Y 2 . If we assume that Poisson’s ratio for the material is zero (v = 0), then yielding occurs when o = Y/.& . If the biaxial stress state is 0,= -0,= 0 (Figure 4.6c), a state of pure shear exists and yielding is again predicted to occur when 0= Y/.& ,provided that v = 0. The yield function for the strain-energy density criterion is obtained by setting Uo from Eq. 4.7 equal to Uo, from Eq. 4.8 to obtain

Hence, the yield function has the form 2

f = 0,-Y

2

(4.10)

where the effective stress is 2 2 2 oe = o1+ 0 2 + 0 3 - 2 ~ ( 0 ~ 0+2 0103 + 0203)

(4.1 1)

In general, the yield surface for the strain-energy density criterion is an ellipsoid in principal stress space, the specific shape of which depends on the value of Poisson’s ratio v . When v = 0, the ellipsoid reduces to a sphere with radius equal to the yield stress Y. Figure 4.9 illustrates the yield surface for a biaxial stress state (0, = 0) and three values of Poisson’s ratio.

4.4

YIELDING OF DUCTILE METALS It is well known in metallurgy that certain metal crystals have slip planes along which the resistance to shear force is relatively small. Thus, for such metals, yield criteria are based on limiting values of shear stress. Two such criteria are presented in the following discussion.

118

CHAPTER 4 INELASTIC MATERIAL BEHAVIOR

-a2

FIGURE 4.9

4.4.1

Strain-energy density yield surface for biaxial stress state (03 = 0).

Maximum Shear-Stress (Tresca) Criterion

The maximum shear-stress criterion, also known as the Tresca criterion, states that yielding begins when the maximum shear stress at a point equals the maximum shear stress at yield in uniaxial tension (or compression). For a multiaxial stress state, the maximum shear stress is , ,z = (om,- omin)/2, where om,and omh denote the maximum and minimum ordered principal stress components, respectively. In uniaxial tension (ol= o,0,= o3= 0), the maximum shear stress is zm, = o/2.Since yield in uniaxial tension must begin when o = Y, the shear stress associated with yielding is predicted to be z, = Y/2.Thus, the yield function for the maximum shear-stress criterion may be defined as

Y f = oe-2

(4.12)

where the effective stress is

(4.13) The magnitudes of the extreme values of the shear stresses are (see Eq. 2.44 and Figure 2.13)

(4.14)

is the largest of (z1, z;?, 5).If the principal stresses are unordered, The maximum shear stress yielding under a multiaxial stress state can occur for any one of the followingconditions: o2- o3 = fY 03-01=

fY

o1- o2 = fY

(4.15)

4.4

YIELDING OF DUCTILE METALS

119

By Eq. 4.15, the yield surface for the maximum shear-stress criterion is a regular hexagon in principal stress space (Figure 4.10). For a biaxial stress state (03 = 0), the yield surface takes the form of an elongated hexagon in the (q, 0,) plane (Figure 4.1 1). The Tresca criterion exhibits good agreement with experimental results for certain ductile metals. This can be anticipated by reexamination of the metallurgical basis for yielding. The movement of dislocations along slip planes, which is responsible for permanent defomation, is a shear-related phenomenon. Thus, the Tresca criterion has some physical basis. However, for a state of pure shear, such as occurs in a torsion test, the shear yield stress zy of some ductile metals is found to be approximately 15% higher than the value predicted by the Tresca criterion. Thus, the Tresca criterion is conservativefor these metals. Nevertheless, because it is fairly accurate and computationally simple to use, the maximum shear-stress criterion is a reasonable choice for most ductile metals. Hydrostatic axis (Ul = u2= u3) Maximum shear-stress criterion (Tresca)

Distortional energy density criterion (von Mises)

FIGURE 4.10 Yield surface in principal stress space.

von Mises ellipse (octahedral shear-stress criterion)

ul=-yyJp! u1-0,= Y

ra= - (Eq. 4.12) I

a, = -Y

I

FIGURE 4.1 1 Yield surfaces for biaxial stress state (0, (pure shear).

r -'(Eq. B -

d3

4.26)

= 0). For points A and

6,cr, = -cr2 = cr

120

CHAPTER 4 INELASTIC MATERIAL BEHAVIOR

4.4.2 Distortional Energy Density (von Mises) Criterion The distortional energy density criterion, often attributed to von Mises, states that yielding begins when the distortional strain-energy density at a point equals the distortional strainenergy density at yield in uniaxial tension (or compression). The distortional strain-energy density is that energy associated with a change in the shape of a body. The total strain-energy density U, (Eq.4.7) can be broken into two parts: one part that causes volumetric change Uv and one that causes distortion UD.The appropriate manipulations of Eq. 4.7 give

u,

=

2 ( 0 1 +02+03)

18K

+

2 2 2 (0, - 0 2 ) + ( 0 2- 0 3 ) + ( 0 3 - 0 11

12G

(4.16)

where K is the bulk modulus (K = E/[3(1 - 2v)l) and G is the shear modulus (G = E/[2( 1 + v)]). The first term on the right side of Q.4.16 is Uv, the strain-energy density associated with pure volume change. The second term is the distortional strain-energy density 2

UD =

(01 - 0 2 )

2

+ ( 0 2 - 0 3 ) + ( 0 3 - 01)

2

12G

(4.17)

At yield under a uniaxial stress state (o1= 0,0, = 0,= 0), UD= UDy= Y2/6G.Thus, for a multiaxial stress state, the distortional energy density criterion states that yielding is initiated when the distortional energy density UDgiven by Eq. 4.17 equals Y2/6G. The distortional energy density criterion can be expressed in an alternative form as follows. By Eqs. 4.17 and 2.27, the distortional energy density UDcan be written in terms of the second deviatoric stress invariant J2 as (4.18) where

Relative to the general (x, y, z) axes, J2 can be expressed in terms of the stress invariants I, and Z, (see Eqs. 2.21 and 2.27) as J2 =

I2-5I1 1 2

(4.19b)

At yield in uniaxial tension (or compression), 0,= +Y and 0,= 0,= 0. Then, IJ2I =

1 2

-Y 3

(4.20)

Therefore, by Eqs. 4.19a and 4.20, we may write the yield function for the distortional energy density (von Mises) criterion as (4.21)

YIELDING OF DUCTILE METALS

4.4

121

A more compact form for the yield function is 2

2

f = 0,-Y

(4.22)

where the effective stress is (4.23a) In terms of the rectangular components of stress, the effective stress for the von Mises criterion can be written as Oe

=

2

2

2

~ [ ( O x x - O y y+) ( O y y - O z z ) +(Oz,-Oxx)

2

2

2

2

1 + 3 ( 0 x y + ~ y , + ~ x , )(4.23b)

By comparison of Eq. 2.22 and Eq. 2.27, we observe that J2and the octahedral shear stress are related by

So, we can rewrite the yield function, Eq. 4.21, for the von Mises yield criterion in the alternative form (4.24) Thus, according to Eq. 4.24, when f = 0, the octahedral shear stress at a point reaches the value ( & /3)Y = 0.471 and yielding occurs. This result agrees with that obtained by Eq. 4.21. For this reason, the distortional energy density (von Mises) criterion is also referred to as the octahedral shear-stress criterion. For a three-dimensional stress state, the yield surface for the von Mises criterion forms a cylinder that circumscribes the Tresca hexagon (Figure 4.10). For a biaxial stress state (0, = 0), the von Mises yield surface reduces to an ellipse in the oI-q plane (Figure 4.1 1). As with the Tresca criterion, the von Mises criterion is fairly accurate in predicting initiation of yield for certain ductile metals. The von Mises criterion is more accurate for some materials than the Tresca criterion in predicting yield under pure shear. A state of pure shear exists for a principal stress state 0,= -9 = 0,0,= 0 (Figure 4 . 6 ~ )With . this stress state, Eq. 4.22 predicts that yield occurs under pure shear when 2

30 = Y

2

(4.25)

For this stress state, the maximum shear stress is, , z = I q - 9 1 / 2 = 0.Therefore, at yield cr=, , ,z = zy. Substitution of this value for ointo the von Mises criterion, Eq. 4.25, gives the shear stress at yield as

Y = 0.577Y zY = -

*r3

(4.26)

as compared to zy = Y/2, which is predicted by the Tresca criterion, Eqs. 4.12 and 4.13. Thus, the von Mises criterion predicts that the pure-shear yield stress is approximately 15%greater than that predicted by the Tresca criterion (see also Figure 4.1 1).

122

CHAPTER 4 INELASTIC MATERIAL BEHAVIOR

If the principal stresses are known, the Tresca criterion is easier to apply than the von Mises criterion. However, since the von Mises yield function is continuously differentiable, that is, its yield surface has a unique outward normal at all points (Figures 4.10 and 4.1 l), it is preferred in computational plasticity studies in which plastic flow and strain hardening are considered. Materials that behave according to either the von Mises or Tresca criterion are often called J2 materials, since the effective stress can be written solely in terms of this invariant (Chen and Han, 1988).

4.4.3

Effect of Hydrostatic Stress and the %Plane

Examination of the yield functions for the Tresca and von Mises yield criteria indicates that the hydrostatic stress, om = (q + 0.+ 0,)/3, has no influence on the initiation of yielding. This agrees with experimental evidence that indicates certain ductile metals do not yield under very high hydrostatic ~ t r e s sThis . ~ independence of hydrostatic stress permits us to study yield behavior by examining just cross sections of the Tresca and von Mises yield surfaces. Consider an arbitrary stress state represented by a point B ( q , 9, 03)that lies on line M of the von Mises yield surface (Figure 4.12). The vector OB, which represents this stress state, can be decomposed into two components: OA that lies along the hydrostatic axis [line L with direction cosines: ( l/& , 1/& , l / & )] and AB that lies in a plane normal to line L. Vector OA represents the hydrostatic component of the stress state, and vector AB represents its deviatoric component. Since hydrostatic stress has no influence on yielding, it is sufficient to discuss the yield surface only in terms of the deviatoric component (vector AB). The plane that contains point B and is normal to the hydrostatic axis also contains all other points that represent stress states with the same hydrostatic stress. Such a plane is known as a deviatoric plane. Now consider a second stress state represented by point D that also lies on line M and differs from point B only in its hydrostatic stress component. With respect to yielding, point D is identical to point B; they represent identical deviatoric stress states. Therefore, line M must be parallel to line L, the hydrostatic axis. The fact that line M is parallel to the

Hydrostatic axis (ul = a, = UJ

\

,'- Deviatoric plane

Deviatoric plane

FIGURE 4.12 Deviatoric planes. 3However, hydrostatic tension can contribute to brittle fracture in otherwise ductile metals.

4.4

YIELDING

OF DUCTILE METALS 123

hydrostatic axis implies that all possible stress states may be viewed in terms of only their deviatoric components. Thus, only a single deviatoric plane is needed to study the yield criterion. As our reference plane, we choose the deviatoric plane for which ol = 0,= o3= 0 (hence, om = 0). This reference plane is known as the n-plane (Lubliner, 1990; Section 3.3). Figure 4.13 shows the n-plane as the plane of the paper with the three orthogonal, principal stress axes oblique to the plane. The Tresca and von Mises yield surfaces form a regular hexagon and circle, respectively, on the n-plane. To construct these surfaces, we must determine the lengths of the line segments OB and OA (or OC) (see Figure 4.13). Consider the uniaxial stress state (cq,0,= o3= 0) and unit vectors i, j, and k along axes o,, 02,and 03, respectively. The vector that represents this stress state is oli.This vector may be decomposed into two perpendicular components: one component a, that lies along the hydrostatic axis L, with unit vector n = (i + j + k), and a second component a, that lies in the z-plane. 2 2 2 we find on=(m3ol ) to By geometry, oL=q i * n= ol/&.Since o1 = .oL+ on, be the length of the projection of olion the n-plane. Similar results are obtained for stress states (02,ol= 0,= 0) and (03ol , = 0,= 0). Thus, the components of a general stress state (o,, 02,03) have projections on the z-plane: (m3ol, ) (m302, ) 0,. The stress state (0, = Y, 0,= o3= 0) represents the initiation of yield in a uniaxial tension test for both the Tresca and von Mises criteria. For this case, the length of the projection on the z-plane is Y and the stress state lies at a common point on both yield surfaces, point A in Figure 4.13. By inspection, the intersection of the von Mises cylinder (Figure 4.10) with the n-plane is a circle of radius (m3Y.) Next consider a state of yield under pure shear according to the Tresca criterion (ol= -0,= Y/2,02 = 0).The projections of the componentsof this stress state on the sc-plane are OE for ol and OD for 0,.Line segments OD and OE are each of length (m3o, )= (m3(Y/2) ) = (l/h) Y. We note that OD = OE = OA/2. The sum of the two vector projections gives the projection of the pure shear-stress state OB, where OB = 2(0D) cos 30 = Y / h . The point B lies on the Tresca yield surface. For pure shear, the von Mises criterion

(m)

(m)

j

f u21

von Mises circle

I

Uniaxial stress

I

Uniaxial stress

FIGURE 4.13

4

Yield surfaces in the n-plane.

-(J2/3)y

124

CHAPTER 4 INELASTIC MATERIAL BEHAVIOR

FIGURE 4.14

Geometry of yielding in pure shear.

predicts that yield is initiated at point C, where OC = ( m 3 ) Y. The ratio OCJOB is 1.15. This fact confirms the earlier statement that the von Mises criterion predicts yield at a shear stress that is 15% higher than that predicted by the Tresca criterion. In general, uniaxial stress states exist along the projections of the (q, 02,0,)coordinate axes on the n-plane. Pure shear-stress states exist along the lines labeled S in Figure 4.13, for which one principal stress is zero and the other two principal stresses are equal in magnitude but of opposite sign. The values of the principal stresses that produce yielding in pure shear can be found as follows. A close-up view of a portion of the n-plane from Figure 4.13 is shown in Figure 4.14. The pure shear-stress state (0, = -03,o2= 0) can be transformed back to principal stress coordinates using the law of sines. For the Tresca criterion, yield occurs at point B; lines OD and OE have length Y / & . Hence, the principal stresses are

and the shear yield stress is zy = Y/2. Similarly for the von Mises criterion, yield occurs at point C, lines OF and OG have length ( h , /3)X the principal stresses are

EXAMPLE 4.3 Comparison of Tresca and won ~j~~~

When the loads that act on the hub of a flywheel reach their working values, the nonzero stress compo, = 100 MPa, oyy = -14.0 MPa, and o = nents at the critical point in the hub where yield is initiated ate 0 4 50.0 m a . The load-stress relations are h e a r so that the factor of safety SF (see Eq. 1.16) can be applied to either the loads or stress components. The flywheel material has a yield stress Y = 300 MPa.

(a)Assuming that the material is a Tresca material, determine the factor of safety SF against yield. (b) Assuming that the material is a von Mises material, determine the factor of safety SF against yield.

4.4

YIELDING OF DUCTILE METALS

125

(c) Determine which criterion, Tresca or von Mises, is more conservative.

(d) Illustrate the stress state and factors of safety in the n-plane for the material.

Solution

(a) Tresca (maximum shear-stress) criterion: This criterion is defined by Eq. 4.12, with, , ,z = Y/2 = (a,,,=- omin)/2.To determine a , , and amin. we compute the principal stresses (al, a,, 0,)at the point. With the given data and Eqs. 2.20 and 2.21, the principal stresses are the roots of a3- 8602 39000= 0. The roots are (1 18.8,0, - 32.8). Hence, a, = 118.8 MPa and amin = -32.8 MPa. When the loads are increased by the factor of safety SF, the principal stresses are also increased by the fac, , z = Y/2 = 30012 = SF(o,,, - a,3/2 = SF(118.8 + 32.8)/2. Therefore, SF = tor SE Consequently, 1.98, if the material obeys the Tresca (maximum shear-stress) criterion. (b) Von Mises (octahedral sheur-stress)criterion:By Eq.4.21, including the factor of safety SF, we have

Y =

"[( J2

211'2

118.8)2 + (32.8)2 + (- 32.8 - 118.8)

Hence, SF = 2.17 if the material obeys the von Mises criterion. (c) The same design loads are applied to the flywheel in parts (a) and (b). If the Tresca criterion is applicable, the design loads are increased by a factor of 1.98 to initiate yield. However, if the von Mises criterion is applicable, the design loads are increased by a factor of 2.17 to initiate yield. Thus, the Tresca criterion is more conservative; it predicts yield initiation at smaller loads than the von Mises criterion.

(d) Illustration in the n-plane: To illustrate this solution, we simply project each of the principal stress components onto the n-plane, sum the projected vectors, and determine the length of the resultant. The factors of safety are determined by comparing this length to the radial distances from the origin to the appropriate yield surfaces. As an alternative, we may work with the principal values of the deviatoric stress. Both approaches are considered.

In Figure E4.3u, the projections of the components of principal stress are shown. Vector OA is the projection of a, and has length ( m 3 ) a,= 97.0 MPa. Likewise, vector AB is the projection of a3and has length ( m 3 ) a, = -26.78 MPa. The sum of these two projections, which are 60"apart (see Figure 4.13), is vector OB, which has length 112.8 MPz If the mean stress, a , = 28.67 MPa, is subtracted from each of the principal stress components, the principal values (S1, S2, S), of the deviatoric stress are obtained as (90.13 MPa, -28.67 MPa, -61.47 MPa) (see EQ. 2.28). The deviatoric stress components (S,, S2, S3) are projected in the same way as the principal stress components. The projections are illusirated in Figure E4.3as vectors OE, EF, and FB,with lengths 73.59, -23.41, and -50.19, respectively. The sum of the three projections is vector OB,which is identical to that in Figure H.3a.Vector OB can be Written in terms of its rectangular components as OB = 107.2011- 35.1 lv, where u and v are horizontal and vertical unit vectors in the n-plane.

I

von Mises circle

von Mises circle

I Tresca hexagon

(4

(b)

FIGURE E4.3 (a) Principal stress projections in the n-plane. ( b ) Deviatoric stress projections in the n-plane.

126

CHAPTER 4 INELASTIC MATERIAL BEHAVIOR

By inspection, we see that the stress state illustrated by vector OB is elastic, since it is within the boundary of the two yield surfaces under consideration. For the Tresca criterion, the factor of safety against yield is the ratio of the lengths of vectors OC and OB. The extension of vector OB to the Tresca hexagon defines point C,the point at which yielding would occur if the given stress state is increased proportionally.Vector OC takes the form OC = 212.13~- 69.48~and has length 223.2 MPa. Hence, the factor of safety against yield for the Tresca criterion is SF = 223.2/112.8 = 1.98. For the von Mises criterion, the factor of safety is the ratio ODIOB. The length of vector OD is simply the radius of the von Mises circle, which is ( m 3 ) Y = 244.95 MPa. Thus, for the von Mises criterion, SF = 244.95/112.8= 2.17.

4.5

ALTERNATIVE YIELD CRITERIA Interest in predicting the initiation of yielding is not limited to ductile metals. Many other materials used in engineering applications exhibit inelastic (yielding) behavior that is distinct from that of ductile metals. Thus, suitable yield criteria for these materials are needed. Some of these materials include soil, rock, concrete, and anisotropic composites. A brief discussion of yield criteria4 for these materials follows in this section.

4.5.1

Mohr-Coulomb Yield Criterion

The yield behavior of many cohesive materials, including rock and concrete, has been observed to depend on hydrostatic stress. Specifically, an increase in hydrostatic compressive stress produces an increased ability of some materials to resist yield. Also, these materials may exhibit different yield stresses in tension and compression. The Mohr-Coulomb yield criterion is a generalization of the Tresca criterion that accounts for the influence of hydrostatic stress. The yield function is written in terms of the stress state and two material properties: the cohesion c and angle of internal friction 4. For principal stresses in the order ol> 0,> 03,the Mohr-Coulomb yield function is (Lubliner, 1990)

f = o,-03+(a,+03)[email protected]@

(4.27)

For unordered principal stresses, the yield function becomes

= YT, 0,= 0,= 0), we can derive the If we impose uniaxial tension until yield occurs (0, yield stress in tension from Eq. 4.27 as

Y, =

2ccosq 1 + sin4

(4.29)

Similarly, if we impose uniaxial compression with a stress state of (q= 0,= 0,0,= -Yc), the yield stress in compression is

2c cos @ Y, = 1 - [email protected]

(4.30)

%e term yield is not entirely appropriate to describe the behavior of some of these materiais in that their nonlinear response is often brittle unless relatively high confining pressure (hydrostatic compression) is applied.

Next Page

4.5

ALTERNATIVE YIELD CRITERIA

127

Equations 4.29 and 4.30 can be solved to obtain c and Cp in terms of YT and Yc as (4.31)

(4.32) If a material such as concrete is being studied and strength paramenters Y, and Yc are known, Eqs. 4.31 and 4.32 can be used to find the properties c and Cp needed by the MohrCoulomb yield function, Eq.4.28. The yield surface for the Mohr-Coulomb criterion has the form of an irregular hexagonal pyramid. The axis of the pyramid is the hydrostatic axis. The geometry of the pyramid depends on c and @.The three-dimensional Mohr-Coulomb yield surface is shown in Figure 4 . 1 5 ~and its intersection with the z-plane is shown in Figure 4.15b. Compressive stress axes are used, as is common in studies of cohesive materials. Enforcing the yield criterion ( f = 0) expressed in Eq. 4.27, we obtain a plane in the sextant o1> 0,> 0,.The other five planes are obtained by enforcing the yield criterion in Eq. 4.28 for the remaining principal stress ordering. Instead of writing equations for the six planes, we can define the geometry of the irregular hexagon by two characteristic lengths, rc and rT, in the z-plane. These lengths have the form (Chen and Han, 1988)

(4.33)

For a frictionless material (Cp = 0), the Mohr-Coulomb criterion reduces to the Tresca criterion, and c = zy,the yield stress in pure shear.

Drucker-Praget Mohr-Coulomb

/

Drucker-Prager Mohr-Coulomb Hydrostatic axis (al = a 2 = u3)

FIGURE 4.15 Mohr-Coulomb and Drucker-Prager yield surfaces. (a) In principal stress space. ( b ) Intersection with the z-plane.

CHAPTER

5

APPLICATIONS OF ENERGY METHODS r E n e r g y methods are used widely to obtain solutions to elasticity problems

and determine deflections of structures and machines. Since energy is a scalar quantity, energy methods are sometimes called scalar methods. In this chapter, energy methods are employed to obtain elastic deflections of statically determinate structures and to determine redundant reactions and deflections of statically indeterminate structures. The applications of energy methods in this book are limited mainly to linearly elastic material behavior and small displacements. However, in Sections 5.1 and 5.2, energy methods are applied to two nonlinear problems to demonstrate their generality. For the determination of the deflections of structures, two energy principles are presented: 1. the principle of stationary potential energy and 2. Castigliano's theorem on deflections.

5.1 ~~~

PRINCIPLE OF STATIONARY POTENTIAL ENERGY ~~

We employ the concept of generalized coordinates (x,,x2, ...,x,) to describe the shape of a structure in equilibrium (Langhaar, 1989; Section 1.2). Since plane cross sections of the members are assumed to remain plane, the changes of the generalized coordinates denote the translation and rotation of the cross section of the member. In this chapter, we consider applications in which a finite number of degrees of freedom, equal to the number of generalized coordinates, specifies the configuration of the system. Consider a system with a finite number of degrees of freedom that has the equilibrium configuration (x,,x2, ...,x,). A virtual (imagined) displacement is imposed such that the new configuration is (x, + 6xl, x2 + h2,...,x, + &,), where (ckl,fk2, ..., &,) is the virtual displacement.' The virtual work &V corresponding to the virtual displacement is given by

6W = Q , 6 x 1 + Q * 6 ~ X 2 + . . . + Q j 6 x i + . . . + Q , 6 ~ ,

(a)

where (Ql, Q2, ..., Q i y ..., Q,) are components of the generalized load. They are functions of the generalized coordinates. Let Qi be defined for a given cross section of the structure; 'Note that the virtual displacement must not violate the essential boundary conditions (support conditions) for the structure.

147

148

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

Q j is a force if 6xjis a translation of the cross section, and Qi is a moment (or torque) if 6xj is a rotation of the cross section. For a deformable body the virtual work 6W corresponding to virtual displacement of a mechanical system may be separated into the sum

m = me+mi

(b)

where 6We is the virtual work of the external forces and 6Wi is the virtual work of the internal forces. Analogous to the expression for 6W in Eq. (a), under a virtual displacement (&,, 6c2, ..., &,), we have

me= P,SX, + P26x2 + ... + P,6x,

(c)

where ( P I ,P,, ...,P,) are functions of the generalized coordinates ( x l ,x2, ...,x,). By analogy to the Qi in Eq. (a), the functions ( P I ,P,, ...,P,) are called the components of generalized external load. If the generalized coordinates (x,, x2, ..., x,) denote displacements and rotations that occur in a system, the variables (P1,P2, ...,P,) may be identified as the components of the prescribed external forces and couples that act on the system. Now imagine that the virtual displacement takes the system completely around any closed path. At the end of the closed path, we have 6Cl = h2= - - - = &, = 0. Hence, by Eq. (c), 6We = 0. In our applications, we consider only systems that undergo elastic behavior. Then the virtual work 6Wi of the internal forces is equal to the negative of the virtual change in the elastic strain energy SU, that is,

m i= -6U

(4

where U = U(x,, x2, ...,x,) is the total strain energy of the system. Since the system travels around a closed path, it returns to its initial state and, hence, 6U = 0. Consequently, by Eq. (d), 6Wi = 0. Accordingly, the total virtual work 6W [Eq. (b)] also vanishes around a closed path. The condition 6W = 0 for virtual displacements that carry the system around a closed path indicates that the system is conservative. The condition 6W = 0 is known as the principle of stationary potential energy. For a conservative system (e.g., elastic structure loaded by conservative external forces), the virtual change in strain energy 6U of the structure under the virtual displacement (&,, &, ..., &,) is

dU 6U = -6x

dU + -6x2

dx,

ax2

+ ... + -dU ax, 'xn

Then, Eqs. (a) through (e) yield the result

or

dU dXi

Qj = Pi--,

i = 1 , 2 , ..., n

For any system with finite degrees of freedom, if the components Qi of the generalized force vanish, then the system is in equilibrium. Therefore, by Eq. (f), an elastic system with n degrees of freedom is in equilibrium if (Langhaar, 1989; Section 1.9)

5.1

PRINCIPLEOF STATIONARY POTENTIAL ENERGY

149

U

s

Elongation e

FIGURE 5.1

Nonlinear elastic load-elongation curve.

P . = dU -,

i = 1 , 2,..., n

dXi

(5.1)

The relation given in Eq. 5.1 is sometimes referred to as Castigliano’sfirst theorem. For a structure, the strain energy U is obtained as the sum of the strain energies of the members of the structure. Note the similarity between Eqs. 5.1 and Eqs. 3.1 1. As a simple example, consider a uniform bar loaded at its ends by an axial load P. Let the bar be made of a nonlinear elastic material with the load-elongation curve indicated in Figure 5.1. The area below the curve represents the total strain energy U stored in the bar, that is, U = P de; then by Eq. 5.1, P = &J/de,where P is the generalized external force and e the generalized coordinate. If the load-elongation data for the bar are plotted as a stress-strain curve, the area below the curve is the strain-energy density Uo stored in the bar (see Figure 3.1). Then, Uo = cr de and, by Eqs. 3.1 1, cr = dUo/de. Equation 5.1 is valid for nonlinear elastic (conservative)problems in which the nonlinearity is due either to finite geometry changes or material behavior, or both. The equation is also valid for systems with inelastic materials as long as the loading is monotonic and proportional. The following example problem indicates the application of Eq. 5.1 for finite geometry changes.

EXAMPLE 5.1 Equilibrium of a Linear Elastic Two-Bar System

Two bars AB and CB of lengths L,and L,, respectively, are attached to a rigid foundation at points A and C, as shown in Figure E5.la. The cross-sectional area of bar AB is A and that of bar CB is A,. The corresponding moduli of elasticity are El and E,. Under the action of horizontal and vertical forces P and Q, pin B undergoes finite horizontal and vertical displacement with components u and v, respectively (Figure E5. la). The bars AB and CB remain linearly elastic.

(a)Derive formulas for P and Q in terms of u and v. (b) Let E,A,/L, = K, = 2.00 N/mm and E2A2/L2= K2 = 3.00 N/mm, and let bl = h = 400 mm and b, = 300 mm. For u = 30 mm and v = 40 mm, determine the values of P and Q using the formulas derived in part (a). (c) Consider the equilibrium of the pinB in the displaced position B* and verify the results of part (b).

(d) For small displacement components u and v (u, v to the average shear stress Vy/A. For example, by this procedure, the magnitude of k for the rectangular cross section is

(5.15)

This value is larger and hence more conservative than the more exact value 1.20. Nevertheless, since the more precise value is known, we recommend that k = 1.20 be used for rectangular cross sections. Values of k are listed in Table 5.1 for several beam cross sections.

5.3.3

Strain Energy UTfor Torsion

The strain energy U, for a torsion member with circular cross section (Figure 5 . 7 ~ may ) be derived as follows: Let the z axis lie along the centroidal axis of the torsion member. Before torsional loads T I and T2 are applied, sections BC and DF are a distance dz apart. After the torsional loads are applied, these sections become sections B*C* and D*F*, with section

(a)

FIGURE 5.7

Strain energy resulting from torsion.

5.3

CASTIGLIANO'S THEOREM ON DEFLECTIONS FOR LINEAR LOAD-DEFLECTION RELATIONS

161

D*F* rotated relative to section B*C* through the angle dp, as shown in the enlarged freebody diagram of the element of length dz (Figure 5.7b). For linear elastic material behavior, d p varies linearly with T (Figure 5.7~).The shaded area below the inclined straight line is equal to the torsional strain energy dUT for the segment dz of the torsion member. Hence, the total torsional strain energy UT for the torsional member becomes

Noting that b d p = ydz and assuming that y = z/G and Z= Tb/J (where b is the radius and J is the polar moment of inertia of the cross section), we may write UTin the form

(5.16) Equation 5.16 represents the strain energy for a torsion member with circular cross section. The unit angle of twist 8for a torsion member of circular cross section is given by 8= TIGJ. Torsion of noncircular cross sections is treated in Chapter 6. Equation 5.16 is valid for other cross sections if the unit angle of twist 8 for a given cross section replaces T/GJ in Eq. 5.16. For abrupt changes in material E, torsional load T, or polar moment of inertia J, the value of UTmay be computed following the same procedure as for U, (Eq. 5.9).

EXAMPLE 5.3 Linear SpringWeight System

Consider weights W, and W2 supported by the linear springs shown in Figure E5.3.The spring constants are k , and k,. Determine the displacements q1and q2 of the weights as functions of W,, W2,k l , and k2. Assume that the weights are applied slowly so that the system is always in equilibrium as the springs are stretched from their initially unstretched lengths.

FIGURE E5.3

Solution

Under the displacements q1 and q2, spring 1 undergoes an elongation q1 and spring 2 undergoes an elongation q2 - q,. Hence, by Eq. 5.12, the potential energy stored in the springs is

The internal tension forces in springs 1 and 2 are

F , = k,q,,

F , = k,(q,-q,)

But by equilibrium,

F , = W , iW 2 , F2 = W 2

162

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

Then, by Eqs. (a)-(c), the potential energy in terms of W,, W2,k,,and k2 is

u = I(W1 - + W2I2 + -1 -w; 2

2 k2

kl

By Eqs. 5.4 and (d), we obtain

au - W l + W 2

ql=aw,--

kl

au

Wl+W2

aw2

kl

q 2 = - = -

+-W2

(el

k2

Equation (e) agrees with a direct solution of Eqs. (b) and (c), without consideration of potential energy.

EXAMPLE 5.4 Nonlinear Spring System

Assume that the force-elongation relation for the springs of Example 5.3 is

F = kx 2

(4

Determine the displacements q1 and q2 of the weights as functions of W1, W2, k,, and k2

Solution

[\$

1/2

x =

Hence, by Eqs. 5.1 1 and (b), the complementary strain energy of the system is

or

By equilibrium, as in Example 5.3, F , = Wl+W2,

F, = W ,

So, Eqs. (c) and (d) yield 2 (W,

c =3- [

+ w2)3/2 k:l2

+-I

wy2 kk/2

Then, by Eqs. 5.2 and (e), we obtain 41 =

w, + w, m1 = [7-]

5.4

DEFLECTIONS OF STATICALLY DETERMINATE STRUCTURES

163

5.4 DEFLECTIONS OF STATICALLY DETERMINATE STRUCTURES In the analysis of many engineering structures, the equations of static equilibrium are both necessary and sufficient to solve for unknown reactions and for internal actions in the members of the structure. For example, the simple structure shown in Figure E5.1 is such a structure; the equations of static equilibrium are sufficient to solve for the tensions N , and N , in members AB and CB, respectively. Structures for which the equations of static equilibrium are sufficient to determine the unknown tensions, shears, etc., uniquely are said to be statically determinate structures. Implied in the expression “statically determinate” is the condition that the deflections caused by the loads are so small that the geometry of the initially unloaded structure remains essentially unchanged and the angles between members are essentially constant. If these conditions were not true, the internal tensions, etc., could not be determined without including the effects of the deformation and, hence, they could not be determined solely from the equations of equilibrium. The truss shown in Figure 5.8 is a statically determinate truss. A physical characteristic of a statically determinate structure is that every member is essential for the proper functioning of the structure under the various loads to which it is subjected. For example, if member AC were to be removed from the truss of Figure 5.8, the truss would collapse. Often, additional members are added to structures to stiffen the structure (reduce deflections), to strengthen the structure (increase its load-canying capacity), or to provide alternate load paths (in the event of failure of one or more members). For example, for such purposes an additional diagonal member BD may be added to the truss of Figure 5.8; see Figure 5.9. Since the equations of static equilibrium are just sufficient for the analysis of the truss of Figure 5.8, they are not adequate for the analysis of the truss of Figure 5.9. Accordingly, the truss of Figure 5.9 is said to be a statically indeterminate structure. The analysis of statically indeterminate structures requires additional information (additional equations) beyond that obtained from the equations of static equilibrium.

lQ

FIGURE 5.8

Statically determinate truss.

Ql

FIGURE 5.9 Statically indeterminate truss.

164

CHAPTER 5 APPLICATIONS

OF ENERGY METHODS

In this section, the analysis of statically determinate structures is discussed. The analysis of statically indeterminate structures is presented in Section 5.5. The strain energy U for a structure is equal to the sum of the strain energies of its members. The loading for thejth member of the structure is assumed to be such that the strain energy U j for that member is

where UNj,UMj,Usj, and UTjare given by Eqs. 5.8, 5.13, 5.14, and 5.16, respectively. In the remainder of this chapter the limitations placed on the member cross section in the derivation of each of the components of the strain energy are assumed to apply. For instance, each beam is assumed to undergo bending about a principal axis of the beam cross section (see Appendix B and Chapter 7); Eqs. 5.13 and 5.14 are valid only for bending about a principal axis. For simplicity, we consider bending about the x axis (taken to be a principal axis) and let M, = M and Vy = V With the total strain energy U of the structure known, the deflection q, of the structure at the location of a concentrated force Fiin the direction of Fiis (see Eq. 5.4)

(5.17)

and the angle (slope) change 0, of the structure at the location of a concentrated moment

M iin the direction of M iis (see Eq. 5.5)

(5.18)

where m is the number of members in the structure. Use of Castigliano’s theorem on deflections, as expressed in Eqs. 5.17 and 5.18, to determine deflections or rotations at the location of a concentrated force or moment is outlined in the following procedure:

1. Write an expression for each of the internal actions (axial force, shear, moment, and torque) in each member of the structure in terms of the applied external loads. 2. To determine the deflection q iof the structure at the location of a concentrated force Fiand in the directed sense of Fi,differentiate each of the internal action expressions with respect to Fi.Similarly, to determine the rotation 0, of the structure at the location of a concentrated moment M iand in the directed sense of Mi, differentiate each of the internal action expressions with respect to M , .

5.4

DEFLECTIONS OF STATICALLY DETERMINATE STRUCTURES

165

3. Substitute the expressions for internal actions obtained in Step 1 and the derivatives obtained in Step 2 into Eq. 5.17 or 5.18 and perform the integration. The result is a relationship between the deflection qi(or rotation Oi)and the externally applied loads. 4. Substitute the magnitudes of the external loads into the result obtained in Step 3 to obtain a numerical value for the displacement qior rotation Oi.

5.4.1

Curved Beams Treated as Straight Beams

The strain energy resulting from bending (see Eq.5.13) was derived by assumingthat the beam is straight. The magnitude of U, for curved beams is derived in Chapter 9, where it is shown that the error in using Eq.5.13 to determine U, is negligible as long as the radius of curvatureof the beam is more than twice its depth. Consider the curved beam in Figure 5.10 whose strain energy is the sum of UN,Us, and U, each of which is caused by the same load P. If the radius of curvature R of the curved beam is large comparedto the beam depth, the magnitudesof UNand Us will be small compared to U, and can be neglected. We assume that UN and Us can be neglected when the ratio of length to depth is greater than 10. The resulting error is often less than 1%and will seldom exceed 5%. Numerical results are obtained in Examples5.9 and 5.10.

FIGURE 5.10

EXAMPLE 5.5 End Load on a Cantilever Beam

I

Curved cantilever beam.

Determine the deflection under load P of the cantilever beam shown in Figure E5.5.Assume that the beam length L is more than five times the beam depth h.

I

FIGURE E5.5

Solution

I

Since L > 5h, the strain energy Us is small and will be neglected. Therefore, the total strain energy is (Eq. 5.13)

u=u,= 0

By Castigliano’s theorem, the deflection qp is (Eq. 5.2)

0

I

By Figure E5.5,M, = Pz. Therefore, aM,/dP = z, and by Eq. (b), we find L

2

Pz qp = j-dz EI, 0

I This result agrees with elementarybeam theory.

=

PL3 3E1,

100

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

EXAMPLE 5.€ Cantilever Bean Loaded ir Its Plant

The cantilever beam in Figure E5.6 has a rectangular cross section and is subjected to equal loads P at the free end and at the center as shown.

: O=P

C

A

B

-I

2

4

FIGURE E5.6 (a) Determine the deflection of the free end of the beam.

(b) What is the error in neglecting the strain energy resulting from shear if the beam length L is five times the beam depth h? Assume that the beam is made of steel (E = 200 GPa and G = 77.5 GPa).

Solution

(a) To determine the dependencies of the shear V and moment M on the end load P, it is necessary to distinguish between the loads at A and B. Let the load at B be designated by Q . The moment and shear functions are continuous from A to B and from B to C. From A to B, we have

V = P ,

*

*.

M = Pz,

From B to C, we have

..

V=P+Q,

*

dM

“. a p = z

g

[ );

% - l z -

‘ M = P z + - +QZ,

= 1

dM

-

.* . = = z + -

L 2

where we have chosen point B as the origin of coordinate Z for the length from B to C. Equation 5.17 gives (with Q = P and k = 1.2)

(b) Since the beam has a rectangular section,A = bh and I = bh3/12.Equation (a) can be rewritten as follows:

EbqP - - - - 1.8LE + 7( 12)L3

P

-

Gh

16h3

- 1.8(5)(200)+ 7 ( 1 2 ) ( S 3 ) 77.5

16

= 23.23 + 656.25 = 679.48

Therefore, the error in neglecting shear term is 23.23(100) = 3.42% 679.48 Alternatively, one could have used the approximatevalue k = 1.50 (Eq. 5.15). Then the estimate of shear contribution would have been increased by the ratio 1.50/1.20 = 1.25. Overall the shear contribution would still remain small.

5.4

DEFLECTIONS OF STATICALLY DETERMINATE STRUCTURES

167

A shaft AB is attached to the beam CDFH, see Figure E5.7. A torque of 2.00 kN m is applied to the end B of the shaft. Determine the rotation of section B. The shaft and beam are made of an aluminum alloy for which E = 72.0 GPa and G = 27.0 GPa. Assume that the hub DF is rigid.

EXAMPLE 5.7 A Shaft-Beam Mechanism

2 kN-rn

FIGURE E5.7

Solution

Shaft-beam mechanism.

Since the beam is slender, the strain energy resulting from shear can be neglected. Hence, the total strain energy of the mechanism is

The pin reactions at C and H have the same magnitude but opposite sense. Therefore, moment equilibrium yields the result

H = C = T/lOOO

(b)

By Castigliano's theorem, the angular rotation at B is

By Figure E5.7 and Eq. (b), we have

T = 2,000,000 N mm, M, = Czl = O.OOITzl [N mm]

(4

= 1.272 x lo6 mm4, Eqs. (c) and (d) yield With I, = (30)(40)3/12= 160,000 mm4 and J = ?~(60)~/32 9, = 0.054 rad.

The cantilever beam in Figure E 5 . 8 ~is subjected to a uniformly distributed load w.Determine the deflection of the free end. Neglect the shear strain energy Us.

EXAMPLE 5.8 Uniformly Loaded Cantilever Beam

(a)

I

FIGURE E5.8

Uniformly loaded cantilever beam.

168

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

Solution

Since there is no force acting at the free end, we introduce the fictitious force P (Figure E5.8b). (See the discussion in Section 5.4.2.) Hence, the deflection qp at the free end is given by (see Eq. 5.2) (a) P=O

The bending moment M, caused by P and w is 1 2 M, = Pz+-wz

(b)

2

and

-=z dM, dP Substitution of Eqs. (b) and (c) into Eq. (a) yields 4

L

qp =

1 WL ~(Pz + i w z 2 ) / z dz = 8EI, EIx P=O

This result agrees with elementary beam theory.

EXAMPLE 5.9 Curved Beam Loaded in Its Plane

The curved beam in Figure E5.9 has a 30-mm square cross section and radius of curvature R = 65 111111. The beam is made of a steel for which E = 200 GPa and v = 0.29.

(a) If P = 6.00 kN, determine the deflection of the free end of the curved beam in the direction of P. (b) What is the error in the deflection if U, and Usare neglected?

FIGURE E5.9

Solution

The shear modulus for the steel is G = E/[2(1 + v)]= 77.5 GPa. (a) It is convenient to use polar coordinates. For a cross section of the curved beam located at angle 8 from the section on which P is applied (Figure E5.9),

N = pcose,

ZdP ! = case

V = Psino,

dP = sine

M = PR(i-cose),

dM = R(i-cose) dP

(a)

5.4

1

DEFLECTIONS OF STATICALLY DETERMINATE STRUCTURES

169

Substitution into Eq. 5.17 gives

I

3d2

3d2

cos8)R d8+ 0

1 k PGAs i n ( s i n 8 ) Rd8 0

3d2

+

P R ( 1 ~ ~ e ) R ( 1 - c o s 8 ) Rd8 0

Using the trigonometric identities cos2 8 =

4p =

-

1 + -1 2 2

cos 28 and sin2 8 = 1 - -1 cos 28, we find that 2

2

3zPR + 1.2(3n)PR + 4GA

4EA

3~(65)(6000) 4(200x 103)(30)2

+

1.2(3z)(65)(6000) 4(77,500)(30)2

= 0.0051 + 0.0158 + 1.1069 = 1.1278

+

-

['

(65)3(6000)( 12)

+

1,200 x 1 ~ ) ~ ) ( 3 0 ) ~

(b) If U, and Usare neglected,

q p = 1.1069mm and the percentage error in the deflection calculation is - 1.85% error = (1.1278 - 1.1069)100 1.1278

This error is small enough to be neglected for most engineering applications. The ratio of length to depth for this beam is 3z(65)/[2(30)] = 10.2 (see Section 5.4.1).

EXAMPLE 5.10 Semicircular Cantilever Beam

The semicircularcantilever beam in Figure E5.10 has a radius of curvatureR and a circular cross section of diameter d. It is subjected to loads of magnitude P at points B and C.

PI FIGURE E5.10 (a) Determine the vertical deflection at C in terms of P, modulus of elasticity E, shear modulus G, radius of curvature R, cross-sectionalarea A, and moment of inertia of the cross section 1.

(b) Let P = 150 N, R = 200 mm, d = 20.0 mm, E = 200 GPa, and G = 77.5 GPa. Determine the effect of neglecting the strain energy Usdue to shear.

170

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

Solution

(a) Since we wish to determine the vertical deflection at C, the contribution to the total strain energy of the load at C must be distinguished from the contribution of the load at B. Therefore, as in Example 5.6, we denote the load P at B by Q (= P in magnitude) (Figure E5.10). For section BC, we have

!!idP

N = PCOS~, V = Psing,

M

=

= sin4

ap

= PR( 1 - COS~),

COSQ

-ah'- - R ( l dP

cosq)

For section AB,we have

N = (P+Q)sin6, V = (P+Q)cos6,

M = PR(l+sin6)+QRsin6, Substitution of Eqs. (a) and (b) into Eq. 5.17 yields, with k = 1.33,

znPR2(1 - COS4)'

'1 '1"'1.33(P 0

0

""PR(1

+I

EI

+ Q)sin26Rde

"'(P

I

Rd'+

EA

0

+ Q)cos26R d e GA

+ sin6)+QRsin6

0

(1

Rde

EI

Integration yields, if we note that Q = P, 3 a P R 3 n 133PR qc = --+-L 4 EA 4 GA +

The three terms on the right-hand side of Eq. (d) are the contributions of the axial force, shear, and moment, respectively, to the displacement qc. (b) For P = 150 N, R = 200 mm, d = 20.0 mm (hence,A = 314 mm' and I = 7850 mm4),E = 200 GPa, and G = 77.5 GPa, Eq. (d) yields

qc = 0.0011 +0.0039 + 4.9666 = 4.97 mm where 0.001 1 is due to the axial force, 0.0039 is due to shear, and 4.9666 is due to moment. The contributions of axial load and shear are negligible. Since Rld = 200/20 = 10, this result confirms the statement at the end of Section 5.4.1.

5.4.2 Dummy Load Method and Dummy Unit Load Method As illustrated in the preceding examples, Castigliano's theorem on deflections, as expressed in Eqs. 5.17 and 5.18, is useful for the determination of deflections and rotations

5.4

DEFLECTIONS OF STATICALLY DETERMINATE STRUCTURES

17 1

at the locations of concentrated forces and moments. Frequently, it is necessary to determine the deflection or rotation at a location that has no corresponding external load (see Example 5.8). For example, we might want to know the rotation at the free end of a cantilever beam that is subjected to concentrated loads at midspan and at the free end but has no concentrated moment at the free end (as is the case in Example 5.6). Castigliano’s theorem on deflections can be applied in these situations as well. The modified procedure, known as the dummy load method, is as follows:

1. Apply a fictitious force Fi(or fictitious moment Mi)at the location and in the direction of the displacement qi(or rotation ei)to be determined. 2. Write an expression for each of the internal actions (axial force, shear, moment, and torque) in each member of the structure in terms of the applied external forces and moments, including the fictitious force (or moment). 3. To determine the deflection qiof the structure at the location of a fictitious force Fi and in the sense of Fi,differentiate each of the internal action expressions with respect to Fi.Similarly, to determine the rotation eiof the structure at the location of a fictitious moment M iand in the sense of Mi,differentiate each of the internal action expressions with respect to Mi. 4. Substitute the expressions for the internal actions obtained in Step 2 and the derivatives obtained in Step 3 into Eq. 5.17 or 5.18 and perform the integration. The result is a relationship between the deflection qi(or rotation ei)and the externally applied loads, including the fictitious force Fi(or moment Mi). 5. Since, in fact, the fictitious force (or moment) does not act on the structure, set its value to zero in the relation obtained in Step 4.Then substitute the numerical values of the external loads into this result to obtain the numerical value for the displacement qi(or rotation @). The name dummy load method derives from the procedure. A fictitious (or dummy) load is applied, its effect on internal actions is determined, and then it is removed. If the procedure is limited to small deflections of linear elastic structures (consisting of tension members, compression members, beams, and torsion bars), then the derivatives of the internal actions with respect to the fictitious loads are equivalent to the internal actions that result from a unitforce (or unit moment) applied at the point of interest. When the method is used in this manner, it is referred to as the dummy unit load method. The net effect of this procedure is that it eliminates the differentiation in Eqs. 5.17 and 5.18. The internal actions (axial, shear, moment, and torque, respectively) in member j resulting from a unit force at location i may be represented as (5.19a) Similarly, the internal actions in member j resulting from a unit moment at location i may be represented as (5.19b) In the dummy unit load approach, Eqs. 5.17 and 5.18 take the form F

F

F

Gj Aj

5 zj

q i = g [ , \$ .N.n \$ d ..z + , - dk.V.v z + , .u. d z + M.m .. j = 1

F

]

T.t u d.. z

I,,

(5.20a)

172

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

(5.20b) j = 1

where N j , V j ,Mi, and Tiare the internal member forces resulting from the real loads. The use of this method is illustrated in the following examples.

EXAMPLE 5.1 1 Cantilever Beam Deflections and Rotations

The cantilever beam in Figure E5.11 has a rectangular cross section and is subjected to a midspan load P as shown. Neglect strain energy resulting from shear.

FIGURE E5.11 (a) Determine the vertical deflection and rotation of the free end of the beam by the dummy load method.

(b) Show that the same results are obtained by the dummy unit load method.

Solution

(a) The first step in the dummy load method is to apply a fictitious load FA and a fictitious moment MA at pointA as shown in Figure E5.11.Next, we write the moment expressions for the two intervals of the beam. For intervalA-B

MA, = MA+FAz For interval B-C

( I;)

MBc = M A + F A Z + -

+PZ

Differentiation of Eqs. (a) and (b) with respect to the fictitious force and moment yields, for intervalA-B,

and for interval B-C,

To find the vertical deflection at point A, we substitute Eqs. (a), (b), (c), and (e) into Eq. 5.17 and perform the integration: Lt.2 L ~ . ~ M ~ z + F A( ) ( z ) d z + 'A = EI 0 0

5

MA + FA( 2

+L / 2 ) +P Y EI

[Z + i ) d Z

5.4

")

= MA( 2EI

DEFLECTIONSOF STATICALLY DETERMINATE STRUCTURES

173

") (*)

+ FA( 3EI + P

48EI

Since, in fact, the fictitious loads FA and MA do not exist, they are set to zero. Then Eq. (h) yields the deflection of point A as

5PL3 9.4 = 48EI To find the rotation of the section at A, we substitute Eqs. (a), (b), (d), and (f) into Eq. 5.18 and perform the integration:

Again, the fictitious loads FA and MA are set to zero. Then Eq.Q yields the rotation of the section at A as

8 - PLL

A-8EI

(b) In the dummy unit load method, FA and MA are set to unity. Then the internal moment M resulting from the real force at B and the internal moments mF and r# (see Eqs. 5.19a and 5.19b) resulting from the unit force and unit moment at A are, for intervalA-B, MAB = 0 F mAB

(m)

= l.O(z) = z

M

nAB= 1.0 and for interval B-C,

MBC = PZ

(4)

m B C = 1.0 F + F

M

mBC = 1.0

=

z+y

-

L

(r)

The deflection at point A is obtained by the substitution of Eqs. (m), (n), (p), and (9) into Eq. 5.20a. The result is [see Eq. (i)]

- -5PL'

48EI

The rotation of the section at A is obtained by the substitution of Eqs. (m), (o), (p), and (r) into Eq. 5.20b. The result is (see Eq. 1)

Thus, the equivalence of the dummy load approach with the dummy unit load approach is demonstrated for this example.

174

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

EXAMPLE 5.12 Pin-Connectea Truss

The pin-connected truss in Figure E5.12 is made of an aluminum alloy for which E = 72.0 GPa. The magnitudes of the loads are P = 10 kN and Q = 5 kN. Members BC, CD, and DE each have crosssectional area of 900 mm2. The remaining members each have cross-sectional area of 150 mm2. Determine the rotation of member BE caused by the loads P and Q.

Q FIGURE E5.12

Solution

To determine the rotation of member BE by energy methods, a moment M must be acting on member BE. Let M be an imaginary counterclockwise moment represented by a couple with equal and opposite forces M/L(L = BE = 2500 mm) applied perpendicular to BE at points B and E as indicated in Figure E5.12. Equations of equilibrium give the following values for the axial forces in the members of the structure:

NAB = ;(Q

+ 2P)-

NAB -- - _5 -

5M -, 3L

dM

-aNBC =o

5 NBC = - 3 ( Q + P ) , NED=

3L

aM

-~ =NoB D

Q,

dM ~ N B E= --4 -

5P 4 M NBE = T - F ~

dM

-

4P+5M 3 3L’

N c D = NDE = --

aNCD

3L

- 5

aM - 3L

After the partial derivatives aNjldM have been taken, the magnitude of M in the Nj is set to zero. The values of N j and dNj/aM are then substituted into Eq. 5.18 to give

I“

- 2(4)(10,000~(2000)

3( 72,OO0)(900)

3 (2500)

= - 0.0041 15 - 0.002058 - 0.000549

The negative sign for e,, indicates that the angle change is clockwise; that is, the angle change has a sign opposite to that assumed for M.

5.4

EXAMPLE 5.13 Curved Beam Loaded Perpendicular t o Its Plane

DEFLECTIONS OF STATICALLY DETERMINATESTRUCTURES

175

The semicircular curved beam of radius R in Figure E5.13 has a circular cross section of radius r. The curved beam is indicated by its centroidal axis to simplify the figure. It is fixed at 0 and lies in the (x, y) plane with center of curvature at C on the x axis. Load P parallel to the z axis acts at a section n/2 from the fixed end. Determine the z component of the deflection of the free end. Assume that R/r is sufficiently large for Us to be negligible.

FIGURE E5.13

Solution

To find the z component of the deflection of the free end of the curved beam, a dummy unit load parallel to the z axis is applied at B as indicated in Figure E5.13. Consider a section D of the curved beam at an angle 8 measured from section A at the load P. The internal moment and torque at section D resulting from forces at A and B are

M, = P(AF) = PRsinB T , = P(DF) = PR( 1 - case) F

m, = l.O(BE) = Rcos8

t i = l.O(DC + C E ) = R( 1 + sine) These values are substituted into Eqs. 5.20a and 5.20b to give

[

PRsinO(Rcos8)+PR(1-cos8)[R(1 E[ GJ 0

7r’2

qB =

+ sine)]

1

Rde

~ - ~-[ P 1R+ (1 + v)(n- l ) ] nEr4

EXAMPLE 5.14 Stiffness of a Coil Spring

A coil spring is formed by winding a wire (or circular rod) of diameter d into a helix with diameter D, number of coils n, and pitch angle p (see Figure E 5 . 1 4 ~in which n = 3). Assume that the material has modulus of elasticity E and shear modulus G. Determine the stiffness of the spring under a concentric axial load P. Ignore end effects; that is, ignore the method by which the axial load is applied to the ends of the spring. Assume that the ratio d/D is small enough that the equations for bending and torsion of straight members (Chapter 1 ) apply.

176

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

(a)

FIGURE E5.14

Solution

Even though the force P acts at the location and in the direction of interest, we use the dummy unit load method to find deflection of the spring. The concentric axial load P causes a shear force V and a normal force N that act on the cross section of the wire. The effect of these internal forces is expected to be small and we dismiss them from consideration here. The load P has a lever arm of D/2 relative to the centroidal axis of the wire. Hence it produces a moment of magnitude PD/2. The components of this moment relative to the cross-sectional plane of the wire are a bending moment M and a torque T (see the enlarged view of a portion of the top coil in Figure 5.14b) given by

If end effects are ignored, M and T are each constant over the full length of the spring. The corresponding moment and torque in the spring caused by a concentric unit axial load on the spring are

Substitution of Eqs. (a) and (b) into Eq. 5.20a gives

The differential ds is an element of arc length of the wire. The limit of integrationL is the total length of wire in the spring, which is approximated as L = n z D . Since all quantities are constant with respect to s, the integration is trivial. Hence, the axial deflection of the spring is

The spring stiffness k is found by dividing the axial load P by the deflection q from Eq. (c). After substitution for A, I, and J in terms of d, this results in k =

EGd4 8nD3(2G sin2P+ E cos2p)

5.5

STATICALLY INDETERMINATE STRUCTURES

177

The relative effects of the bending and torsional moments on the stiffness of the spring can now be examined. For instance, in a closely wound spring the pitch angle p i s small and the effect of bending moment M is small. For this case, sin2p = 0, cos2p = 1, and only the torque T contributes to strain energy in the spring. Hence, the stiffness is given by Gd4 k, = -

8nD3

5.5 STATICALLY INDETERMINATE STRUCTURES As we observed in Section 5.4,a statically determinate structure (Figure 5.8) may be made statically indeterminate by the addition of a member (member BD in Figure 5.9). Alternatively, a statically indeterminate structure may be rendered statically determinate if certain members, internal actions, or supports are removed. For example, the truss in Figure 5.9 is rendered statically determinate if member BD (or equally well member AC) is removed. Such a member in a statically indeterminate structure is said to be redundant, since after its removal the structure will remain in static equilibrium under arbitraq loads. In general, statically indeterminate structures contain one or more redundant members or supports. For simplicity a redundant member or redundant support is often referred to only as a redundant, without additional qualification. Generally in the analysis of structures, internal actions in each member of the structure must be determined. For statically indeterminate structures, the equations of static equilibrium are not sufficient to determine these internal actions. For example, in Figure 5.1la, the propped cantilever beam has four unknown support reactions, whereas there are only three equations of equilibrium for a planar structure. If the support at B were removed, the beam would function as a simple cantilever beam. Hence, we may consider the support at B to be redundant and, if it is removed, the beam is rendered statically determinate. The choice of the redundant is arbitrary. If we consider the support at B to be redundant, additional information is required to determine the magnitude of the reaction R (see Figure 5.1 lc). As we shall see, the fact that

(b)

FIGURE 5.1 1 Structures with redundant supports.

Next Page

178

CHAPTER 5 APPLICATIONS OF ENERGY METHODS

the support at B prevents the tip of the beam from displacing vertically may be used, in conjunction with Castigliano’s theorem on deflections, to obtain the additional equation needed to determine the redundant reaction R. Likewise, the three support reactions at A (or E ) for member ABCDE in Figure 5.1 lb can be chosen as the redundants. Hence, either the support at A or E (but not both) may be removed to render the structure statically determinate. Let us assume that the support reactions at E are chosen as the redundants (Figure 5.114.The three redundant reactions are a vertical force VE,which prevents vertical deflection at E; a bending moment ME, which prevents bending rotation of the section at E; and a torque TE,which prevents torsional rotation of the section at E. The fact that vertical deflection, bending rotation, and torsional rotation are prevented at section E may be used, in conjunction with Castigliano’s theorem on deflections, to obtain the additional equations needed to determine the support reactions at E. The structures in Figure 5.12 do not contain redundant reactions but do contain redundant members. In Figure 5.12a,the member BE (or CD) of the truss is redundant. Hence, the truss is statically indeterminate. If either member BE or member C D is removed, the truss is rendered statically determinate. Likewise, the member ABC of the statically indeterminatestructurein Figure 5.12b is redundant. It may be removed to render the structurestaticallydeterminate. Since the truss of Figure 5.12~2is pin-joined, the redundant member BE is subject to an internal axial force. Hence, the only redundant internal force for the truss is the tension in member BE (Figure 5.12~).However, the redundant member ABC of the structure in Figure 5.12d may support three internal reactions: the axial force N, shear V , and moment M.The additional equations (in addition to the equations of static equilibrium) required to determine the additional unknowns (the redundant internal actions caused by redundant members) in statically indeterminant structures may be obtained by the application of Castigliano’s theorem on deflections. In particular, we can show that

(5.21)

(b)

FIGURE 5.12 Structures with redundant members.

CHAPTER

6

TORSION I

In this chapter, we treat the problem of torsion of prismatic bars with noncircular cross sections. We treat both linearly elastic and fully plastic torsion. For prismatic bars with circular cross sections, the torsion formulas are readily derived by the method of mechanics of materials. However, for noncircular cross sections, more general methods are required. In the following sections, we treat noncircular cross sections by several methods, one of which is the semiinverse method of Saint-Venant (Boresi and Chong, 2000). General relations are derived that are applicable for both the linear elastic torsion problem and the fully plastic torsion problem. To aid in the solution of the resulting differential equation for some linear elastic torsion problems, the Saint-Venant solution is used in conjunction with the Prandtl elastic-membrane (soap-film) analogy. The semiinverse method of Saint-Venant is comparable to the mechanics of materials method in that certain assumptions, based on an understanding of the mechanics of the problem, are introduced initially. Sufficient freedom is allowed so that the equations describing the torsion boundary value problem of solids may be employed to determine the solution more completely. For the case of circular cross sections, the method of SaintVenant leads to an exact solution (subject to appropriate boundary conditions) for the torsion problem. Because of its importance in engineering, the torsion problem of circular cross sections is discussed first.

6.1 TORSION OF A PRISMATIC BAR OF CIRCULAR CROSS SECTION Consider a solid cylinder with cross-sectional area A and length L. Let the cylinder be subjected to a twisting couple T applied at the right end (Figure 6.1). An equilibrating torque acts on the left end. The vectors that represent the torque are directed along the z axis, the centroidal axis of the shaft. Under the action of the torque, an originally straight generator of the cylinder AB will deform into a helical curve AB*.However, because of the radial symmetry of the circular cross section and because a deformed cross section must appear to be the same from both ends of the torsion member, plane cross sections of the torsion member normal to the z axis remain plane after deformation and all radii remain straight. Furthermore, for small displacements, each radius remains inextensible. In other words, the torque T causes each cross section to rotate as a rigid body about the z axis (axis of the couple); this axis is called the axis oftwist. The rotation p of a given section, relative to the plane z = 0, will depend on its distance from the plane z = 0. For small deformations,

200

6.1

TORSION OF A PRISMATIC BAR OF CIRCULAR CROSS SECTION 201

Undeformed position of generator

.L’I

FIGURE 6.1 Circular cross section torsion member.

following Saint-Venant, we assume that the amount of rotation of a given section depends linearly on its distance z from the plane z = 0. Thus,

p

= 8z

(6.1)

where 8 is the angle of twist per unit length of the shaft. Under the conditions that plane sections remain plane and Eq. 6.1 holds, we now seek to satisfy the equations of elasticity; that is, we employ the semiinverse method of seeking the elasticity solution. Since cross sections remain plane and rotate as rigid bodies about the z axis, the displacement component w,parallel to the z axis, is zero. To calculate the (x, y) components of displacements u and v, consider a cross section at distance z from the plane z = 0. Consider a point in the circular cross section (Figure 6.2) with radial distance OP. Under the deformation, radius OP rotates into the radius OP* (OP* = OP). In terms of the angular displacement p of the radius, the displacement components (u, v) are u = x*-x

= oP[cos(p+Cp)-cosCp]

v = y * - y = OP[sin(P+Cp)-sinCp] Expanding cos(p + Cp) and [email protected] + Cp) and noting that x = OP cos Cp and y = OP sin Cp, we may write Eqs. 6.2 in the form u = x(cosp- 1 ) -ysinp

v = xsinp+y(cOsp-l)

FIGURE 6.2 Angular displacement p.

202

CHAPTER6 TORSION

Restricting the displacement to be small (since then sin p = p and cos p = l), we obtain with the assumption that w = 0, 24

v = xp,

= -yp,

w =0

(6.4)

to first-degree terms in p. Substitution of Eq. 6.1 into Eqs. 6.4 yields u = -6yz

, v=exz,

w=o

(6.5)

On the basis of the foregoing assumptions, Eqs. 6.5 represent the displacement components of a point in a circular shaft subjected to a torque T. Substitution of Eqs. 6.5 into Eqs. 2.81 yields the strain components (if we ignore temperature effects) E,

- eyy -

E,,

=

E

XY

= 0 , 2 ~ , , = y,,

= -6y, 2eZy = y,,

= OX

(6.6)

Since the strain components are derived from admissible displacement components, compatibility is automatically satisfied. (See Section 2.8; see also Boresi and Chong, 2000, Section 2.16.) With Eqs. 6.6, Eqs. 3.32 yield the stress components for linear elasticity oXx=

oYy- oZz= oXy=

0,

oZx= -6Gy,

oZy= OGx

(6.7)

Equations 6.7 satisfy the equations of equilibrium, provided the body forces are zero (Eqs. 2.45). To satisfy the boundary conditions, Eqs. 6.7 must yield no forces on the lateral surface of the bar; on the ends, they must yield stresses such that the net moment is equal to T and the resultant force vanishes. Since the direction cosines of the unit normal to the lateral surface are (1, m,0) (see Figure 6.3), the first two of Eqs. 2.10 are satisfied identically. The last of Eqs. 2.10 yields

lo,,+ muzy = 0

(6.8)

By Figure 6.3,

I =

C O S ~=

X

b’

m = sin#=

2 b

Substitution of Eqs. 6.7 and 6.9 into Eqs. 6.8 yields

-xr+xr b b

=0

Therefore, the boundary conditions on the lateral surface are satisfied.

FIGURE 6.3

Unit normal vector.

(6.9)

6.1

TORSION OF A PRISMATIC BAR OF CIRCULAR CROSS SECTION

203

On the ends, the stresses must be distributed so that the net moment is T. Therefore, summation of moments on each end with respect to the z axis yields (Figure 6.4)

x M Z= T =

I (xozy-y~z,)dA

(6.10)

A

Substitution of Eqs. 6.7 into Eq. 6.10 yields

T = G 8 j ( x 2 + y 2 ) d A = G81r2dA A

(6.1 1)

A

Since the last integral is the polar moment of inertia (J = zb4/2) of the circular cross section, Eq. 6.1 1 yields 8 = -T

(6.12)

GJ

which relates the angular twist 8 per unit length of the shaft to the magnitude T of the applied torque. The factor GJ is the torsional rigidity (or torsional stiffness) of the member. Because compatibility and equilibrium are satisfied, Eqs. 6.7 represent the solution of the elasticity problem. However, in applying torsional loads to most torsion members of circular cross section, the distributions of o,, and oZy on the member ends probably do not satisfy Eqs. 6.7. In these cases, it is assumed that o,,and oZy undergo a redistribution with distance from the ends of the bar until, at a distance of a few bar diameters from the ends, the distributions are essentially given by Eqs. 6.7. This concept of redistribution of the applied end stresses with distance from the ends is known as the Saint-Venant principle (Boresi and Chong, 2000). Since the solution of Eqs. 6.7 indicates that o,, and oZyare independent of z, the stress distribution is the same for all cross sections. Thus, the stress vector T for any point P in a cross section is given by the relation T

= - BGyi + 8Gxj

(6.13)

The stress vector T lies in the plane of the cross section, and it is perpendicular to the radius vector r joining point P to the origin 0. By Eq. 6.13, the magnitude of T is

z = O G t , / m = 8Gr Hence, z is a maximum for r = b; that is, z attains a maximum value of 8Gb.

FIGURE 6.4

Shear stresses (o,,,oJ.

(6.14)

204

CHAPTER6 TORSION

Substitution of Eq. 6.12 into Eq. 6.14 yields the result z= Tr

(6.15)

J

which relates the magnitude z of the shear stress to the magnitude T of the torque. This result holds also for cylindrical bars with hollow circular cross sections (Figure 6.5), with inner radius a and outer radius b; for this cross section J = n(b4- a4)/2and a Ir I b.

6.1.1

Design of Transmission Shafts

Torsional shafts are used frequently to transmit power from a power plant to a machine; an application is noted in Figure 6.6, where an electric motor is used to drive a centrifugal pump. By dynamics, the power P,measured in watts @ d s ] ,transmitted by a shaft is defined by the relation

P =To

(a)

where T is the torque applied to the shaft and w is the angular velocity [rad/s] of the rotating shaft. The frequency [Hz] of rotation of the shaft is denoted by\$ Thus,

w = 2n-f

(b)

Equations (a) and (b) yield

If the power P and frequencyf are specified,Eq.(c) determines the design torque for the shaft. The dimensions of the shaft are dictatedby the mode of failure, the strength of the material associated with the mode of failure, the required factor of safety, and the shaft cross section shape.

0

FIGURE 6.5

Hollow circular cross section.

.. .

Electric motor

& . -

Circular shaft

FIGURE 6.6 Transmission of power through a circular shaft.

,

6.1

EXAMPLE 6.1 Shaft with Hollow Circular Cross Section Solution

TORSION OF A PRISMATIC BAR OF CIRCULAR CROSS SECTION

205

A steel shaft has a hollow circular cross section (see Figure 6.5), with radii a = 22 mm and b = 25 mm. It is subjected to a twisting moment T = 500 N m. (a) Determine the maximum shear stress in the shaft.

(b) Determine the angle of twist per unit length. (a) The polar moment of inertia of the cross section is

J = z(b4 - a4)/2= ~ ( 2 -5Z4)/2 ~ = 245,600 mm4 = 24.56 x

m4

Hence, by Eq. 6.15,

, , ,z

= Tb/J = 500 x 0.025/24.56 x

= 50.9 MPa

(b) By Eq. 6.12, with G = 77 GPa,

8 = T/GJ = 500477 x lo9 x 24.56 x lo-') = 0.0264 rad/m

EXAMPLE 6.2 Circular Cross Section Drive Shaft

Two pulleys, one at B and one at C, are driven by a motor through a stepped drive shaft ABC, as shown in Figure E6.2. Each pulley absorbs a torque of 113 N m. The stepped shaft has two lengths AB = L , = 1 m and BC = L2 = 1.27 m. The shafts are made of steel (Y = 414 MPa, G = 77 GPa). Let the safety factor be SF = 2.0 for yield by the maximum shear-stress criterion. (a) Determine suitable diameter dimensions d, and d2 for the two shaft lengths.

(b) With the diameters selected in part (a), calculate the angle of twist p, of the shaft at C. Pulley

Pulley C

B

A dl

FIGURE E0.2

Solution

Circular cross section shaft.

Since each pulley removes 1 13 N m, shaft AB must transmit a torque T , = 226 N m, and shaft BC must transmit a torque T2 = 113 N m. Also, the maximum permissible shear stress in either shaft = z,/SF = 0.25Y = 103.5 m a . length is (by Eq. 4.12), , ,z (a) By Eq. 6.15, we have, , ,z

3

= 2T/ ( zr,) . Consequently, we have

rl = [2T/(zzmax)]'/3= [2 x 226/(1c x 103.5 x lO6)I1i3= 0.0112 m Hence, the diameter d, = 2rl = 0.0224 m = 22.4 mm. Similarly, we find d2 = 2r2 = 2 X 0.00886 m = 0.0177 m = 17.7 mm. Since these dimensions are not standard sizes, we choose d, = 25.4 rnm and d2 = 19.05 mm, since these sizes (1.0 and 0.75 in., respectively) are available in U.S. customary units. (b) By Eq. 6.12, the unit angle of twist in the shaft 1engthAB is

8 , = T,/(GJI) = 2T,/(Gnr;)

= (2 x 226)/(77 x lo9x 7c ~ 0 . 0 1 2 7 ~=) 0.07183 rad/m

Similarly, we obtain 8, = 0.1135 rad/m. Therefore, the angle of twist at C is

0,

= 1.0 x 0.07183 + 1.27 x 0.1 135 = 0.216 rad = 12.4".

*

206

CHAPTER6 TORSION

EXAMPLE 6.3 Design Torqus for a Hollow Torsion Shah

The torsion member shown in Figure E6.3 is made of an aluminum alloy that has a shear yield strength zy= 190 Mpa and a shear modulus G = 27.0 GPa. The length of the member is L = 2.0 m. The outer diameter of the shaft is Do = 60.0 mm and the inner diameter is Di = 40.0 mm. Two design criteria are specified for the shaft. First, the factor of safety against general yielding must be at least SF = 2.0. Second, the angle of twist must not exceed 0.20 rad. Determine the maximum allowable design torque T for the shaft.

FIGURE E0.3

Solution

(a) Consider first the case of general yielding. P general yielding, the maximum shear stress in the shaft must be equal to the shear yield strength zy= 190 MPa. Hence, by Eq. 6.15, the design torque T is (SF)T =

TYJ -

D0/2

or T = (190 x 106)J (0.060) By Figure E6.3,

or -6

4

J = 1 . 0 2 1 10 ~ m Hence, T = 3.233 kN m

(b) For a limiting angle of twist of y = 8L = 0.20 rad, the design torque is obtained by Eq. 6.12 as

T = GJ8 =

(27 x 109)(1.021x 10-~)(0.20) 2.0

or T = 2.757 kN m Thus, the required design torque is limited by the angle of twist and is T = 2.757 kN m.

6.1

EXAMPLE 6.4 Solid Shaft with Abrupt Change in Cross Section

TORSION OF A PRISMATIC BAR OF CIRCULAR CROSS SECTION

207

The torsion member shown in Figure E 6 . h is made of steel (G = 77.5 GPa) and is subjected to torsional loads as shown. Neglect the effect of stress concentrations at the abrupt change in cross section at section B and assume that the material remains elastic. (a) Determine the maximum shear stress in the member.

(b) Determine the angle of twist ty of sections A, B, and C,relative to the left end 0 of the member.

12.5 kN * m

4kN.m

-

10 kN m

-

1.5 kN m

J

C z

N

(0)

f T - I

12.5 kN m

0

(b) 12.5 kN * m

4kN-m f

(C)

-

12.5 kN m

4kN.m

10 kN * m

(4 FIGURE E6.4

Solution

(a) Note that the member is in torsional equilibrium and that the twisting moment is constant in the segments OA, AB,and BC of the member. The moments in segments UA, AB,and BC are obtained by moment equilibrium with the free-body diagrams shown in Figures E 6 . 4 , c, and d. Thus,

To, = -12.5 kN m T A B = -8.5 kN m T,, = 1 . 5 k N - m Since the magnitude of TOA is larger than that of TAB,the maximum shear stress in the segment OAB occurs in segment OA. Hence, the maximum shear stress in the member occurs either in segment OA or segment BC. In segment OA, by Eq. 6.15,

In length BC, by Eq. 6.15,

208

CHAPTER6 TORSION

Hence, the maximum shear stress in the member is z = 63.66 MPa in segment OA. (b) The angle of twist is given by Eq. 6.12 as

where the positive direction of rotation is shown in Figure E6.k. For section A, Eq. (a) yields yA =

ToALOA = -0.00821 rad GJOA

The negative sign for yAindicates that section A rotates clockwise relative to section 0. For section B, the angle of twist is (C)

WB = WA + WBA where VlgA is the angle of twist of section B relative to sectionA. Thus by Eqs. (a)-(c)

yB

I

(4

Similarly, the angle of twist of section C is Wc = WB+ WCB

(e)

where tycB is the angle of twist of section C relative to sectionB. Thus by Eqs. (a), (d), and (e)

yC = -0.00322rad In summary, the angle of twist at section A is 0.00821 rad clockwise relative to section 0, and the angles of twist at sectionsB and C are 0.01268 rad and 0.00322 rad, both clockwise relative to section 0.

EXAMPLE 6.5 Sha&-Speed Reducer System

A solid shaft is frequently used to transmit power to a speed reducer and then from the speed reducer to other machines. For example, assume that an input power of 100 kW at a frequency of 100 Hz is transmitted by a solid shaft of diameter Dinto a speed reducer. The frequency is reduced to 10 Hz and the output power is transferred to a solid shaft of diameterD,,,. Both input and output shafts are made of a ductile steel (z, = 220 MPa). A safety factor of SF = 2.5 is specified for the design of each shaft. The output power is also 100 kW, since the speed reducer is highly efficient. Determine the diameters of the input and output shafts. Assume that fatigue is negligible.

Solution

Since fatigue is not significant, general yielding is the design failure mode. By the relation among power, frequency, and torque, the input torque Ti, and the output torque Toutare, respectively, T. =

'*

P = 2?rfi,

To, =

P = -

159.2 N m

1592 N m

2 E f out

For a safety factor of 2.5, the diameters Dinand Do,, are given by Eqs. 6.15, (a), and (b) as follows:

zyJout- z ~ ( kD

(SF)Tout= -Rout

t ~ t ) / ~ ~

(Dout/2)

6.2

SAINT-VENANT'S SEMIINVERSE METHOD

209

Therefore.

D, = 20.96mm DOut= 45.17 mm

Note that although the two shafts transmit the same power, the high-speed shaft has a much smaller diameter. So, if weight is to be kept to a minimum, power should be transmitted at the highest possible frequency. Weight can also be reduced by using a hollow shaft.

6.2

SAINT-VENANT'S SEMIINVERSE METHOD The analysis for the torsion of noncircular cross sections proceeds in much the same fashion as for circular cross sections. However, in the case of noncircular cross sections, SaintVenant assumed more generally that w is a function of (x, y), the cross-section coordinates. Then, the cross section does not remain plane but warps; that is, different points in the cross section, in general, undergo different displacements in the z direction. Consider a torsion member with a uniform cross section of general shape as shown in Figure 6.7. Axes (x, y, z) are taken as for the circular cross section (Figure 6.1). The applied shear stress distribution on the ends (ozx,ozr)produces a torque T. In general, any number of stress distributions on the end sections may produce a torque T. According to Saint-Venant's principle, the stress distribution on sections sufficiently far removed from the ends depends principally on the magnitude of T and not on the stress distribution on the ends. Thus, for sufficiently long torsion members, the end stress distribution does not affect the stress distributions in a large part of the member. In Saint-Venant's semiinverse method we start by approximating the displacement components resulting from torque T. This approximation is based on observed geometric changes in the deformed torsion member.

6.2.1

Geometry of Deformation

As with circular cross sections, Saint-Venant assumed that every straight torsion member with constant cross section (relative to axis z) has an axis of twist, about which each cross section rotates approximately as a rigid body. Let the z axis in Figure 6.7 be the axis of twist. For the torsion member in Figure 6.7, let OA and OB be line segments in the cross section for z = 0, which coincide with the x and y axes, respectively. After deformation, by rigid-body displacements, we may translate the new position of 0, that is, 0*, back to

Undeformed end section

P: oi, Y. z)

FIGURE 6.7

Torsion member.

210

CHAPTER6 TORSION

coincide with 0, align the axis of twist along the z axis, and rotate the deformed torsion member until the projection of O*A* on the (x,y ) plane coincides with the x axis. Because of the displacement (wdisplacement) of points in each cross section, O*A* does not, in general, lie in the (x,y) plane. However, the amount of warping is small for small displacements; therefore, line OA and curved line O*A* are shown as coinciding in Figure 6.7. Experimental evidence indicates also that the distortion of each cross section in the z direction is essentially the same. This distortion is known as warping. Furthermore, experimental evidence indicates that the cross-sectional dimensions of the torsion member are not changed significantly by the deformations, particularly for small displacements. In other words, deformation in the plane of the cross section is negligible. Hence, the projection of O*B* on the (x,y) plane coincides approximately with the y axis, indicating that exy (y, = 215~)is approximately zero (see Section 2.7, particularly, Eq. 2.74). Consider a point P with coordinates (x,y, z) in the undeformed torsion member (Figure 6.7). Under deformation, P goes into P*.The point P,in general, is displaced by an amount w parallel to the z axis because of the warping of the cross section and by amounts u and v parallel to the x and y axes, respectively.The cross section in which P lies rotates through an angle p with respect to the cross section at the origin. This rotation is the principal cause of the (u, v) displacements of point P. These observations led Saint-Venant to assume that p = &, where 8 is the angle of twist per unit length, and therefore that the displacement components take the form u = -42

, v=

exz, w =

(6.16)

where y is the warping function (compare Eqs. 6.16 for the general cross section with Eqs. 6.5 for the circular cross section). The function y(x,y) may be determined such that the equations of elasticity are satisfied. Since we have assumed continuous displacement components (u, v, w),the small-displacementcompatibility conditions (Eqs. 2.83) are automatically satisfied. The state of strain at a point in the torsion member is given by substitution of Eqs. 6.16 into Eqs. 2.81 to obtain EXX

-- EYY

=

E,,

=

EXY

=0 (6.17)

2Ezy = yzy = 8 ( \$ + x )

If the equation for yzxis differentiated with respect to y, the equation for y, is differentiated with respect to x, and the second of these resulting equations is subtracted from the first, the warping function y may be eliminated to give the relation (6.18)

If the torsion problem is formulated in terms of (yZx,yzy),Eq. 6.18 is a geometrical condition (compatibility condition) to be satisfied for the torsion problem.

6.2.2 Stresses at a Point and Equations of Equilibrium For torsion members made of isotropic materials, stress-strain relations for either elastic (the fist of Eqs. 6.17 and Eqs. 3.32) or inelastic conditions indicate that

6.2

oxx= ayy-

SAINT-VENANT'S SEMIINVERSEMETHOD

o,, = oxy= 0

2 11

(6.19)

The stress components (oZx, a?) are nonzero. if body forces and acceleration terms are neglected, these stress components may be substituted into Eqs. 2.45 to obtain equations of equilibrium for the torsion member:

(6.20) (6.21) (6.22) Equations 6.20 and 6.21 indicate that o,,= oxzand oq = oyzare independent of z. These stress components must satisfy Q. 6.22, which expresses a necessary and sufficient condition for the existence of a stress function \$(x, y ) (the so-calledPmndtl stress function) such that

- JCp

- -& ozy- -JCp ozx

(6.23)

f3X

Thus, the torsion problem is transformed into the determination of the stress function Cp. Boundary conditions put restrictions on Cp.

6.2.3

Boundary Conditions

Because the lateral surface of a torsion member is free of applied stress, the resultant shear stress zon the surface S of the cross section must be directed tangent to the surface (Figures 6 . 8 and ~ b). The two shear stress components ozxand ozrthat act on the cross-sectional element with sides dx,dy, and ds may be written in terms of T (Figure 6.8b) in the form ozx= z s i n a

(6.24)

ozy= z c o s a where, according to Figure 6.8u, s in a = dx -

ds'

c o s a = dY -

(6.25)

ds

Since the component of T in the direction of the normal n to the surface S is zero, projections of czx and czy in the normal direction (Figure 6.M) yield, with Q. 6.25, oZxcosa- o,,sina

= 0

(6.26)

'This approach was taken by Randtl. See Section 7.3 of Boresi and Chong (2000).

212

CHAPTER6 lORSION

/

I

R

\ X

(b)

FIGURE 6.8 Cross section of a torsion member.

Substituting Eqs. 6.23 into Eq. 6.26, we find

or @ = constant on the boundary S

(6.27)

Since the stresses are given by partial derivatives of @ (see Eqs. 6.23), it is permissible to take this constant to be zero; thus, we select @ = 0 on the boundary S

(6.28)

The preceding argument can be used to show that the shear stress (6.29)

at any point in the cross section is directed tangent to the contour @ = constant through the point. The distributions of o,,and ozyon a given cross section must satisfy the following equations:

C F x = 0 = jozxdxdy = j\$dxdy

(6.30)

C F y = 0 = jozydxdy = - j g d x d y

(6.31)

E M Z= T =

~ ( X O ~ ~ - ~dxdy O , , )

(6.32)

In satisfying the second equilibrium equation, consider the strip across the cross section of thickness dy as indicated in Figure 6 . 8 ~Because . the stress function does not vary in the y direction for this strip, the partial derivative can be replaced by the total derivative. For the strip, Eq. 6.31 becomes

6.3

LINEAR ELASTIC SOLUTION

2 13

(6.33) = dY[W)-\$(A)I = 0

since \$ is equal to zero on the boundary. The same is true for every strip so that satisfied. In a similar manner, Eq. 6.30 is verified. In Eq. 6.32, consider the term

Fy = 0 is

which for the strip in Figure 6 . 8 becomes ~

(6.34) Evaluating the latter integral by parts and noting that \$(B) = \$(A) = 0, we obtain

I xd\$

\$(B)

-dy

(6.35)

= -dy

\$(A)

xA

)

xA

Summing for the other strips and repeating the process using strips of thickness du for the other term in Eq. 6.32, we obtain the relation T = 2

[email protected] d x d y

(6.36)

The stress function \$ can be considered to represent a surface over the cross section of the torsion member. This surface is in contact with the boundary of the cross section (see Eq. 6.28). Hence, Eq. 6.36 indicates that the torque is equal to twice the volume between the stress function and the plane of the cross section.

Note: Equations 6.18, 6.23, 6.28, and 6.36, as well as other equations in this section, have been derived for torsion members that have uniform cross sections that do not vary with z, that have simply connected cross sections, that are made of isotropic materials, and that are loaded so that deformations are small. These equations are used to obtain solutions for torsion members; they do not depend on any assumption regarding material behavior except that the material is isotropic; therefore, they are valid for any specified material response (elastic or inelastic). Two types of typical material response are considered in this chapter: linearly elastic response and elastic-perfectly plastic response (Figure 4.4~). The linearly elastic response leads to the linearly elastic solution of torsion, whereas the elastic-perfectly plastic response leads to the fully plastic solution of torsion of a bar for which the entire cross section yields. The material properties associated with various material responses are determined by appropriate tests. Usually, as noted in Chapter 4, we assume that the material properties are determined by either a tension test or torsion test of a cylinder with thin-wall annular cross section.

6.3 LINEAR ELASTIC SOLUTION Stress-strain relations for linear elastic behavior of an isotropic material are given by Hooke's law (see Eqs. 3.32). By Eqs. 3.32 and 6.23, we obtain

214

CHAPTER6 TORSION

(6.37)

Substitution of Eqs. 6.37 into Eq. 6.18 yields (6.38) If the unit angle of twist 6 is specified for a given torsion member and @ satisfies the boundary condition indicated by Eq. 6.28, then Eq. 6.38 uniquely determines the stress function @(x,y ) . Once @hasbeen determined, the stresses are given by Eqs. 6.23 and the torque is given by Eq. 6.36. The elasticity solution of the torsion problem for many practical cross sections requires special methods (Boresi and Chong, 2000) for determining the function @ and is beyond the scope of this book. As indicated in the following paragraphs, an indirect method may be used to obtain solutions for certain types of cross sections, although it is not a general method. Let the boundary of the cross section for a given torsion member be specified by the relation F(x,y) = 0

(6.39)

Furthermore, let the torsion member be subjected to a specified unit angle of twist and define the stress function by the relation

@ = BF(x,y)

(6.40)

where B is a constant. This stress function is a solution of the torsion problem, provided F(x, y) = 0 on the lateral surface of the bar and d2F/dx2+ d 2 F / d y 2= constant

Then, the constant B may be determined by substitutingEq. 6.40 into Eq. 6.38. With B determined, the stress function @ for the torsion member is uniquely defined by Eq. 6.40. This indirect approach may, for example, be used to obtain the solutions for torsion members whose cross sections are in the form of a circle, an ellipse, or an equilateral triangle.

6.3.1

Elliptical Cross Section

Let the cross section of a torsion member be bounded by an ellipse (Figure 6.9). The stress function @ for the elliptical cross section may be written in the form (6.41) since F(x, y ) = x2/h2 + y 2 / b 2- 1 = 0 on the boundary (Eq.6.39). Substituting Eq. 6.41 into Eq. 6.38, we obtain B = --h2b2GB h2 + b2

(6.42)

in terms of the geometricalparameters (h, b), shear modulus G , and unit angle of twist 6. With @ determined, the shear stress components for the elliptical cross section are, by Eqs. 6.23,

6.3 LINEAR ELASTIC SOLUTION

2 15

FIGURE 6.9 Ellipse.

(6.43)

(6.44)

The maximum shear stress ,T section. Its value is

occurs at the boundary nearest the centroid of the cross

(6.45)

The torque T for the elliptical cross section torsion member is obtained by substituting Eq. 6.41 into Eq. 6.36. Thus, we obtain T = -2B j x 2dA + T2Bj y 2 dA - 2BjdA = ?!!I h2

+2

h2

b

I - 2BA

b2

Determination of I,, Iy and A in terms of (b,h) allows us to write T = -nBhb

The torque may be expressed either in terms of ,T 6.46. Thus. ‘max

- 2T

-zbh2’

(6.46)

or 8 by means of Eqs. 6.42,6.45, and

e = T ( b 2+ h 2 )

(6.47)

Gnb3h3

where Gnb3h3/(b2+ h2)= GJ is called the torsional rigidity (stiffness) of the section and the torsional constant for the cross section is J = nb3h3/(b2+ h2)

6.3.2 Equilateral Triangle Cross Section Let the boundary of a torsion member be an equilateral triangle (Figure 6.10). The stress function is given by the relation

(;; x-

4=

A f

3y-2h)(x+fiy-2h)(x+;) 3 3

(6.48)

216

CHAPTER6 TORSION

FIGURE 6.10

Equilateral triangle.

Proceeding as for the elliptical cross section, we find

- 15&T , 0 = -15&T - -

(6.49) 2h3 Gh4 where Gh4/ 15 & = GJ is called the torsional rigidity of the section. Hence, the torsional constant for the cross section is %lax

J = h4/(15&)

6.3.3 Other Cross Sections There are many torsion members whose cross sections are so complex that exact analytical solutions are difficult to obtain. However, approximate solutions may be obtained by Prandtl’s membrane analogy (see Section 6.4). An important class of torsion members includes those with thin walls. Included in the class of thin-walled torsion members are open and box-sections. Approximate solutions for these types of section are obtained in Sections 6.5 and 6.7 by means of the Prandtl membrane analogy.

6.4 THE PRANDTL ELASTIC-MEMBRANE (SOAP-FILM) ANALOGY In this section, we consider a solution of the torsion problem by means of an analogy proposed by Prandtl (1903). The method is based on the similarity of the equilibrium equation for a membrane subjected to lateral pressure and the torsion (stress function) equation (Eq.6.38). Although this method is of historical interest, it is rarely used today to obtain quantitative results. It is discussed here primarily from a heuristic viewpoint, in that it is useful in the visualization of the distribution of shear-stress components in the cross section of a torsion member. To set the stage for our discussion, consider an opening in the (x, y) plane that has the same shape as the cross section of the torsion bar to be investigated. Cover the opening with a homogeneous elastic membrane, such as a soap film,and apply pressure to one side of the membrane. The pressure causes the membrane to bulge out of the (x, y) plane, forming a curved surface. If the pressure is small, the slope of the membrane will also be small. Then, the lateral displacement z(x, y) of the membrane and the Prandtl torsion stress function \$(x, y) satisfy the same equation in (x, y). Hence, the displacement z(x, y) of the membrane is mathematically equivalent to the stress function \$(x, y ) , provided that z(x, y) and

6.4

THE PRANDTL ELASTIC-MEMBRANE (SOAP-FILM) ANALOGY

2 17

@(x,y ) satisfy the same boundary conditions. This condition requires the boundary shape of the membrane to be identical to the boundary shape of the cross section of the torsion member. In the following discussion, we outline the physical and mathematical procedures that lead to a complete analogy between the membrane problem and the torsion problem. As already noted, the Prandtl membrane analogy is based on the equivalence of the torsion equation (Eq. 6.38 is repeated here for convenience)

(6.50)

and the elastic membrane equation (to be derived in the next paragraph)

-d2z + + - d2z -- - p dx2

dy2

S

where z denotes the lateral displacement of an elastic membrane subjected to a lateral pressure p in terms of force per unit area and an initial (large) tension S (Figure 6.1 1) in terms of force per unit length. For the derivation of the elastic membrane equation, consider an element ABCD of dimensions dx, dy of the elastic membrane shown in Figure 6.11. The net vertical force resulting from the tension S acting along edge AD of the membrane is (if we assume small displacements so that sin a = tan a ) -Sdysina=-Sdytana

= -Sdy-

m

ax

and, similarly, the net vertical force resulting from the tension S (assumed to remain constant for sufficiently small values of p) acting along edge BC is

Similarly,for edgesAB and DC, we obtain

view

FIGURE 6.1 1 Deformation of a pressurized elastic membrane.

218

CHAPTER6 TORSION

Consequently,the summation of force in the vertical direction yields for the equilibrium of the membrane element du dy d2Z

d2Z

dx2

?Y2

S-dxdy+S-dxdy+pdxdy

or

-d2z + + -d2z -- - p dx2

(6.51)

ay2

By comparison of Eqs. 6.50 and 6.5 1, we arrive at the following analogous quantities: z = [email protected], E=c2GO S

(6.52)

where c is a constant of proportionality.Hence, z

-

@

p/s - 2G8’

f\$=- 2G8SZ

(6.53)

P

Accordingly,the membrane displacement z is proportional to the Prandtl stress function @, and since the shear-stress components o,, oq are equal to the appropriate derivatives of @ with respect to x and y (see Eqs. 6.23), it follows that the stress components are proportional to the derivativesof the membrane displacement z with respect to the (x,y ) coordinates (Figure 6.1 1). In other words, the stress components at a point (x, y ) of the bar are proportional to the slopes of the membrane at the corresponding point (x,y ) of the membrane. Consequently,the distribution of shear-stress components in the cross section of the bar is easily visualized by forming a mental image of the slope of the corresponding membrane. Furthermore, for simply connected cross sections? since z is proportional to @. by Eqs. 6.36 and 6.53, we note that the twisting moment T is proportional to the volume enclosed by the membrane and the (x,y ) plane (Figure 6.1 1). For multiply connected cross section, additional conditions arise (Section 6.6; see also Boresi and Chong, 2000). An important aspect of the elastic membrane analogy is that valuable deductions can be made by merely visualizing the shape that the membrane must take. For example, if a membrane covers holes machined in a flat plate, the corresponding torsion members have equal values of GO; therefore, the stiffnesses (see Eqs. 6.47 and 6.49) of torsion members made of materials having the same G are proportional to the volumes between the membranes and flat plate. For cross sections with equal area, one can deduce that a long narrow rectangular section has the least stiffness and a circular section has the greatest stiffness. Important conclusions may also be drawn with regard to the magnitude of the shear stress and hence to the cross section for minimum shear stress. Consider the angle section shown in Figure 6.12~2.At the external comers A, B , C , E, and F, the membrane has zero slope and the shear stress is zero; therefore, external comers do not constitute a design problem. However, at the reentrant comer at D (shown as a right angle in Figure 6.12a), the corresponding membrane would have an infinite slope, which indicates an infinite *A region R is simply connected if every closed curve within it or on its boundary encloses only points in R. For ~ R ) is simply connected (as are all the cross sections in example, the solid cross section in Figure 6 . 8 (region Section 6.3),since any closed curve in R or on its boundary contains only points in R . However, a region R between two concentric circles is not simply connected (see Figure 6.5),since its inner boundary r = a encloses points not in R. A region or cross section that is not simply connected is called multiply cmnected.

6.5

(a)

FIGURE 6.12

NARROW RECTANGULAR CROSS SECTION

(b)

2 19

(C)

Angle sections of a torsion member. (a) Poor. (b) Better. (c) Best.

shear stress in the torsion member. In practical problems, the magnitude of the shear stress at D would be finite but very large compared to that at other points in the cross section.

6.4.1

Remark on Reentrant Corners

If a torsion member with cross section shown in Figure 6 . 1 2 ~ is made of a ductile material and it is subjected to static loads, the material in the neighborhood of D yields and the load is redistributed to adjacent material, so that the stress concentration at point D is not particularly important. If, however, the material is brittle or the torsion member is subjected to fatigue loading, the shear stress at D limits the load-carrying capacity of the member. In such a case, the maximum shear stress in the torsion member may be reduced by removing some material as shown in Figure 6.12b. Preferably, the member should be redesigned to alter the cross section (Figure 6.12~). The maximum shear stress would then be about the same for the two cross sections shown in Figures 6.12b and 6.12~for a given unit angle of twist; however, a torsion member with the cross section shown in Figure 6.12~would be stiffer for a given unit angle of twist.

6.5

NARROW RECTANGULAR CROSS SECTION The cross sections of many members of machines and structures are made up of narrow rectangular parts. These members are used mainly to carry tension, compression, and bending loads. However, they may be required also to carry secondary torsional loads. For simplicity, we use the elastic membrane analogy to obtain the solution of a torsion member whose cross section is in the shape of a narrow rectangle. Consider a bar subjected to torsion. Let the cross section of the bar be a solid rectangle with width 2h and depth 2b, where b >> h (Figure 6.13). The associated membrane is shown in Figure 6.14. Except for the region near x = +b, the membrane deflection is approximately independent of x. Hence, if we assume that the membrane deflection is independent of x and parabolic with respect to y, the displacement equation of the membrane is z =

1

-(\$I

(6.54)

where zo is the maximum deflection of the membrane. Note that Eq. 6.54 satisfies the condition z = 0 on the boundaries y = +h. Also, if p / S is a constant in Eq. 6.51, the parameter z o may be selected so that Eq. 6.54 represents a solution of Eq. 6.51. Consequently, Eq. 6.54 is an approximate solution of the membrane displacement. By Eq. 6.54 we find

220

CHAPTER6 TORSION

FIGURE 6.13 Narrow rectangular torsion member. Y

FIGURE 6.14

Membrane for narrow rectangular cross section.

d2z -+-d2z = - 220

dx2 dy2

(6.55)

h2

By Eqs. 6.55,6.51, and 6.52, we may write -2z01h2 = -2cG8 and Eq. 6.54 becomes

4

= G0h2[1 -

(\$1

(6.56)

Consequently,Eqs. 6.23 yield

(6.57) and we note that the maximum value of o,,is

zmax= 2G0h, fory = +h

(6.58)

Equations 6.36 and 6.56 yield b h

T = 21

1\$ dx dy = 3-1G 0 ( 2 b ) ( 2 h ) 3

= GJ8

(6.59)

-b-h

where

is the torsional constant and GJ is the torsional rigidity. Note that the torsional constant J is small compared to the polar moment of inertia Jo = [ ( 2 b ) ~ h+)(2h)(2b)3]/12; ~ see Table B.l.

6.5

NARROW RECTANGULARCROSS SECTION

22 1

In summary, we note that the solution is approximate and, in particular, the boundary condition for x = -+bis not satisfied. From Eqs. 6.58 and 6.59 we obtain

(6.61)

6.5.1 Cross Sections Made Up of Long Narrow Rectangles Many rolled composite sections are made up of joined long narrow rectangles. For these cross sections, it is convenient to define the torsional constant J by the relation n

(6.62) where C is a correction coefficient. If bi > 10hi for each rectangular part of the composite cross section (see Table 6.1 in Section 6.6), then C = 1 . For many rolled sections, bi may be less than lOhi for one or more of the rectangles making up the cross section. In this case, it is recommended that C = 0.91.When n = 1 and b > 10h, C = 1 and Eq. 6.62 is identical to Eq. 6.60. For n > 1 , Eqs. 6.61 take the form

(6.63) where h,, is the maximum value of the hi. Cross-sectional properties for typical torsion members are given in the manual published by the American Institute of Steel Construction, Inc. (AISC, 1997). The formulas for narrow rectangular cross sections may also be used to approximate narrow curved members. See Example 6.6.

EXAMPLE 6.6 Torsion of a

Consider a torsion member of narrow semicircular cross section (Figure E6.6), with constant thickness 2h and mean radius a. The mean circumference is 2b = nu. We consider the member to be equivalent to a slender rectangularmember of dimension 2 h x aa. Then, for a twisting moment T applied to the member, by Eqs. 6.61, we approximate the maximum shear stress and angle of twist per unit length as follows:

Member with Narrow Semicircular Cross Section

Zmax

I

-

= 2Th J ’

3

Hence,

zmax=- 3T 4zah2

and Q = - =TGJ

Alternatively, we may express 8 in terms of, , ,z

I

aa J = -(2h) 3

FIGURE E6.6

3T 8aGah3

as 8 = zm,/2Gh.

222

CHAPTER6 TORSION

6.6 TORSION OF RECTANGULAR CROSS SECTION MEMBERS In Section 6.5 the problem of a torsion bar with narrow rectangular cross section was approximated by noting the deflection of the corresponding membrane. In this section we again consider the rectangular section of width 2h and depth 2b, but we discard the restriction that h , = 570 x lo3 mm4, I , = -332.5 x lo3 mm4, and A =

292

CHAPTER 7 BENDING OF STRAIGHT BEAMS

and R , all lie in a plane that forms an angle of 20" counterclockwise from the y axis. Determine the point in the beam at which the maximum tensile flexural stress acts and the magnitude of that stress.

P I

P = 3.00 kN

I

Rl

R2

FIGURE P7.33 FIGURE P7.30

7.34. A beam has a square cross section (Figure P7.34). a. Determine an expression for om, in terms of M,h, and y. b. Compare values of om, for y = 0, 15, and 45".

Plane of the loads

63.5 mm

Y A

Y1

1

FIGURE P7.34

Y2

FIGURE P7.31

1148 mm2) by means of a 76 mm by 6 mm plate riveted to the angle (Figure P7.32). The action line of load P coincides with the centroidal axis of the plate. Determine the maximum stress at a section, such as AA, of the angle. Hint:Resolve the load P into a load (equal to P) at the centroid of the angle and a bending couple.

7.35. Consider the beam shown in Figure p7.35. a. Derive an expression for omax in terms of M,h, and y. b. Compare values of omax for y = 0,30,45,60, and 90".

Plane of the load

~~m 22.1 mm

FIGURE P7.35

A1

Y

FIGURE P7.32

7.36. An I-beam has the cross section shown in Figure P7.36. The design flexural stress is limited to 120 m a . Determine the allowable bending moment M.

7.37. A T-beam has the cross section shown in Figure P7.37. 7.33. The beam shown in Figure P7.33 has a cross section of depth 60 mm and width 30 mm. The load P and reactions R 1

The design flexural stress is limited to 150 m a . Determine the allowable bending moment M.

PROBLEMS

7.39. A circular cross section shaft is mounted in bearings that develop shear reactions only (Figure P7.39). Determine the location and magnitude of the maximum flexural stress in the beam.

pl00 m m y

x

*h

= 20"

-

f

100 J jmm m

293

m

Y

FIGURE P7.36

200 mm

FIGURE P7.39 Y

FIGURE P7.37

7.40. A wood beam of rectangular cross section 200 mm by 100 mm is simply supported at its ends (Figure P7.40). Determine the location and magnitude of the maximum flexural stress in the beam.

7.38. A beam has an isosceles triangular cross section (Figure P7.38). The maximum flexural stress is limited to 90 MPa. Determine the magnitude of the allowable bending moment M.

FIGURE P7.38 FIGURE P7.40

Section 7.3 7.41. Determine the deflection of the beam in Problem 7.18. E = 12.0 GPa for the yellow pine. 7.42. The beam in Problem 7.20 is made of 7075-T6 aluminum alloy for which E = 71.7 GPa. Determine the deflection of the free end of the beam. 7.43. The beam in Problem 7.21 is made of 7075-T6 aluminum alloy for which E = 71.7 GPa. Determine the deflection of the free end of the beam. 7.44. The beam in Problem 7.23 is made of yellow pine for which E = 12.0 GPa. Determine the deflection at the center of the beam. 7.45. Determine the deflection of the center of the beam in Problem 7.25. E = 200 GPa.

7.46. The beam in Problem 7.26 is subjected to a distributed load of w = 6.5 kN/m. Determine the deflection at the center of the beam. E = 200 GPa. 7.47. Determine the deflection of the beam in Problem 7.27. E = 200 GPa. 7.48. Determine the deflection of the free end of the beam in Problem 7.28. E = 72.0 GPa. 7.49. Determine the deflection of the midspan of the beam in Problem 7.29. E = 72.0 GPa. 7.50. Determine the deflection of the free end of the beam in Problem 7.30. E = 200 GPa. 7.51. Determine the deflection at midspan of the beam of Problem 7.33. E = 200 GPa.

294

CHAPTER 7 BENDING OF STRAIGHT BEAMS

7.52. A cantilever beam of length L has the cross section shown in Figure P7.34 and is subjected to moment M at its free end. Determine the deflection of the free end in terms of E, L, M, y, and h. Consider only the case for which 0 Iy I 90".

7.53. A structural steel cantilever beam (E = 200 GPa) of length L = 3.0 m has the cross section shown in Figure W.36 and is subjected to a moment M = 5 kN m at its free end. Determine the deflection of the free end.

Section 7.5 7.54. The cantilever beam in Problem 7.28 is made of a lowcarbon steel that has a yield stress Y = 200 MPa.

b. Determine the fully plastic load Pp for the beam for the condition that a = a/6.

a. Determine the fully plastic load Pp for the beam for the condition that a = 0.

7.55. The cantilever beam in Problem 7.30 is made of a mild steel that has a yield stress Y = 240 MPa. Determine the fully plastic load P , for the condition that a = 0.

REFERENCE BORESI,A. P., and CHONG,K . P. (2000). Elasticity in Engineering Mechanics, 2nd ed. New York: Wiley-Interscience.

CHAPTER

8

SHEAR CENTER FOR THIN-WML BEAM CROSS SECTIONS n H

s defined in Chapter 7, the shear center is a point in the cross section of a

beam through which the plane of loads must pass for the beam to be subjected to only bending and shear. No torsion is caused by transverse loads that act through the shear center. Locating the shear center for a beam cross section is a necessary step in the analysis of beam under loads that cause bending, shear, and possibly torsion. For a general cross section, the theory of elasticity may be used to locate the shear center (Boresi and Chong, 2000). However, in this chapter we use the methods of mechanics of materials to develop an approximate solution for the location of the shear center for thin-wall beam cross sections.

8. I APPROXIMATIONS FOR SHEAR IN THIN-WALL BEAM CROSS SECTIONS For a beam with a cross section that possess two or more axes of symmetry or antisymmetry, the bending axis is the same as the longitudinal centroidal axis, because for each cross section the shear center and centroid coincide. However, for cross sections with only one axis of symmetry,the shear center and centroid do not coincide, but both lie on the symmetry axis. For example, consider the equal-leg angle section shown in Figure 8.1. Let the beam cross section be oriented so that the principal axes of inertia (X, Y) are directed horizontally and vertically.When the load P is applied at the centroid 0 of the cross section, the beam bends and twists (Figure 8 . 1 ~ ~However, ). the beam bends without twist if it is loaded by a force P that passes through the shear center C (Figure 8.lb). As is shown later, the shear center C coincides approximatelywith the intersection of the center lines of the two legs of the angle section. To locate the shear center for a thin-wall cross section, we first make simplifying assumptions. They may be illustrated by reference to Figure 8.2. In Figure 8.2, the cross section shown is that of the beam in Figure 8.lb and is obtained by passing a cutting plane perpendicular to the bending axis through the beam. The view shown is obtained by looking from the support toward the end of the beam at which P is applied. For equilibrium of the beam element so obtained, the shear stresses on the cut cross section must balance the load P. However, the shear stresses in the cross section are difficult to compute exactly. Hence, simplifying approximations are employed. Accordingly, consider a portion of the legs of the cross section, shown enlarged in Figure 8.2b. Let axes x-y-z be chosen so that the x-y axes are tangent and normal, respectively,to the upper leg, and let the z axis be taken perpendicular to the cross section (the plane of Figure 8.2b) and directed positively along the axis of the beam from the load P to the support. Then, the shear stress 295

296

CHAPTER 8 SHEAR CENTER FOR THIN-WALL BEAM CROSS SECTIONS

P

P (b)

(a)

FIGURE 8.1 Effect of applying load through shear center. ( a )Load P applied at point 0 produces twist and bending. ( b ) Load P applied at point Cproduces bending only.

(b)

(0)

FIGURE 8.2

Shear stress distribution in an equal-leg angle section.

components in the cross section of the beam are o, and oq as shown. Since the shear = 0. Hence, oq vanishes at BD and stresses on the lateral surfaces of the beam are zero, oyz EF (since oyz = oq;see Eq. 2.4). Since ozy = 0 at BD and EF and the wall thickness between BD and EF is small (a thin wall) with respect to the length of the legs of the cross section, we assume that oq does not change significantly (remains approximately zero) through the wall. The effect of o (the shear stress in the thickness direction) is ignored in the following dis'y cussion. In addition, it is assumed that the shear stress component o, (along the legs) is approximately constant through the wall thickness and is equal to the average tangential . these approximations for oq and ,a , we find shear stress z in the wall (Figure 8 . 2 ~ )With that a reasonably accurate and simple estimate of the shear center location may be obtained.

8.2 SHEAR FLOW IN THIN-WALL BEAM CROSS SECTIONS The average shear stress z at each point in the walls of the beam cross section is assumed to have a direction tangent to the wall. The product of this shear stress and the wall thickness t defines the shearpow q; thus, q = zt

(8.1)

8.2

SHEAR FLOW IN THIN-WALL BEAM CROSS SECTIONS

297

In the equation that will be derived for determining the shear flow q, we assume that the beam material remains linearly elastic and that the flexure formula is valid. Hence, we assume that the plane of the loads contains the bending axis of the beam and is parallel to one of the principal axes of inertia. It is convenient to consider a beam cross section that has one axis of symmetry (the x axis in Figure 8.3). If the load P is parallel to the y axis and passes through the shear center C”, the x axis is the neutral axis for linearly elastic behavior and the flexure formula is valid. The derivation of the formula for q requires that both the bending moment M, and total shear Vybe defined; load P is taken in the negative y direction so that both M, and Vyare positive. We wish to determine the shear flow q at point J in the cross section of the beam in Figure 8.3a at a distance z + dz from load P. The free-body diagram necessary to determine q is obtained by three cutting planes. Cutting planes 1 and 2 are perpendicular to the z axis at distances z and z + dz from the load I? Cutting plane 3 is parallel to the z axis and perpendicular to the lateral surface of the beam at J. The free body removed by the three cutting planes is indicated in Figure 8.3b. The normal stress o,,as given by the flexure formula acts on the faces made by cutting planes 1 and 2. The resulting forces on these faces of area A’ are parallel to the z axis and are indicated in Figure 8.3b as H and H’, respectively. Since the forces H and H‘ are unequal in magnitude, equilibrium of forces in the z direction is maintained by the force q dz on the face made by cutting plane 3. Therefore, q d z = H’-H

(8.2)

Now, integration of o,,over the faces with area A‘ at sections 1 and 2 yields (with the flexure formula)

H = I o z z d A = j%dA A’

A’

‘X

and

FIGURE 8.3 Shear flow in a beam having a symmetrical cross section.

298

CHAPTER 8 SHEAR CENTER FOR THIN-WALL BEAM CROSS SECTIONS

Substituting these two relations into Eq. 8.2 and solving for q yields

q = d- M - j, y 1d A dz I X A ‘ According to beam theory, the total shear Vyin the cross section of a beam is given by Vy= dM,/dz.

Also, since

Y dA =

where 7’ is the distance from the x axis to the centroid of A’,

A’

we may express q as

Vy A’Y’

q = -

I, Furthermore, since the value of the shear stress z in the longitudinal section cut by plane 3 (Figure 8.3) is the same as the shear stress in the cross section cut by plane 2, the shear flow in the cross section at point J is

where t is the wall thickness at point J. The first moment of area A’, that is, A’Y: is commonly denoted by Q. Equation 8.3 is used to locate the shear center of thin-wall beam cross sections for both symmetrical and nonsymmetrical bending. The method is demonstrated in Section 8.3 for beam cross sections made up of moderately thin walls. In many applications (e.g.. girders), the beam cross sections are built up by joining stiff longitudinal stringers by thin webs. The webs are generally stiffened at several locations along the length of the beam. The shear center location for beams of this type is considered in Section 8.4.

8.3 SHEAR CENTER FOR A CHANNEL SECTION A cantilever beam subjected to a bending load V at C’ in a plane perpendicular to the axis x of symmetry of the beam is shown in Figure 8.4. We wish to locate the plane of the load

so that the channel bends without twisting. In other words, we wish to locate the bending axis CC‘ of the beam or the shear center C of any cross section AB. In Figure 8.4a let V be transformed into a force and couple at sectionAB by introducing, at the shear center C whose location is as yet unknown, two equal and opposite forces V’ and V”, each equal in magnitude to V The forces V and V” constitute the external bending couple at section AB, which is held in equilibrium by the internal resisting moment at section AB in accordance with the flexure formula, Eq. 7.1; the distribution of the normal stress 0, on section AB is shown in Figure 8.4a. The force V’ is located at a distance e from the center of the web of the channel, as indicated in Figures 8.4a and 8.4b. Force V’ is resisted by shear stress z or shear flow q (Eq. 8.3) in cross section AB. Since the shear flow is directed along the straight sides of the channel, it produces forces F , , F,, and F,, which lie in the cross section as indicated in Figure 8.4b. Accordingly, by equilibrium

CF, = F , - F l CFy

= 0

= V‘-F, = 0

X M A = V’e-Flh = 0

(8.6)

8.3

SHEAR CENTER FOR A CHANNEL SECTION

299

Fixed end of cantilever beam

FIGURE 8.4 Shear center for a channel section. ( a )Channel section beam. ( b ) Location of C. (c) Idealized areas.

The magnitude of the load V' is assumed to be known. Therefore, the determination of the distance e from the center line of the web to the shear center requires only that the force Fl (= F2) be determined. To determine F,, it is convenient to think of the beam cross section as made up of line segments (Figure 8.4~)with specified thicknesses. Since the forces F , , F2, F3 are assumed to lie along the center line of the walls, the cross section is idealized as three narrow rectangles of lengths b, h, and b as indicated in Figure 8.4~;note that the actual and idealized cross-sectional areas are equal since the three areas overlap. However, the moments of inertia of the actual and idealized cross sections differ from each other slightly. The moment of inertia of the idealized area is

I , = -twh 1 12

3 + 2 b t f ( g )2 +2-btf 1 3

12

This result may be simplified further by neglecting the third term, since for the usual channel section tf is small compared to b or h. Thus, we write 1

I , = -twh 12

3

+ -21 tf bh2

(8.7)

The force Fl may be found from the shear flow equation

5

b V b V t h b F, = fqdl = f A'T'dl = yf Id1 = 0 X O 21, 0

Vy t f b2h 41,

where q is given by Eq. 8.3. The distance e to the shear center of the channel section is determined by substituting Eqs. 8.7 and 8.8 into Eq. 8.6 with the magnitude of V' set equal to that of V y .Thus, we find

e =

b 1 twh 2+-3 tfb

(8.9)

300

CHAPTER 8 SHEAR CENTER FOR THIN-WALL BEAM CROSS SECTIONS

Because of the assumptions employed and approximations used, Eq. 8.9 gives only an approximate location of the shear center for channel sections. However, the error is small for thin-wall sections. The approximate locations of the shear center for several other thin-wall sections with an axis of symmetry are given in Table 8.1. TABLE 8.1 Locations of Shear Centers for Sections Having One Axis of Symmetry

-

b t

Figure A

tt

-[

b

h 26, 2b, 2 + 3b -+ b 1 -

Figure B

+

;;z)

4b:

1 - , b: e- -b

bL 2b, twh' 2+-+b 3t,b

bl b, A, = 2 a 8 - 2 b ~ i n 8 - n + , / ~ ~ + 2 + , / ~ ~ s i n - ' ( b + ~ ~ ~ ~ ~ ) a + bcos 8

Forb>a, A, = 2a8-2bsin8+ 2 + , / m l n (

A = b2 8--sin2B; b2 2

R = a-

a + bcos8

4bsin38 3(28- sin28)

A, = 2a 8 + 26 sin 8 - n d m - 2 + , / n s i d 1 ( b a - bcos 8

")

curved beam is composed of two or more of the fundamental areas listed in Table 9.2. The values of A, A,, and R for the composite area are given by summation. Thus, for composite cross sections, n

A = x A i

(9.12)

i= 1 n

(9.13) i= 1

326

CHAPTER 9 CURVED BEAMS

(9.14)

where n is the number of fundamental areas that form the composite area.

9.2.1

Location of Neutral Axis of Cross Section

The neutral axis of bending of the cross section is defined by the condition Oe, = 0. The neutral axis is located at distance R, from the center of curvature. The distance R , is obtained from Eq. 9.1 1 with the condition that Oge = 0 on the neutral surface I = R,. Thus, Eq. 9.11 yields

R, =

AM,

A,M,

+ N ( A - RA,)

(9.15)

For pure bending, N = 0, and then Eq. 9.15 yields R, =

A -

(9.16)

Am

EXAMPLE 9.1 Stress in Curved Beam Portion ot a Frame

The frame shown in Figure E9.1 has a 50 mm by 50 mm square cross section. The load P is located 100 mm from the center of curvature of the curved beam portion of the frame. The radius of curvature of the inner surface of the curved beam is a = 30 mm. For P = 9.50 kN, determine the values for the maximum tensile and compressive stresses in the frame.

FIGURE E9.1

Solution

The circumferential stresses cooare calculated using Eq. 9.1 1. Required values for A , A,,,, and R for the curved beam are calculated using the equations in row (a)of Table 9.2. For the curved beam a = 30 mm and c = 80 mm. Therefore, A = b ( c - a ) = 50(80-30) = 2500mm' C 80 A , = bln - = 50 In- = 49.04 U 30

Hence, the maximum tensile stress is (at point B) GgeB =

+ 155(9500)[2500- 30(49.04)] PA + MA rx (( AR-Ar A, -mA) ) - -9500 2500 2500(30)[55(49.04)-25001

= 106.2 MPa

9.2

CIRCUMFERENTIAL STRESSES IN A CURVED BEAM

327

The maximum compressive stress is (at point C) 9500

oeec =

EXAMPLE 9.2 Semicircular Aircraft Beam

2500

+

155(9500)[2500-80(49.04)]

= -49.3

2500(80)[55(49.04) -25001

In a test of a semicircular aircraft fuselage beam, the beam is subjected to an end load P = 300 N that acts at the centroid of the beam cross section (Figure E9.2). (a) Using Eq. 9.1 1, determine the normal stress oeothat acts on the sectionAB as a function of radius r and angle 8, where, by Figure E9.2u, 1.47 m 5 r < 1.53 m and 0 5 8 5 a.

(b) Determine the value of 8 for which the stress oeeis maximum. (c) For the value of 8 obtained in part (b), determine the maximum tensile and compressive stresses and their locations.

(d) Determine the maximum tensile and compressive stresses acting on the section at 8 = z/2. (e) Compare the results obtained in parts (c) and (d) to those obtained using straight-beam theory, where oee= -My/I. mm

t

0'

= 300 N

P = 300 N

(a)

FIGURE E9.2

Solution

(a) Consider the free-body diagram of the beam segment 0 < 8 < a (Figure E9.2b), where N, V, and M are the normal force, the shear force, and the bending moment acting on the section at 8, respectively. By Figure E9.2b, we have

3

CF.= V + P s i n e = o C F e = N+Pcos8 = 0 E M o = PR(l-cose)-M

=0

or V = -Psino = -300sin8 [N] N = - P ~ O S= ~ -3oocOse [NI M = PR(1-cos8) = 450(1-cos8) "em]

For the cross section, by Figure E9.26 and Table 9.2, A = b ( c - a ) = 0.04(1.53-1.47) = 0.0024m C 153 A, = b In - = 0.04 In= 0.00160021 m U 1.47

R = 1.5 m

2

328

CHAPTER s CURVED BEAMS

Note that the number of digits of precision shown for A , is required in Eq. 9.1 1. Now, by Eqs. (a), (b), and 9.1 1, we have

Gee =

N M(A-rA,) + A Ar(RA,-A) 14.2857 - 9.5250r cos r )(I -

105

a,, = - ~ c o s (~ +

CkPal

(C)

(b) For maximum (or minimum) Coo,

1

=

14 2857 - 9.5250r d8 = [125+(

.

Hence, (Tee is minimum at 8 = 0 and it is maximum at 8 = n,with values given by Eq. (c). (c) From Eq. (c), the maximum tensile and compressive stresses at 8 = n are as follows:

For r = 1.47 m, the tensile stress at A is

a,, = 125 + 38,633 = 38,758 kPa = 38.76 MPa For r = 1.53 m, the compressive stress at B is

aee= 125 - 37,588 = -37,463 kPa = -37.46 MPa (d) By Eq. (c), with 8 = n12, For r = 1.47 m, the tensile stress at A is

a,, = 0 + 19,316 kPa

= 19.32 MPa

For r = 1.53 m, the compressive stress at B is gee=

0- 18,794kpa = -18.79 MPa

(e) Using straight-beam theory, we have

MY 00, = -I

where, by Figure E9.2a, 3 -1 4 1 3 1 I = --bh = -(0.04)(0.06) = 7 . 2 10 ~ m 12 12

and for 8 = n, M = 2PR = 2(300)(1.5) = 900 N

m

Hence, by Eq. (h), 00, = -(

9

1.25 x 10 ) y

(i)

For y = -0.03 m (point A in Figure E9.2a), Eq. (i) yields (Tee = 37.50 MPa, compared to see = 38.76 MPa in part (c). For y = +0.03 m (point B in Figure E9.2a), Eq. (i) yields = -37.50 MPa, compared to O,, = 37.46 MPa in part (c). For 8 = n12, M = P R = (300)(1.5) = 450 N

m

and then by Eq. (h), 00, =

8

-(6.25 x 10 ) y

(3

For y = -0.03 m (point A ) , Eq. 6) yields 00, = 18.75 MPa, compared to oee = 19.32 MPa in part (d). ,, = 18.79 MPa in part (d). For y = +0.03 m (point B), Eq.(i) yields Oee = -18.75 MPa, compared to a

9.2

EXAMPLE 9.3 Stresses in t Crane Hook

CIRCUMFERENTIAL STRESSES IN A CURVED BEAM

329

Section BC is the critically stressed section of a crane hook (Figure E9.34. For a large number of manufactured crane hooks, the critical section BC can be closely approximated by a trapezoidal area with half of an ellipse at the inner radius and an arc of a circle at the outer radius. Such a section is shown in Figure E9.3b, which includes dimensions for the critical cross section. The crane hook is made of a ductile steel that has a yield stress of Y = 500 MPa. Assuming that the crane hook is designed with a factor of safety of SF = 2.00 against initiation of yielding, determine the maximum load P that can be carried by the crane hook.

Note: An efficient algorithm to analyze crane hooks has been developed by Wang (1985).

c

&

24.0 m m 5.0 mm-+

mm4

mm--+-+60.0

-100

! B O

fP

(b)

(a)

FIGURE E9.3

Solution

Crane hook.

The circumferential stresses Oee are calculated using Eq.9.1 1. To calculate values of A, R, and A, for the curved beam cross section, we divide the cross section into basic areasA,, A,, and A, (Figure E9.3b). For area A a = 84 mm. Substituting this dimension along with other given dimensions into Table 9.2, row (j),we find 2

A, = 1658.76 mm , R , = 73.81 mm,

A,,

= 22.64 mm

(a)

For the trapezoidal area A,, a = 60 + 24 = 84 mm and c = a + 100 = 184 mm. Substituting these dimensions along with other given dimensions into Table 9.2, row (c), we find

A, = 6100.00 mm’,

R, = 126.62 mm,

A,,

= 50.57 mm

(b)

For area A,, 6 = 0.5721 rad, b = 31.40 mm, and a = 157.60 mm. When these values are substituted into Table 9.2, row (h), we obtain 2

A, = 115.27 mm , R , = 186.01 mm,

A,,

= 0.62 mm

(c)

Substituting values ofAi, Ri, andAmjfrom Eqs. (axe) into Eqs. 9.12-9.14, we calculate

A = 6100.00 + 115.27 + 1658.76 = 7874.03 mrn2 A, = 50.57 + 0.62 + 22.64 = 73.83 mm R = 6100.00( 126.62) + 115.27( 186.01) + 1658.76(73.81) 7874.03 = 116.37 mm As indicated in Figure E9.3c, the circumferential stress distribution oee is due to the normal load

N = P and moment M, = PR. The maximum tension and compression values of 0 8 0 occur at points B and C, respectively. For points B and C, by Figure E9.3b, we find

330

CHAPTER 9 CURVED BEAMS

rB = 60mm rc = 6 0 + 2 4 + 1 0 0 + 5 = 1 8 9 m

Substituting the required values into Eq. 9.1 I , we find

oees=

-+ P 7874.03

116.37P[7874.03 - 60( 73.83)] 7874.03( 60)[ 116.37( 73.83) - 7874.031

= 0.000127P + 0.001182P

= 0.001309P (tension)

oeec=

-+ P 7874.03

116.37P[7874.03- 189(73.83)] 7874.03( 189)[116.37(73.83) - 7874.031

= 0.000127P - 0.000662P = -0.000535P

(compression)

is greater than oeec,initiation of yield occurs when oeeB Since the absolute magnitude of oBeB equals the yield stress Y. The corresponding value of the failure load (Pf)is the load at which yield occurs. Dividing the failure load Pf = Y/(0.001309) by the factor of safety SF = 2.00, we obtain the design load P ; namely, P =

EXAMPLE 9.4 Proof Test of a Crane Hook

500 = 190,900N 2.00(0.001309)

To proof test a crane hook an engineer applies a load P to the hook through a pin (Figure E9.k). Assume that the pin exerts a pressure p sin 6 [N/mm2] at radius ri for 0 I 8 I K, where p is a constant. The hook has a uniform rectangular cross section of thickness t. (a) Determine the circumferential stress 0 0 0 as a function of P,r,,

c, r, and 6.

(b) For ri = 60 mm, r, = 180 mm, and t = 50 mm, determine the maximum tensile and compressive stresses on the cross section at 6 = I C / ~and 6 = IC in terms of P. (c) If the maximum allowable tensile stress is 0 0 0 = 340 MPa, what is the allowable load P for a

safety factor of 2.2? p+

X

(a)

FIGURE E9.4

9.2

Solution

CIRCUMFERENTIALSTRESSES IN A CURVED BEAM

331

(a) Consider the free-body diagram of the hook segmentABC (Figure E9.46). Summing forces in the y direction, we have IF

C F Y = P-j[([email protected])([email protected])t][email protected]= 0 0

or 2P = c t

Next consider the free-body diagram of an element of the hook. By Figure E9.4 we have for equilibrium in the x direction e

C F x = - N s i n O - V c o s e + p i t j [email protected]@[email protected]= 0 0

or 1 Nsine+VcosO = -prit(l-cos28) 4

For equilibrium in they direction, we have e

C F Y = [email protected]+ Vsin8-prit

[email protected]@[email protected]= 0 0

or Ncos8 - Vsine =

1 - -prit(20sin28)

4

For equilibrium of moments

3

C M o = M-NR = 0

or M = NR The solution of Eqs. (b), (c), and (d) is 1 N = -prit(sine- ecose) 2 1 V = -prit(Bsin8) 2 1 M = -priRt(sin8Bcose) 2

332

CHAPTER 9 CURVED BEAMS

where

A = (r,,-ri)t

Hence, by Eqs. (h), (i), and (j),

(b) For ri = 60 mm, r,, = 180 mm, and t = 50 mm, Eq. (k) yields oee= P(sin0-

For 8 = ~ / 2Eq. , (1) yields

oee= P

e c o s e ) r z 6 -0.0005372)

r-”

- 0.0005372)

For maximum tensile stress, r = ri = 60 mm, at which

(oee),,

= 0.000539P

For maximum compressive stress, r = ro = 180 mm, at which

(oee),

= -0.000179P

oee= P

( ? ? - 0.001690)

For 8 = K, Eq. (1) yields

For maximum tensile stress, r = ri = 60 mm, at which (oee),, = 0.00169P

For maximum compressive stress, r = r,, = 180 mm, at which

(~ee),

=

-0.000563P

(c) For a maximum allowable tensile stress of 340 MPa and a safety factor of 2.2,Eq. (0)yields

9.3 RADIAL STRESSES IN CURVED BEAMS

340 2.2

I

333

- 0.00169P

or the maximum allowable load is P = 91,447 N = 91.45IcN.

9.3 RADIAL STRESSES IN CURVED BEAMS The curved beam formula for circumferential stress 006 (Eq. 9.11) is based on the assumption that the effect of radial stress is small. This assumption is accurate for curved beams with circular, rectangular, or trapezoidal cross sections, that is, cross sections that do not possess thin webs. However, in curved beams with cross sections in the fonn of an H, T, or I, the webs may be so thin that the maximum radial stress in the web may exceed the maximum circumferential stress. Also, although the radial stress is usually small, it may be significant relative to radial strength, for example, when anisotropic materials, such as wood, are formed into curved beams. The beam should be designed to take such conditionsinto account. To illustrate these remarks, we consider the tensile radial stress, resulting from a positive moment, that occurs in a curved beam at radius r from the center of curvature 0 of the beam (Figure 9%). Consider equilibrium of the element BDGF of the beam, shown enlarged in the free-body diagram in Figure 9%. The faces BD and GF, which subtend the infinitesimal angle do, have the area A' shown shaded in Figure 9.5b. The distribution of oee on each of these areas produces a resultant circumferential force T (Figure 9 . 5 ~given ) by the expression (9.17) The components of the circumferentialforces along line OL are balanced by the radial stress orr acting on the area tr d8, where t is the thickness of the cross section at the distance r from the center of curvature 0 (Figure 9 3 ) . Thus for equilibrium in the radial direction along OL,

F, = 0 = o,,trde- 2T sin(d612) = (o,,tr- T)do since for infinitesimal angle den, sin(dW2) = den. Therefore, the tensile stress resulting from the positive moment is T or, = -

(9.18)

ti-

0

urr

(a)

FIGURE 9.5 ment BDGF:

(b)

(C)

Radial stress in a curved beam. ( a )Side view. (b)Cross-sectional shape. (c) Ele-

334

CHAPTER 9 CURVED BEAMS

The force T is obtained by substitution of Eq. 9.1 1 into Eq. 9.17. Thus, r

T = !Aj d A + - j R \$ !AMx -, - A a

MAx ,A m -A) j d A A(R a

T = cA N +

a

(9.19)

AAl, - A‘A, A ( R A , - A ) MX

where r

r

A l , = j Y a

and

A’=JdA

(9.20)

a

Substitution of Eq. 9.19 into Eq. 9.18 yields the relation for the radial stress. For rectangular cross section curved beams subjected to shear loading (Figure 9.4b), a comparison of the resulting approximate solution with the elasticity solution indicates that the approximate solution is conservative. Furthermore, for such beams it remains conservative to within 6% for values of Rlh > 1.O even if the term involving N in Eq.9.19 is discarded. Consequently, if we retain only the moment term in Eq.9.19, the expression for the radial stress may be approximated by the formula *rr =

A A L - A’A, t r A ( R A , - A ) Mx

(9.21)

to within 6% of the elasticity solution for rectangular cross section curved beams subjected to shear loading (Figure 9.4b).

9.3.1 Curved Beams Made from Anisotropic Materials Typically, the radial stresses developed in curved beams of stocky (rectangular, circular, etc.) cross sections are small enough that they can be neglected in analysis and design. However, some anisotropic materials may have low strength in the radial direction. Such materials include fiber-reinforced composites (fiberglass) and wood. For these materials, the relatively small radial stress developed in a curved beam may control the design of the beam owing to the corresponding relatively low strength of the material in the radial direction. Hence, it may be important to properly account for radial stresses in curved beams of certain materials.

EXAMPLE 9.5 Radial Stress in a T-Section

The curved beam in Figure E9.5 is subjected to a load P = 120 kN. The dimensions of sectionBC are also shown. Determine the circumferential stress at B and radial stress at the junction of the flange and web at section BC.

FIGURE E9.5

9.3

Solution

RADIAL STRESSES IN CURVED BEAMS

335

The magnitudes ofA, A,, and R are given by Eqs. 9.12,9.13, and 9.14, respectively. They are

A = 48( 120) + 120(24) = 8640 mm2

A,,, = 120 In-120 + 24 In-240 = 77.93 mm 72 120 The circumferential stress is given by Eq. 9.11. It is

120,000 364.0( 1 2 0 , ~ ) [ 8 6 4 0 -72(77.93)]

8640 8640(72)[124.0(77.93) -86401 = 13.9 + 207.8 = 221.7 MPa +

OeeB =

The radial stress at the junction of the flange and web is given by Eq. 9.21, with r = 120 mm and t = 24 mm. Magnitudes of A’ and A; are

A‘ = 48( 120) = 5760 mm2 A h = 120In-120 = 61.30mm 72 Substitution of these values into Eq. 9.21, which neglects the effect of N, gives orr

=

364.0( 120,OOO)[8640(61.30)- 5760(77.93)] 24( 120)(8640)[124.0(77.93)- 86401

- 138.5 MPa

Hence, the magnitude of this radial stress is appreciably less than the maximum circumferential stress ( JoeBB I > loeecl)and may not be of concern for the design engineer.

EXAMPLE 9.6 Radial Stress in an I-Section

The curved section of the frame of a press is subjected to a positive moment M, = 96 kN m and a shear load P = 120 kN (Figure E9.6~).The dimensions of section BC are shown in Figure E9.6b. Determine the circumferential stress beeat point B and the radial stress orrat points B’ and C’ of section BC. Include the effects of traction N.

FIGURE E9.6

Solution

The magnitudes ofA, A,, and R are given by Eqs. 9.12,9.13, and 9.1, They are

A = 150(60) + 50( 120) + 150(40) = 21,000 mm2 140 A,,, = 150 In+ 50 In-260 + 150 In-300 = 136.360 mm 80 140 260 150(60)110 + 50( 120)200 + 150(40)280 = 184.286 mm R = 21,000

(a)

336

CHAPTER 9 CURVED BEAMS

By Figure E9.6c,

3

E M o = M-Mo-PR = 0

or

M = 96,000,000+ 120,000(184.286) = 118.1 x lo6 N mm Then, by Eq. 9.11 with r = 80 mm, the circumferential stress at b is

120,000+ 118,100,000 (21,000- 80( 136.360)] Oee = 21,000 21,000(80)[184.286( 136.360) -21,0001 = 5.71 + 171.80 = 177.51 MPa To find the radial stress or,. at the junction of the flange and web (point B‘), we require the geometric terms A’ and A h . By Eq. 9.20, A’ = 150(60) = 9000 mm

2

140

(b)

dr 140 150- = 150l11- 80 = 83.94mm

Ah = 80

With the values in Eq. (b), r = 140 mm, and t = 50 mm, Eqs. 9.18 and 9.19 yield A’ N + AA; - A’A,

orr= - A tr

I

trA(RA,-A)

M

- 9000 120,000+

[21,000(83.94)-9000(136.360)] (118.1 21,000 50( 140) 50( 140)(21,000)[184.286( 136.360) -21,0001

= 7.347

+ 104.189 =

106)

111.54 MPa

Here we see that the effect of N represents (7.347/ 111.54) x 100%= 6.59% of the total orrat B’ . Similarly, for the radial stress at point C‘, where r = 260 mm and t = 50 mm, the geometric terms A’ and A h are A’ = 150(60)+50(120) = 15,000mm2 260

140

150&+

Ah = 80

dr 50 - = 114.89 mm 140

Then, by Eqs. 9.18,9.19, and (c), we have Orr

=

15,000 120,000

[21,000(114.89)- 15,000(136.360)]

50(260) 50(260)(21,000)[ 184.286( 136.360) - 21,0001

(118.1

106)

+

= 6.59 + 38.48 = 45.07 MPa

At C’, the effect of N represents 14.6% of the total radial stress. In either case (point B‘ or C’), orris considerably less than oee= 177.54 MPa.

9.3

EXAMPLE 9.7 Radial Stress in Glulam Beam

RADIAL STRESSES IN CURVED BEAMS

337

A glued laminated timber (glulam) beam is used in a roof system. The beam has a simple span of 15 m and the middle half of the beam is curved with a mean radius of 10 m. The beam depth and width are both constant: d = 0.800 m and b = 0.130 m. Dead load is 2400 N/m and snow load is 4800 N/m. The geometry of the beam and assumed loading are shown in Figure E9.7. (a) Determine the maximum circumferential and radial stresses in the beam. (b) Compare the maximum circumferential stress to that obtained from the straight-beam flexure formula. (c) Compare the maximum circumferential and radial stresses to the allowable stress limits for Douglas fir: ~ ~ ~ (= 15.8 ~ l MPa, l ~ ~ ) = 0.119 MPa (AITC, 1994). 7200 Nlm

1

\

R=lOm

\

4

FIGURE E9.7

Solution

(a) The maximum bending moment occurs at midspan and has magnitude Mx = wZ2/8 = 202,500 N m. Circumferential stress (Tee is calculated using Eq. 9.1 1. For the curved beam described,

a = R - -d = 9.6m 2 d c = R + - = 10.4m 2 A = 0.13 x 0.80 = 0.104 m' 10 4 A,,, = 0.13ln= 0.0104056 9.6 The maximum circumferential stress occurs at the inner edge of the beam r = a. It is Mx(A-'Am)

uee(max) = A a ( R A , - A )

- 202,500[0.104-9.6(0.0104056)] - 15.0 0.104(9.6)[10.0(0.0104056)-0.1041

The maximum radial stress is calculated using Eq. 9.21. However, the location at which o,.,.(,,)occurs is unknown. Thus, we must maximize or,.with respect to r. For a rectangular cross section, the quantities in Eq. 9.21 are t = b = width of cross section

d = c - a = depth of cross section A = bd A' = b ( r - a ) C

A, = b l n -

Q

r A; = b ln-

U

338

CHAPTER

s

Mxr

CURVED BEAMS

Substitution of these expressionsinto Eq. 9.21 gives

h(i) - (r - a )

~n

a,, = -

rd[R ln(:)-d]

occurs at Maximizing a,, with respect to r, we find that o,~,,,~) (I-;.:)

r = ae

We evaluate Eq. (b) for the particular cross section of this example to obtain r = 9.987 m. At that location, the radial stress is, by Eq. (a),

I

- 202,500 - 0.13

0.80 )"(nI

9.6

- [(9.987 - 9.6) In

9.987(0.80)[ 10.0 In(%)

- 0.801

= 0.292 MPa An approximate formula for computing radial stress in curved beams of rectangular cross section is

(AITC, 1994, p. 227) 3M or, = -

2Rbd

Using this expression, we determine the radial stress to be or,= 0.292 MPa. The approximation of Eq.(d) is quite accurate in this case! In fact, for rectangular curved beams withR/d > 3, the error in Eq. (d) is less than 3%. However, as R/d becomes small, the error grows substantially and Eq. (d) is nonconservative. (b) Using the curved beam formula, Eq. 9.11, we obtain the maximum circumferential stress = 15.0 m a . Using the straight-beam flexure formula, Eq. 7.1, with I, = bd3/12 = as (Tee(,,) 0.005547 m4, we obtain CTBe = 202,500(0.40)/0.005547 = 14.6 MPa. Thus, the straight-beam flexure formula is within 3% of the curved beam formula. One would generally consider the flexure formula adequate for this case, in which R/d = 12.5. (c) The maximum circumferential stress is just within its limiting value; the beam is understressed just 5%. However, the maximum radial stress is 245% over its limit. It would be necessary to modify beam geometry or add mechanical reinforcement to make this design acceptable.

9.4 CORRECTION OF CIRCUMFERENTIAL STRESSES IN CURVED BEAMS HAVING I, T, OR SIMILAR CROSS SECTIONS If the curved beam formula is used to calculate circumferential stresses in curved beams having thin flanges, the computed stresses are considerably in error and the error is nonconservative. The error arises because the radial forces developed in the curved beam

CORRECTION OF CIRCUMFERENTIALSTRESSES IN CURVED BEAMS HAVING 1, T, OR SIMILAR CROSS SECTIONS

9.4

339

causes the tips of the flanges to deflect radially, thereby distorting the cross section of the curved beam. The resulting effect is to decrease the stiffness of the curved beam, to decrease the circumferential stresses in the tips of the flanges, and to increase the circumferential stresses in the flanges near the web. Consider a short length of a thin-flanged I-section curved beam included between faces BC and FH that form an infinitesimal angle d 8 as indicated in Figure 9 . 6 ~If. the curved beam is subjected to a positive moment M,,the circumferential stress distribution results in a tensile force T acting on the inner flange and a compressive force C acting on the outer flange, as shown. The components of these forces in the radial direction are T d 8 and C d o . If the cross section of the curved beam did not distort, these forces would be uniformly distributed along each flange, as indicated in Figure 9.6b. However, the two portions of the tension and compression flanges act as cantilever beams fixed at the web. The resulting bending because of cantilever beam action causes the flanges to distort, as indicated in Figure 9 . 6 ~ . The effect of the distortion of the cross section on the circumferential stresses in the curved beam can be determined by examining the portion of the curved beam ABCD in Figure 9.6d. Sections AC and BD are separated by angle 8 in the unloaded beam. When the curved beam is subjected to a positive moment, the center of curvature moves from 0 to 0*, section AC moves to A*C*, section BD moves to B*D*, and the included angle becomes 8*.If the cross section does not distort, the inner tension flange AB elongates to length A*B*. Since the tips of the inner flange move radially inward relative to the undistorted position (Figure 9.6c), the circumferential elongation of the tips of the inner flange is less than that indicated in Figure 9.6d. Therefore, CTee in the tips of the innerflange is less than that calculated using the curved beam formula. To satisfy equilibrium, it is necessary that CTee for the portion of the flange near the web be greater than that calculated using the curved beam formula. Now consider the outer compression flange. As indicated in Figure 9.6d, the outer flange shortens from CD to C*D* if the cross section does not distort. Because of the distortion (Figure 9.6c), the tips of the compressive flange move radially outward, requiring less compressive contraction. Therefore, the magnitude of

c-

C

yI / H

t ??? I ? ? ? ?4 c i ?

c;1 T

F

B

-!* F r

X

Tips of flanges

T

3 i i i iIIQ ii + 1 F

I

FIGURE 9.6 Distortion of cross section of an I-section curved beam.

340

CHAPTER 9 CURVED BEAMS

in the tips of the compression outerflange is less than that calculated by the curved beam formula, and the magnitude of oeein the portion of the compression flange near the web is larger than that calculated by the curved beam formula. The resulting circumferential stress distribution is indicated in Figure 9.7. Since in developing the curved beam formula we assume that the circumferential stress is independent of x (Figure 9.2),corrections are required if the formula is to be used in the design of curved beams having I, T, and similar cross sections. There are two approaches that can be employed in the design of these curved beams. One approach is to prevent the radial distortion of the cross section by welding radial stiffeners to the curved beams. If distortion of the cross section is prevented, the use of the curved beam formula is appropriate. A second approach, suggested by H. Bleich (1933), is discussed next.

9.4.1

Bleich’s Correction Factors

Bleich reasoned that the actual maximum circumferential stresses in the tension and compression flanges for the I-section curved beam (Figure 9.8a) can be calculated by the curved beam formula applied to an I-section curved beam with reducedflange widths, as indicated in Figure 9.8b. By Bleich’s method, if the same bending moment is applied to the two cross sections in Figure 9.8, the computed maximum circumferential tension and

FIGURE 9.7 Stresses in I-section of curved beam.

Center of curvature

(a)

FIGURE 9.8 ( a )Actual and ( b ) modified I-section for a curved beam.

9.4

CORRECTION OF CIRCUMFERENTIAL STRESSES IN CURVED BEAMS HAVING I, T, OR SIMILAR CROSS SECTIONS

341

compression stresses for the cross section shown in Figure 9.8b, with no distortion, are equal to the actual maximum circumferential tension and compression stresses for the cross section in Figure 9.8a, with distortion. The approximate solution proposed by Bleich gives the results presented in tabular form in Table 9.3. To use the table, the ratio b;l7y must be calculated, where bp = projecting width of flange (see Figure 9 . 8 ~ ) 7 = radius of curvature to the center of flange

t f = thickness of flange The reduced width bb of the projecting part of each flange (Figure 9.8b) is given by the relation b'P = abp

(9.22)

where a is obtained from Table 9.3 for the computed value of the ratio bZl7-y . The reduced width of each flange (Figure 9.8b) is given by b' = 2bL + t ,

(9.23)

where tw is the thickness of the web. When the curved beam formula (Eq. 9.1 1 ) is applied to an undistorted cross section corrected by Eq. 9.23, it predicts the maxmum circumferential stress in the actual (distorted) cross section. This maximum stress occurs at the center of the inner flange. It should be noted that the state of stress at this point in the curved beam is not uniaxial. Because of the bending of the flanges (Figure 9.6c), a transverse component of stress 0, (Figure 9.2) is developed; the sign of 0, is opposite to that of bge(,,). Bleich obtained an approximate solution for 0, for the inner flange. It is given by the relation (9.24)

where p is obtained from Table 9.3 for the computed value of the ratio b;/"f ,and where 0 0 6 is the magnitude of the circumferential stress at midthickness of the inner flange; the value of Zee is calculated based on the corrected cross section. Although Bleich's analysis was developed for curved beams with relatively thin flanges, the results agree closely with a similar solution obtained by C. G. Anderson (1950) for I-beams and box beams, in which the analysis was not restricted to thin-flanged sections. Similar analyses of tubular curved beams with circular and rectangular cross

-

TABLE 9.3 Table for Calculating the Effective Width and Lateral Bending Stress of Curved I- or T-Beams

bi/7tf

a

p

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1.o

0.977 0.580

0.950 0.836

0.917 1.056

0.878 1.238

0.838 1.382

0.800 1.495

0.762 1.577

0.726 1.636

0.693 1.677

1.1

1.2

1.3

1.4

1.5

2.0

3.0

4.0

5.0

0.663 1.703

0.636 1.721

0.611 1.728

0.589 1.732

0.569 1.732

0.495 1.707

0.414 1.671

0.367 1.680

0.334 1.700

~~

bEl?tf

a p

342

CHAPTER 9 CURVED BEAMS

sections have been made by S. Timoshenko (1923). An experimental investigation by D. C. Broughton, M. E. Clark, and H. T. Corten (1950) showed that another type of correction is needed if the curved beam has extremely thick flanges and thin webs. For such beams each flange tends to rotate about a neutral axis of its own in addition to the rotation about the neutral axis of the curved beam cross section as a whole. Curved beams for which the circumferential stresses are appreciably increased by this action probably fail by excessive radial stresses.

Note: The radial stress can be calculated using either the original or the modified cross section.

EXAMPLE 9.8 Bleich Correctior; Factors foi T-Section

A T-section curved beam has the dimensions indicated in Figure E9.8a and is subjected to pure bending. The curved beam is made of a steel having a yield stress Y = 280 MPa. (a) Determine the magnitude of the moment that indicates yielding in the curved beam if Bleich’s

correction factors are not used. (b) Use Bleich’s correction factors to obtain a modified cross section. Determine the magnitude of the moment that initiates yielding for the modified cross section and compare with the result of part (a). 20 mm

20 mm

--IF

60 mm

-+I+

60’mm

Center of curvature

Center of curvature

FIGURE E9.8 ( a )Actual section. ( b ) Modified section.

Solution

(a) The magnitudes ofA, A,, and R for the actual cross section are given by Eqs. 9.12,9.13, and 9.14, respectively, as follows: A = 4000 mm2, A, = 44.99 mm, and R = 100.0 mm. By comparison of the stresses at the locations r = 180 mm and r = 60 mm, we find that the maximum magnitude of (Tee occurs at the outer radius (r = 180 mm). (See Eq. 9.1 1.) Thus, oBB(max) -

M,[4000 - 180(44.99)] 14000(180)[100.0(44.9) - 40001/

= 1-1.141 x 10-5MA

where M, has the units of N mm. Since the state of stress is assumed to be uniaxial, the magnitude = -Y. Thus, of M, to initiate yielding is obtained by setting oeB M, =

280

= 24,540,000N

mm = 24.54 kN m

1.141 x lo-’

(b) The dimensions of the modified cross section are computed by Bleich’s method; hence b;/7tr must be calculated. It is

9.5

DEFLECTIONS OF CURVED BEAMS

343

Linear interpolation in Table 9.3 yields a = 0.651 and p = 1.711. Hence, by Eqs. 9.22 and 9.23, the modified flange width is bi = cxbp = 0.651(40) = 26.04 mm and b’ = 2bi + tw = 2(26.04) + 20 = 72.1 mm (Figure E9.8b). For this cross section, by means of Eqs. 9.12,9.13, and 9.14, we find

A = 72.1(20)+20(100) = 3442mm’

72.1(20)(70) + 20( loo)( 130) - 104.9 mm 3442 80 180 A, = 72.1 In- + 20 In= 36.96 mm 60 80 R =

I

Now by means of Eq. 9.1 1, we find that the maximum magnitude of (Tee occurs at the inner radius of the modified cross section. Thus, with r = 60 mm, Eq. 9.1 1 yields

M,[3442 - 60( 36.96)] O

= 3442(60)[ lO4.9(36.96) - 34421

= 1.363 x lO%,

The magnitude of M, that causes yielding can be calculated by means of either the maximum shear stress criterion of failure or the octahedral shear stress criterion of failure. If the maximum shear stress criterion is used, the minimum principal stress must also be computed. The minimum principal stress is o~,.Hence, by Eqs. 9.1 1 and 9.24, we find

M,[3442 - 70(36.96)] = 8.15 x 10-6M, O ” = 3442(70) [ 104.9(36.96) - 34421

-

ox,= -paee= -1.711(8.15 x 10-6M,) = - 1 . 3 9 4 ~10-’Mx

A comparison of the moment M, determined in parts (a) and (b) indicates that the computed M, required to initiate yielding is reduced by 58.8% because of the distortion of the cross section. Since the yielding is highly localized, its effect is not of concern unless the curved beam is subjected to fatigue loading. If the second principal stress O, is neglected, the moment M, is reduced by 16.5% because of the distortion of the cross section. The distortion is reduced if the flange thickness is increased.

9.5

DEFLECTIONS OF CURVED BEAMS A convenient method for determining the deflections of a linearly elastic curved beam is by the use of Castigliano’s theorem (Chapter 5). For example, the deflection and rotation of the free end of the curved beam in Figure 9.242 are given by the relations (9.25)

344

CHAPTER 9 CURVED BEAMS

(9.26) where S,, is the component of the deflection of the free end of the curved beam in the direction of load P I , Cp is the angle of rotation of the free end of the curved beam in the direction of Mo, and U is the total elastic strain energy in the curved beam. The total strain energy U (see Eq. 5.6) is equal to the integral of the strain-energy density Uo over the volume of the curved beam (see Eqs. 3.33 and 5.7). Consider the strain-energy density Uo for a curved beam (Figure 9.2). Because of the symmetry of loading relative to the (y, z ) plane, oxr= ox,= 0, and since the effect of the transverse normal stress 6, (Figure 9.2b) is ordinarily neglected, the formula for the strain-energy density U, reduces to the form

uo =

1

2

1

2

v

1

2

-6''+-6rr--6 2E 2E E rr 6\$6 +-2GOrt1

where the radial normal stress err, the circumferential normal stress b e e , and the shear stress Ore are, relative to the (x, y, z) axes of Figure 9.2b, or,= oYy, b g e = o,,, and Or, = oyz.In addition, the effect of or,is often small for curved beams of practical dimensions. Hence, the effect of 6, is often discarded from the expression for U,. Then,

u,

1

= -6

2

+- 1

2

2E " 2Gore

The stress components b e e and Ore, respectively, contribute to the strain energies U , and Us because of the normal traction N and shear V (Figure 9.2b). In addition, b e e contributes to the bending strain energy U M ,as well as to the strain energy Urnbecause of a coupling effect between the moment M and traction N, as we shall see in the derivation below. Ordinarily, it is sufficiently accurate to approximate the strain energies Us and U, that are due to shear V and traction N , respectively, by the formulas for straight beams (see Section 5.3). However, the strain energy U M resulting from bending must be modified. To compute this strain energy, consider the curved beam shown in Figure 9.2b. Since the strain energy increment dU for a linearly elastic material undergoing small displacement is independent of the order in which loads are applied, let the shear load V and normal load N be applied first. Next, let the moment be increased from zero to M,. The strain energy increment resulting from bending is

d U , = -M,A(d6) 1 = -M,wd6 1 2 2

(9.27)

where A(d6), the change in d6, and w = A(d6)/d6 are due to M, alone. Hence, w is determined from Eq. 9.10 with N = 0. Consequently, Eqs. 9.27 and Eq. 9.10 yield (with N = 0)

dU, =

AmMz 2A(RAm- A)E

(9.28)

During the application of M,, additional work is done by N because the centroidal (middle) surface (Figure 9.2b) is stretched an amount dZoee.Let the corresponding strain energy increment caused by the stretching of the middle surface be denoted by durn. This strain energy increment dUm is equal to the work done by N as it moves through the distance dFee. Thus,

DEFLECTIONS OF CURVED BEAMS

9.5

= NdFge = N E , , R d 8

dUm

345 (9.29)

where d Fee and Fee refer to the elongation and strain of the centroidal axis, respectively. The strain Fee is given by Eq. 9.3 with r = R. Thus, Eq. 9.3 (with r = R) and Eqs. 9.29,9.9, and 9.10 (with N = 0) yield the strain energy increment dUm resulting from coupling of the moment M , and traction N:

durn =

"[-

--M x

E RA,-A

R

A(RA,-A)

I d 8 = - =MXN do

(9.30)

By Eqs. 5.8, 5.14, 9.28, and 9.30, the total strain energy U for the curved beam is obtained in the form

u

=

u,+u,+u,+u,,

or 2

2

kV [email protected]+j 2AE

2A(RA, - A)E

d8

M N -I L d EA

8

(9.31)

Equation 9.31 is an approximation, since it is based on the assumptionsthat plane sectionsremain plane and that the effect of the radial stress 0, on U is negligible. It might be expected that the radial stress increases the strain energy. Hence, Eq. 9.31 yields a low estimate of the actual strain energy. However, if M, and N have the same sign, the coupling Urn,the last term in Eq.9.31,is negative. Ordinarily, Urnis small and, in many cases, it is negative. Hence, we recommend that Urn,the coupling strain energy, be discarded from Eq. 9.31 when it is negative. The discarding of Urnfrom Eq.9.31 raises the estimate of the actual strain energy when Urnis negative and compensates to some degree for the lower estimate caused by discarding 0,. The deflection Selast of rectangular cross section curved beams has been given by Timoshenko and Goodier (1970) for the two types of loading shown in Figure 9.4. The ratio of the deflection 6 , given by Castigliano's theorem and the deflection Selast is presented in Table 9.4 for several values of R/h. The shear coefficientk (see Eqs. 5.14 and 5.15) was taken to be 1.5 for the rectangular section, and Poisson's ratio v was assumed to be 0.30. TABLE 9.4 Ratios of Deflections in Rectangular Section Curved Beams Computed by Elasticity Theory and by Approximate Strain Energy Solution Neglecting UMN Pure bending

Including UMN Pure bending

(21 0.65 0.75 1.o 1.5 2.0 3.0 5.0

0.923 0.974 1.004 1.006 1.004 1.002 1.ooo

1.563 1.381 1.197 1.085 1.048 1.021 1.007

0.697 0.807 0.914 0.968 0.983 0.993 0.997

1.215 1.123 1.048 1.016 1.008 1.003 1.001

346

CHAPTER 9 CURVED BEAMS

Note: The deflection of curved beams is much less influenced by the curvature of the curved beam than is the circumferentialstress c7&% If R/h is greater than 2.0, the strain energy resulting from bending can be approximated by that for a straight beam. Thus, for R/h > 2.0, for computing deflections the third and fourth terms on the right-hand side of EQ. 9.31 may be replaced by (9.32) In particular, we note that the deflection of a rectangular cross section curved beam with R / h = 2.0 is 7.7% greater when the curved beam is assumed to be straight than when it is assumed to be curved.

9.5.1

Cross Sections in the Form of an I, T, etc.

As discussed in Section 9.4, the cross sections of curved beams in the form of an I, T, etc. undergo distortion when loaded. One effect of the distortion is to decrease the stiffness of the curved beam. As a result, deflections calculated on the basis of the undistorted cross section are less than the actual deflections. Therefore, the deflection calculations should be based on modified cross sections determined by Bleich's correction factors (Table 9.3). The strain energy terms U , and U , for the curved beams should also be calculated using the modified cross section. We recommend that the strain energy Us be calculated with k = 1.0, and with the cross-sectional area A replaced by the area of the web A, = th, where t is the thickness of the web and h is the curved beam depth. Also, as a working rule, we recommend that the coupling energy Urn be neglected if it is negative and that it be doubled if it is positive.

EXAMPLE 9.9 Deformations in a Curved Beam Subjected to Pure Bending

The curved beam in Figure E9.9 is made of an aluminum alloy (E = 72.0 GPa), has a rectangular cross section with a thickness of 60 mm, and is subjected to a pure bending momentM = 24.0 kN m.

(a) Determine the angle change between the two horizontal faces where M is applied. (b) Determine the relative displacement of the centroids of the horizontal faces of the curved beam. 100 mm 150 m m

FIGURE E9.9

Solution

Required values for A, A,, and R for the curved beam are calculated using equations in row (a) of Table 9.2: A = 60( 150) = 9000 mm

2

A, = 60 In= = 54.98 mm 100 R = 100+75 = 175 mm

9.5

DEFLECTIONS OF CURVED BEAMS

347

(a) The angle change between the two faces where M is applied is given by Eq.9.26.As indicated in Figure E9.9u,the magnitude of M, at any angle 0 is M, = M . Thus, by Eq. 9.26,we obtain

dU 0

-

54.98(24,OOO,OOO)w 9000[175(54.98)-9OOO](72,OOO)

= 0.01029rad (b) To determine the deflection of the curved beam, a load P must be applied as indicated in Figure + PR sin0 and dU/dP = R sine. Then the deflection is given by Eq.9.25, in which the integral is evaluated with P = 0. Thus, the relative displacement is given by the relation

E9.9b.In this case, M, = M

0

A(RAm- A ) E

or

EXAMPLE 9.10 Deflections in a Press

A press (Figure E9.10~) has the cross section shown in Figure E9.10b.It is subjected to a load P = 11.2kN. The press is made of steel with E = 200 GPa and v = 0.30. Determine the separation of the jaws of the press caused by the load.

10 mm

10 mm

:j FIGURE E9.10

Solution

(a)Curved beam. ( b )Actual section. (c) Modified section.

The press is made up of two straight members and a curved member. We compute the strain energies resulting from bending and shear in the straight beams, without modification of the cross sections. The moment of inertia of the cross section is I, = 181.7x lo3mm4. We choose the origin of the coordinate axes at load P, with z measured from P toward the curved beam. Then the applied shear V and moment M, at a section in the straight beam are

V = P

M, = Pz

348

CHAPTER 9 CURVED BEAMS

I

I

In the curved beam portion of the press, we employ Bleich’s correction factor to obtain a modified cross section. With the dimensions in Figure E9. lob, we find

A linear interpolation in Table 9.3 yields the result a = 0.822. The modified cross section is shown in Figure E9.10~.Equations 9.12-9.14 give

A = 34.7( 10) + lO(40) = 747 mm’ R = 34.7(10)(35)+ 10(40)(60) = 48.4 mm 747

A, = 10 In-80 + 34.7 In-40 = 16.9 mm 40 30 With 8 defined as indicated in Figure E9. lOu, the applied shear V, normal load N, and moment M, for the curved beam are v = pcose N = Psi118 M , = P(100+Rsin8) Summing the strain energy terms for the two straight beams and the curved beam and taking the derivative with respect to P (Eq. 9.25), we compute the increase in distance 6, between the load points as 100

100

6 , = 2 1 -dz P 0

I

AWG

+

2 j - -PdZ r2 + j 0 El,

P cos28 Rd8+jP*[email protected]+j AWG 0

0

P ( 100 + R sin8)2A, d8 A(RA, - A ) E

The shear modulus is G = E/[2(1 + v ) ] = 76,900 MPa and A, = th = (10)(50)= 500 mm2.Hence,

2(11,200)(100) 2(11,200)(100)3 76,900(500) 3(200,000)(181,700) 11,200(48.4)w 11,200(48.4)~ + 500( 76,9OO)(2) 747(200,000)(2) +

+

+

16.9( 11,200) [(100)2n+ n(48.4)2 2 +2(100)(48.4)(2)] 747[48.4( 16.9) - 747](200,000)

or

6, = 0.058 + 0.205 + 0.022 + 0.006 + 0.972 = 1.263 mm

9.6 STATICALLY INDETERMINATE CURVED BEAMS: CLOSED RING SUBJECTED TO A CONCENTRATED LOAD Many curved members, such as closed rings and chain links, are statically indeterminate (see Section 5.5). For such members, equations of equilibrium are not sufficient to determine all the internal resultants (V,N , M,) at a section of the member. The additional relations needed to solve for the loads are obtained using Castigliano’s theorem with

9.6

STATICALLY INDETERMINATE CURVED BEAMS CLOSED RING SUBJECTED TO A CONCENTRATED LOAD

349

appropriate boundary conditions. Since closed rings are commonly used in engineering, we present the computational procedure for a closed ring. Consider a closed ring subjected to a central load P (Figure 9 . 9 ~ )From . the condition of symmetry, the deformations of each quadrant of the ring are identical. Hence, we need consider only one quadrant. The quadrant (Figure 9.9b) may be considered fixed at section FH with a load PI2 and moment Mo at section BC. Because of the symmetry of the ring, as the ring deforms, section BC remains perpendicular to section FH. Therefore, by Castigliano’s theorem, we have for the rotation of face BC (9.33) The applied loads V,N, and M, at a section forming angle 8 with the face BC are

V =P -sin8 2 P N = -cos6 2

(9.34)

M, = M o - g ( l - c o s 8 ) 2 Substituting Eqs. 9.31 and 9.34 into Eq. 9.33, we find n/2

o=

1

[M~

0

e)(

1 - cos e)]~,

nn

do-f

A ( R A , -A ) E

0

(+ e d€J AE

(9.35)

where Urnhas been included. The solution of Eq. 9.35 is (9.36)

H

C

(a)

FIGURE 9.9 Closed ring.

350

CHAPTER 9 CURVED BEAMS

If Rjh is greater than 2.0, we take the bending energy UMas given by Eq. 9.32 and ignore the coupling energy Urn. Then, Mo is given by the relation

M, = PR ?.(I-:)

(9.37)

With Mo known, the loads at every section of the closed ring (Eqs. 9.34) are known. The stresses and deformations of the closed ring may be calculated by the methods of Sections 9.2-9.5.

9.7

FULLY PLASTIC LOADS FOR CURVED BEAMS In this section we consider curved beams made of elastic-perfectly plastic materials with yield stress Y (Figure 1 3 ) . For a curved beam made of elastic-perfectly plastic material, the fully plastic moment Mp under pure bending is the same as that for a straight beam with identical cross section and material. However, because of the nonlinear distribution of the circumferential stress b g g in a curved beam, the ratio of the fully plastic moment Mp under pure bending to maximum elastic moment M yis much greater for a curved beam than for a straight beam with the same cross section. Most curved beams are subjected to complex loading other than pure bending. The stress distribution for a curved beam at the fully plastic load Pp for a typical loading condition is indicated in Figure 9.10. Since the tension stresses must balance the compression stresses and load Pp,the part A, of the cross-sectional area A that has yielded in tension is larger than the part A , of area A that has yielded in compression. In addition to the unknowns AT and A,, a third unknown is Pp, the load at the fully plastic condition. This follows because R (the distance from the center of curvature 0 to the centroid 0) can be calculated and D is generally specified rather than Pp.The three equations necessary to determine the three unknowns AT, A,, and Pp are obtained from the equations of equilibrium and the fact that the sum of A, and A, must equal the cross-sectional area A, that is,

FIGURE 9.10 Stress distribution for a fully plastic load on a curved beam.

9.7

FULLY PLASTIC LOADS FOR CURVED BEAMS

A = AT+Ac

35 1

(9.38)

The equilibrium equations are (Figure 9.10) (9.39) (9.40)

In Eq. 9.40, YT and 7, locate the centroids of AT and A,, respectively, as measured from the centroid 0 of the cross-sectional area of the curved beam (Figure 9.10). Let M be the moment, about the centroidal axis x, resulting from the stress distribution on section BC (Figure 9.10). Then, M = P p D = A,Y

LT + A,Y 7,

(9.41)

Trial and error can be used to solve Eqs. 9.38-9.40 for the magnitudes of AT,4,and Pp, since YT and 7, are not known until A, andAc are known (McWhorter et al., 1971). The moment M (Eq. 9.41) is generally less than the fully plastic moment M p for pure bending. It is desirable to know the conditions under which M resulting from load P p can be assumed equal to Mp, since for pure bending AT is equal to A,, and the calculations are greatly simplified. For some common sections, M = Mp, when D > h. For example, for D = h, we note that M = 0.94Mp for curved beams with rectangular sections and M = 0.96Mp for curved beams with circular sections. However, for curved beams with T-sections,M may be greater than M p . Other exceptions are curved beams with I-sections and box-sections, for which D should be greater than 2h for M to be approximately equal to M p .

9.7.1 Fully Plastic Versus Maximum Elastic Loads for Curved Beams A linearly elastic analysis of a load-carrying member is required to predict the loaddeflection relation for linearly elastic behavior of the member up to the load P y that initiates yielding in the member. The fully plastic load is also of interest since it is often considered to be the limiting load that can be applied to the member before the deformations become excessively large. The fully plastic load P p for a curved beam is often more than twice the maximum elastic load P , Fracture loads for curved beams that are made of ductile metals and subjected to static loading may be four to six times P , Dimensionless load-deflection experimental data for a uniform rectangular section hook made of a structural steel are shown in Figure 9.11. The deflection is defined as the change in distance ST between points S and Ton the hook. The hook does not fracture even for loads such that PIPy > 5 . A computer program written by J. C. McWhorter, H. R. Wetenkamp, and 0. M. Sidebottom (1971) gave the predicted curve in Figure 9.11. The experimental data agree well with predicted results. As noted in Figure 9.1 1, the ratio of P p to P y is 2.44. Furthermore, the loaddeflection curve does not level off at the fully plastic load but continues to rise. This behavior may be attributed to strain hardening. Because of the steep stress gradient in the hook, the strains in the most strained fibers become so large that the material begins to strain harden before yielding can penetrate to sufficient depth at section BC in the hook to develop the fully plastic load.

352

CHAPTER 9 CURVED BEAMS

5

I

I

I

I

I

I

3.7 4

6

8

I

I

4

3 P PY 2

1

'

OO

I I

I I I 2 2.4

r'P

I I

I 10

12

PROBLEMS Section 9.2

9.1. A curved beam has the T-shaped cross section shown in Figure P9.1. The radius of curvature to the inner face of the circumferential flange is 2o mm. The maximum stress has a magnitude of 250 m a . Determine the magnitude of the bending moment that may be applied to the beam.

9.2. A curved steel bar of circular cross section is used as a crane hook (Figure P9.2). The radius of curvature to the inner edge of the bar is r and the bar has diameter d.

a. Determine the maximum tensile and compressive stresses at section A-A in terms of load P, radius r, and diameter d. b. The maximum allowable design tensile stress at sectionA-A . the maximum allowable load p, for a is 375 M P ~ ~~~~e~ radius r = 75 mm and a diameter d = 50 mm.

9.3. In a redesign of the aircraft beam of Example 9.2, the beam is replaced by a beam with the cross section shown in Figure P9.3.

PROBLEMS

353

9.7. The curved beam in Figure p9.7 has a circular cross section 50 mm in diameter. The inside diameter of the curved beam is 40 mm. Determine the stress at B for P = 20 kN.

L-20 mm-

I

i I I

FIGURE P9.1

FIGURE P9.7

9.8. Let the crane hook in Figure E9.3 have a trapezoidal cross section as shown in row (c) of Table 9.2 with (see Figure P9.8) a = 45 mm, c = 80 mm, b, = 25 mm, and b, = 10 mm. Determine the maximum load to be carried by the hook if the working stress limit is 150 MPa. FIGURE P9.2 10 mm

Is\,1470 mm -++-++- 50 mm I 25 mm

i

FIGURE P9.8

50 mm

I

25 mm

I FIGURE P9.3

a. Rework Example 9.2 with the new cross section. b. Compare the results to those of Example 9.2.

c. Comment on the worthiness of the redesign.

9.9. A curved beam is built up by welding together rectangular and elliptical cross section curved beams; the cross section is shown in Figure p9.9. The center of curvature is located 20 mm from B. The curved beam is subjected to a positive bending moment M,. Determine the stresses at points B and C in terms of M,. 15 mm

9.4. Rework Example 9.4 assuming that the pin exerts a uniform pressure p on the hook at radius iifor 0 5 8 I n.Compare the results to those of Example 9.4. 9.5. The frame shown in Figure E9.1 has a rectangular cross section with a thickness of 10 mm and depth of 40 mm. The load P is located 120 mm from the centroid of section BC. The frame is made of steel having a yield stress of Y = 430 MPa. The frame has been designed using a factor of safety of SF = 1.75 against initiation of yielding. Determine the maximum allowable magnitude of P, if the radius of curvature at section BC is R = 40 mm.

9.6. Solve Problem 9.5 for the condition that R = 35 mm.

,

-- ......

,

15 mm 20 mm I

FIGURE P9.9

9.10. A commercial crane hook has the cross-sectional dimensions shown in Figure p9.10 at the critical section that is subjected to an axial load P = 100 kN. Determine the circumferential stresses at the inner and outer radii for this load.

354

CHAPTER 9 CURVED BEAMS

31.0 mm

I

I

FIGURE P9.10 FIGURE P9.12

Assume that area A, is half of an ellipse [see row (j)in Table 9.21 and area A , is enclosed by a circular arc.

9.11. A crane hook has the cross-sectional dimensions shown in Figure P9.11 at the critical section that is subjected to an axial load P = 90.0 kN. Determine the circumferential stresses at the inner and outer radii for this load. Note that A, and A, are enclosed by circular arcs.

9.13. A curved beam with a rectangular cross section strikes a 90" arc and is loaded and supported as shown in Figure P9.13. The thickness of the beam is 50 mm. Determine the hoop stress cooalong line A-A at the inside and outside radii and at the centroid of the beam.

I FIGURE P9.11

9.12. The curved beam in Figure P9.12 has a triangular cross section with the dimensions shown. If P = 40 kN, determine the circumferential stresses at B and C.

k-500 rnm-ttc500 mm+

P9.13

Section 9.3

9.14. Determine the distribution of the radial stress or,in section BC of the beam of Example 9.1. Also determine the maximum value of or,and its location. 9.15. Determine the magnitude of the radial stress or,in section BC of Figure P9.12 at a radial distance of 30 mm from point B. 9.16. For the curved beam in Problem 9.9, determine the radial stress in terms of the moment M, if the thickness of the web at the weld is 10 mm. 9.17. Figure F'9.17 shows a cast iron frame with a U-shaped cross section. The ultimate tensile strength of the cast iron is ou= 320 m a .

a. Determine the maximum value of P based on a factor of safety SF = 4.00,which is based on the ultimate strength. b. Neglecting the effect of stress concentrations at the fillet at the junction of the web and flange, determine the maximum radial stress when this load is applied.

c. Is the maximum radial stress less than the maximum circumferential stress?

is 18

300mm

_-____-

FIGURE P9.17

/

/

PROBLEMS

355

Section 9.4 9.18. A T-section curved beam has the cross section shown in Figure P9.18. The center of curvature lies 40 mm from the flange. If the curved beam is subjected to a positive bending moment M, = 2.50 kN m, determine the stresses at the inner and outer radii. Use Bleich’s correction factors. What is the maximum shear stress in the curved beam?

9.24). A load P = 12.0 kN is applied to the clamp shown in Figure P9.20. Determine the circumferential stresses at points B and C, assuming that the curved beam formula is valid at that section.

60 mm

10 mm

FlGURE P9.18 FIGURE P9.20

9.19. Determine the radial stress at the junction of the web and the flange for the curved beam in Problem 9.18. Neglect stress concentrations. Use the Bleich correction.

9.21. Determine the radial stress at the junction of the web and inner flange of the curved beam portion of the clamp in Problem 9.20. Neglect stress concentrations.

Section 9.5 9.22. If moment M, and axial force N are applied simultaneously, the strain-energy density resulting from these two actions is

where w is given by Eq. 9.10 and 7,, is found from Eq.9.3 with r = R . Using this expression for strain-energy density, derive Eq. 9.3 1. 9.23. The curved beam in Figure P9.23 is made of a steel (E = 200 GPa) that has a yield stress Y = 420 MPa. Determine the magnitude of the bending moment M yrequired to initiate yielding in the curved beam, the angle change of the free end, and the horizontal and vertical components of the deflection of the free end.

9.24. Determine the deflection of the curved beam in Problem 9.7 at the point of load application. The curved beam is made of an aluminum alloy for which E = 72.0 GPa and G = 27.1 GPa. Let k = 1.3. 9.25. The triangular cross section curved beam in Problem 9.12 is made of steel (E = 200 GPa and G = 77.5 GPa). Determine

60 mm

FIGURE P9.23

the separation of the points of application of the load. Let k = 1.5. 9.26. Determine the deflection across the center of curvature of the cast iron curved beam in Problem 9.17 for P = 126 kN. E = 102.0 GPa and G = 42.5 GPa. Let k = 1.0 with the area in shear equal to the product of the web thickness and the depth.

Section 9.6 9.27. The ring in Figure P9.27 has an inside diameter of 100 mm, an outside diameter of 180 mm, and a circular cross section. The ring is made of steel having a yield stress of Y = 520 MPa. Determine the maximum allowable magnitude of P if the ring has been designed with a factor of safety SF = 1.75 against initiation of yielding.

9.28. If E = 200 GPa and G = 77.5 GPa for the steel in Problem 9.27, determine the deflection of the ring for a load P = 60 kN. Let k = 1.3. 9.29. An aluminum alloy ring has a mean diameter of 600 mm and a rectangular cross section with 200 mm thickness and a depth of 300 mm (radial direction). The ring is loaded by

356

CHAPTER

s

CURVED BEAMS

P

9.30. If E = 72.0 GPa and G = 27.1 GPa for the aluminum alloy ring in Problem 9.29, determine the separation of the points of application of the loads. Let k = 1.5. 9.31. The link in Figure P9.31 has a circular cross section and is made of a steel having a yield stress of Y = 250 m a . Determine the magnitude of P that will initiate yield in the link.

FIGURE P9.27

diametrically radial loads P = 4.00 MN. Determine the - opposed __ maximum tensile and compressive circumferential stresses in the ring.

FIGURE P9.31

Section 9.7

9.32. Let the curved beam in Figure 9.10 have a rectangular cross section with depth h and width b. Show that the ratio of the bending moment M for fully plastic load P , to the fully plastic moment for pure bending M, = Ybh2/4 is given by the relation I

9.33. Let the curved beam in Problem 9.5 be made of a steel that has a flat-top stress-strain diagram at the yield stress Y = 430 MPa. From the answer to Problem 9.5, the load that initiates yielding is equal to P , = SF(P) = 6.05 kN. Since D = 3h, assume M = M pand calculate P,. Determine the ratio P p / P y . 9.34. Let the steel in the curved beam in Example 9.8 be elastic-perfectly plastic with yield stress Y = 280 MPa. Determine the fully plastic moment for the curved beam. Note that the original cross section must be used. The distortion of the cross section increases the fully plastic moment for a positive moment.

REFERENCES AMERICAN INSTITUTE OF TIMBER CONSTRUCTION (ARC) (1994). Timber Construction Manual, 4th ed. New York: Wiley. ANDERSON, C. G. (1950). Flexural Stresses in Curved Beams of I- and Box Sections. Presented to Inst. of Mech. Engineers, London, Nov. 3. BLEICH,H. (1933). Die Spannungsverteilung in den Gurtungen gekriimmter Stabe mit T- und I-formigem Querschnitt. Der Stahlblau, Beilage zur Zeitschrif, Die Bautechnik, 6(1): 3-6. BROUGHTON, D. C., CLARK,M. E., and CORTEN,H. T. (1950). Tests and Theory of Elastic Stresses in Curved Beams Having I- and TSections. Exper. Mech., 8(1): 143-155.

I. C., WETENKAMP, H. R., and SIDEBOTTOM, 0. M. MCWHORTER, (1971). Finite Deflections of Curved Beams. J. Eng. Mech. Div., Proc. A X E , 97 345-358. RMOSHENKO, S. (1923). Bending Stresses in Curved Tubes of Rectangular Cross-Section. Trans. ASME, 45: 135-140. S., and GOODIER, J. (1970). Theory of Elasticity, 3rd ed. TIMOSHENKO, New York McGraw-Hill. WANG,C. C. (1985). A Unified Algorithm for Accurately Sizing Straight and Curved Beam Sections to Allowable Stress Limits. Presented at ASME Des. Eng. Div. Conf. and Exhibit on Mech. Vibration and Noise, Cincinnati,OH, Sept. 10-13, Paper 85-DET-102.

CHAPTER

10

BEAMS ON ELASTIC FOUNDATIONS I

I n certain applications, a beam of relatively small bending stiffness is placed on

an elastic foundation and loads are applied to the beam. The loads are transferred through the beam to the foundation. In this chapter, we assume that the foundation resists the loads transmitted by the beam and responds in a linearly elastic manner; that is, the pressure developed at any point between the beam and the foundation is proportional to the deflection of the beam at that point. This type of foundation response is referred to as the Winkler foundation or Winkler model (Hetknyi, 1946; Westergaard, 1948). This assumption is fairly accurate for small deflections. However, if the deflections are large, the resistance of the foundation generally does not remain linearly proportional to the beam deflection. The solution presented in this chapter for beams on elastic foundations can be used to obtain a simple approximate solution for beams supported by identical elastic springs that are spaced uniformly along the beam. Extensive surveys of studies on beams on elastic foundations have been given by Kerr (1964), Selvadurai (1979), Scott (1981), Vallabhan and Das (1988), and Jones and Xenophontos (1977). Design tables based on the Winkler model have been developed by Iyengar and Ramu (1979).

10.1 GENERAL THEORY A single differential equation describes the response of a beam resting on an elastic foundation and subjected to transverse loads. The boundary conditions for the beam depend on how the beam is supported at its ends. For instance, consider a beam of infinite length attached along its length to an elastic foundation (Figure 10.1). Let the origin of coordinate axes (x, y, z) be located at the centroid of the beam cross section and let a concentrated lateral load P be applied to the beam at the origin of the (x,y, z) axes. The z axis coincides with the axis of the beam, the x axis is normal to the figure (directed toward the reader), and the y axis is normal to the elastic foundation. The load P causes the beam to deflect, which in turn displaces the elastic foundation. As a result, a distributed force is developed between the beam and the foundation. Thus, relative to the beam, the stiffness of the foundation produces a laterally distributed force q (force per unit length) on the beam (Figure 10.lb). The distributed load q is taken to be positive when it pushes up on the beam. When the deflection of the beam is directed downward (positive), the supporting medium is compressed and pushes up on the beam (q is positive). When the deflection is upward (negative), tension is produced in the supporting medium; it pulls down on the beam (q is negative). In such regions, we shall assume that the beam is attached to the foundation. 357

358

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

q AZ

(a)Free-body diagram

P

YI

I

I

Pz

(c) Deflection, y

4

4

Y

Pz

(d)Slope, 8 = dz

9

-

I Pz

(e) Bending moment,

M,y = -EIx

-

V, Shear,

d 3y V =-EI,- -

I

d.z3

FIGURE 10.1 Infinite beam on an elastic foundation and loaded at origin.

Also, when the beam deflects, horizontal frictional forces may develop between the beam and the supporting material. The influence of such horizontal forces has been discussed by Hetknyi (1946, Chapter VI). Consider the free-body diagram of a beam element enclosed between two vertical cross sections,' a distance Az apart (Figure lO.lu), with positive sign conventions for the total vertical shear Vy and moment M, indicated. For the indicated sign conventions and for small displacements, we obtain the differential relations 8 = -dY dz'

M, = -El,- dLY dz2

(10.1) I

'This assumes that the beam slope is so small that the cross sections normal to the beam axis can be replaced by vertical sections.

10.1

GENERAL THEORY

359

For the linearly elastic foundation, the distributed load q is linearly proportional to the deflection y of the beam; thus,

(10.2)

9 = kY

where the spring coefficient k may be written in the form k = bk,

(10.3)

in which b is the uniform beam width and k, is the elastic spring constant or modulus of thefoundation. The dimensions of k, are [F/L3]. In the following derivations, we shall use the symbol k. However, it must be remembered that k includes the beam width b and will be numerically equal to ko only if b = 1. When the beam rests on a soil subgrade, the modulus of the foundation can be highly variable. Often in the design of foundations for building structures, initial estimates of foundation modulus k,, are made based on qualitative descriptions of the soil or some knowledge of the unconfined compressive strength qu. See Table 10.1 for representative data for sand and clay soils. Substitution of Eq. 10.2 into the fourth of Eqs. 10.1 yields the differential equation of the bending axis of the beam on an elastic foundation:

EI,-d4Y = -ky dz4

(10.4)

With the notation

p=4F 4EI,

(10.5)

the general solution y of Eq. 10.4 may be expressed as y = e P z ( c ,sinpz + c2cospz) + e-PZ(C3sinpz + ~ ~ c o s p z )

(10.6)

Equation 10.6 represents the general solution for the response of an infinite beam on an elastic foundation subjected to a concentrated lateral load. The magnitudes of the TABLE 10.1 Values of Subgrade Modulus for Sand and Clay Soils

Soil type Loose sand Medium sand Dense sand Clayey sand (medium) Silty sand (medium) Clay, qu< 0.2 N/mm2 Clay, 0.2 N/mm2 < qu< 0.4 N/mm2 Clay, qu =. 0.4 N/mm2 Source: Data adapted from Bowles (1995).

Range of k,, IN/mm31 0.005-0.016 0.010-0.080 0.063-0.126 0.031-0.080 0.024-0.048 0.012-0.024 0.024-0.048 > 0.048

360

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

Y

FIGURE 10.2 Semiinfinite beam on elastic foundation and loaded at the end.

constants of integration C1, C,, C3, and C4 are determined by the boundary conditions. Solutions for the response of a beam supported by an elastic foundation and subjected to specific lateral loads can be obtained by the method of superposition. The solutions for an infinite beam loaded by a concentrated load (Figure 10.1) and for a semiinfinitebeam loaded at the end by a concentrated load P and moment Mo as indicated in Figure 10.2 are employed. In either of the cases shown in Figures 10.1 and 10.2, the deflection of the beam goes to zero for large positive values of z. Consequently, the constants Cl and C, in Eq. 10.6 are zero, and the equation for the displacement y of the bending axis of the beam reduces to y = e-Pz(~,sinpz+ c4cospz), z 2 o

(10.7)

Because of symmetry, the displacement of the beam in Figure 10.1 for negative values of z can be obtained from the solution for positive values of z, that is, y(-z) = y(z). For the case of the semiinfinite beam (Figure 10.2), z 2 0, so Eq. 10.7 applies directly.

10.2 INFINITE BEAM SUBJECTED TO A CONCENTRATED LOAD: BOUNDARY CONDITIONS Consider a beam of infinite length, resting on an elastic foundation and loaded at the origin 0 of coordinate axes (y, z) with concentrated load P (Figure 10.1). To determine the two constants of integration, C3 and C4 in Eq. 10.7, we employ the conditions (a) that the slope of the beam remains zero under the load because of symmetry and (b) that half of the load P must be supported by the elastic foundation under the half of the beam specified by positive values of z. The other half of P is supported by the elastic foundation where z < 0. Thus, we obtain the relations ca

3 = O dz

f o r z = O and 2

Ikydz=P

(10.8)

0

The condition of vanishing slope at z = 0 yields, with Eq. 10.7,

c, = c, = c Hence, Eq. 10.7 becomes y = ce-Pz(sinpz

+ cospz)

Substituting Eq. 10.9 into the second of Eqs. 10.8, we obtain

(10.9)

10.2

INFINITE BEAM SUBJECTED TO A CONCENTRATED LOAD: BOUNDARY CONDITIONS

361

(10.10) Consequently, the equation of the deflected axis of the beam is y = Qe-pz(sinpz 2k

+ cospz),

z2o

(10.11)

Equation 10.11 holds for positive values of z. The deflections for negative values of z are obtained by the condition that y(-z) = y(z), that is, by symmetry. Values for the slope, moment, and shear are obtained by substitution of Eq. 10.11 into Eqs. 10.1.Thus, we find

(10.12)

z20 y = g A 2k pz’

(10.13)

(10.14) 3

VY = - E I Q = - g D p z , ,dz3

z20

(10.15)

where

(10.16)

The four functions A, B, C , and D are all of the same type and they form periodical relations. Thus, by Eq. 10.16,we may write

(10.17)

These relations are useful in applications and in the derivation of formulas for slope, moment, and shear of beams on elastic foundations. For convenience, selected values of Ap,, Bpz, Cp,, and Dpzare listed in Table 10.2.These functions are also plotted in Figure 10.3. Values of deflection, slope, bending moment, and shear at any point along the beam are given by Eqs. 10.12, 10.13, 10.14,and 10.15,respectively. By using the symmetry conditions, y(-z) = y(z), 6(-z) = -6(z), M,(-z) = M,(z), and V,(-z) = -V,(z), these quantities are plotted versus pz in Figures 10.1~-10.16Since all of these quantities approach zero as pz becomes large, the above solutions may be used as approximations for beams of finite length. In particular, in Table 10.2and Figure 10.3,we note thatAp = 0 for pz = 3a/4; therefore, the beam has zero deflection at a distance 3a/(4P) from the load. A beam with a length L = 3a/(2P) loaded at the center has a maximum deflection 5.5% greater (Hetenyi, 1946) and a maximum bending moment 1.9% greater than for a beam with infinite length. Although the error in using the solution for a beam of length L = 3 ~ / ( 2 p )is nonconservative,

362

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

TABLE 10.2

0 0.02 0.04 0.10 0.20 0.30 0.40 0.50 0.60 0.70 1 - A 4 0.80 0.90 1.oo 1.10 1.20 1.30 1.40 1.50 1

in

1.60 1.70 1.80 1.90 2.00 2.20 3

4"

2.40 2.60 2.80 3.00 A

3.20 3.40 3.60 3.80 5 4 4.00 - A

;A

2n

1 0.9996 0.9984 0.9906 0.9651 0.9267 0.8784 0.8231 0.7628 0.6997

0 0.0196 0.0384 0.0903 0.1627 0.2189 0.2610 0.2908 0.3099 0.3199

0.6448

0.3224

0.6353 0.5712 0.5083 0.4476 0.3898 0.3355 0.2849 0.2384

0.3223 0.3185 0.3096 0.2967 0.2807 0.2626 0.2430 0.2226

-0.0093 -0.0658 -0.1109 -0.1458 -0.17 16 -0.1897 -0.201 1 -0.2068

0.2079

0.2079

-0.2079

0.1960 0.1576 0.1234 0.0932 0.0667 0.0244

0.2018 0.1812 0.1610 0.1415 0.1230 0.0895

-0.2077 -0.2046 -0.1985 -0.1899 -0.1793 -0.1547

0

1 0.9604 0.9216 0.8100 0.6398 0.4888 0.3564 0.2414 0.1430 0.0599

0

1 0.9800 0.9600 0.9003 0.8024 0.7078 0.6174 0.5323 0.4529 0.3798 0.3224 0.3131 0.2527 0.1987 0.1509 0.1091 0.0729 0.0419 0.0158

0 -0.0059 -0.0236 -0.0376 -0.0484 -0.0563 -0.0652

0.0671

-0.1342

-0.0671

-0.0056 -0.0254 -0.0369 -0.0422 -0.0432 -0.0431 -0.0408 -0.0366 5.0314

0.0613 0.0383 0.0204 0.0071 0 -0.0024 -0.0085 -0.0121 -0.0137

-0.1282 -0.1020 -0.0777 -0.0563 -0.0432 -0.0383 -0.0238 -0.0124 -0.0040

-0.0669 -0.0637 -0.0573 -0.0493 -0.0432 -0.0407 -0.0323 5.0245 -0.0177

-0.0278

-0.0140

0

-0.0139

-0.0258

-0.0139

0.0019

-0.0120

-0.0090

-0.0090

0.0090

0

0.0019

0.0019

0.0019

0

the error is not large; therefore, the infinite-beam solution yields reasonable results for beams ) loaded at the center. The infinite-beam solution also yields reaas short as L = 3 ~ / ( 2 pwhen sonable results for much longer beams for any location of the concentrated load as long as the distance from the load to either end of the beam is equal to or greater than 3~/(4p).

10.2

INFINITE BEAM SUBJECTED TO A CONCENTRATED LOAD: BOUNDARY CONDITIONS

363

FIGURE 10.3 Beam on elastic foundation functions.

10.2.1

Method of Superposition

Refemng to Eqs. 10.12-10.15, we see that y, 8, M,,and Vy are proportional to the load P. Also, recall by symmetry y(-z) = y(z), 6(-z) = -e(z), M,(-z) = M,(z), and Vy(-z) = -Vy(z). Hence, symmetry2and the principle of superposition are directly applicable to the solution of beams subjected to multiple loads. For example, consider an infinite beam subjected to three point loads P I ,P2, and P3 (Figure 10.4) that act at z = -a, -b, and -c, respectively. The resulting displacement is, by Eq. 10.12,

Similar equations may be written for 8, M,,and V,,. To demonstrate the superposition method, suppose that we want to determine the deflection and rotation at points A and B for the beam in Figure 10.4. For the location of the origin 0 as shown, the coordinate z, is positive and the coordinate z, is negative. At point A the foregoing equation for deflection is applied directly. Likewise, the corresponding equation for rotation follows naturally. Thus,

FIGURE 10.4 Infinite beam subjected to three point loads.

2Symmetry here is equivalent to Maxwell's law of reciprocity (Langhaar, 1989, p. 137).

364

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

However, point B lies to the left of the load P,. Hence the value (z, + c) is negative and cannot be used directly in Eqs. 10.12-10.15. Rather, we use the positive value IZ, + c I in these equations and account for the symmetry of y and the antisymmetry of 8 as follows:

The symmetry of M, and the antisymmetry of Vy are treated similarly.

10.22 Beam Supported on Equally Spaced Discrete Elastic Supports Long beams are sometimes supported by elastic springs equally spaced along the beam (Figure 10.5~). Although coil springs are shown in Figure 10.5, each spring support may be due to the resistance of a linearly elastic member or a structure such as a tension member, straight beam, or curved beam. It is possible to obtain an exact solution for the springsupported beam of Figure 1 0 . 5 ~by energy methods (see Section 5.5, Example 5.18); however, the computational work becomes prohibitive as the number of springs becomes large. Alternatively, we may proceed as follows: Let each spring in Figure 1 0 . 5 ~ have the same constant K. The force R that each spring exerts on the beam is directly proportional to the deflection y of the beam at the section where the spring is attached. Thus, we write R = Ky

(b)

FIGURE 10.5 Infinite beam supported by equally spaced elastic springs.

(10.18)

10.2

INFINITE BEAM SUBJECTED TO A CONCENTRATED LOAD: BOUNDARY CONDITIONS

365

We assume that the load R is distributed uniformly over a spacing I, a distance 112 to the right and to the left of each spring. Thus, we obtain the stepped distributed loading shown in Figure 10% If the stepped distributed loading is approximated by a smooth average curve (dashed curve in Figure lo.%), the approximate distributed load is similar to the distributed load q of Figure 10.lb. Since the dashed curve in Figure 10.5b intersects each of the steps near its center, we assume that the dashed curve does indeed intersect each of the steps directly beneath the spring. Thus, we assume that an equivalent spring constant k exists, such that

(10.19) Hence, substitution of Eq. 10.19 into Eq. 10.5 yields an equivalent p for the springs. Next, we assume that Eqs. 10.12-10.15 are valid for an infinite beam supported by equally spaced elastic supports and loaded at the center. Obviously, the resulting approximate solution becomes more accurate as the spacing 1 between springs becomes small. However, we note that the error for this approximate solution becomes great when the spacing 1 between springs becomes large. It has been found that the error in the solution is not excessive if we require that the spacing 1between springs satisfies the condition

(10.20) The magnitude of the error for spacing that satisfies Eq. 10.20 is discussed in Example 10.2. The approximate solution for a beam of infinite length, with equally spaced elastic supports, may be used to obtain a reasonable approximate solution for a sufficiently long finite-length beam. We note that the load exerted by each elastic spring has been assumed to be distributed over a distance 1, with the distribution being uniform over a distance 112 to the left and right of the spring (Figures 10.5a and 10.5b). Hence, consider a beam of length L supported by discrete elastic springs (Figure 10.6a). In general, the end springs do not coincide with the ends of the beam but lie at some distance less than 112 from the beam ends. Since the distributed effect of the end springs is assumed to act over length I, 112 to the left and right of the end springs, we extend the beam of length L to a beam of length L", where (Figure 10.6b) L" = ml

(b)

FIGURE 10.0 Spring-supported beam. ( a )Actual beam length. ( b )Adjusted length.

(10.21)

366

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

and the integer m denotes the number of spring supports. If L” 2 3n/(2P),the approximate solution for a spring-supported infinite beam yields a reasonably good approximation for a spring-supported finite beam of length L.

EXAMPLE 10.1 Diesel Locomotive Wheek on Rair

A railroad uses steel rails (E = 200 GPa) with a depth of 184 mm. The distance from the top of the rail to its centroid is 99.1 mm, and the moment of inertia of the rail is 36.9 x lo6 mm4. The rail is supported by ties, ballast, and a road bed that together are assumed to act as an elastic foundation with spring constant k = 14.0 N/mm2. (a) Determine the maximum deflection, maximum bending moment, and maximum flexural stress in the rail for a single wheel load of 170 kN.

(b) A particular diesel locomotive has three wheels per bogie equally spaced at 1.70 m. Determine the maximum deflection, maximum bending moment, and maximum flexural stress in the rail if the load on each wheel is 170 kN.

Solution

The equations for bending moment and deflection require the value of p. From Eq. 10.5,we find that

p

=

‘Ex

= 0.000830mm-’

=

4 200~ lo3 3 6 . 9 ~ 10

(a) The maximum deflection and maximum bending moment occur under the load where Ap = Cp =

1.00. Equations 10.12 and 10.14 give

M,,

=

- - l7OXlo3

4/3

4(0.000830)

= 51.21

om, = Mmaxc -- 51.21x106(99.1) = 137.5MPa I X 36.9 x lo6 (b) The deflection and bending moment at any section of the beam are obtained by superposition of and the effects of each of the three wheel loads. With superposition, an examination of Figures 10.1~ 10.k indicates that the maximum deflection and maximum bending moment occur either under the center wheel or under one of the end wheels. Let the origin be located under one of the end wheels. The distance from the origin to the next wheel is z1 = 1.7 x lo3 mm. Hence, pzl = 0.000830(1.7 x lo3) = 1.411. The distance from the origin to the second wheel is z2 = 2( 1.7 x lo3)mm. Hence, pz2= 0.000830(2)(1.7 x lo3)= 2.822. From Table 10.2, we find Apzl = 0.2797,

Cpzl = -0.2018

Apz2 =

Cpz2 = -0.0752

-0.0377,

The deflection and bending moment at the origin (under one of the end wheels) are

yend = g2k( ApzO+ Apzl + A p z 2 ) = 5.039(1 + 0.2797 - 0.0377) = 6.258 mm P 6 Mend = 4p -(C pzO+ Cpzl + Cpz2) = 51.20 x 10 ( 1 -0.2018 -0.0752) = 37.02 kN m

Now, let the origin be located under the center wheel. The distance between the center wheel and either of the end wheels is z1 = 1.7 x lo3mm. Therefore,

10.2

INFINITE BEAM SUBJECTED TO A CONCENTRATED LOAD: BOUNDARY CONDITIONS

367

+ 2Apzl) = 5.039[ 1 + 2(0.2797)] = 7.858 mm ycenter= Q(A 2k bZ0 P MCenter= -\$Cpz0

+ 2Cpz1) = 51.20 x 106 [ 1 - 2(0.2018)]

= 30.54 kN m

Thus, we find

ycenkr = y,,

= 7.858 mm,

Mend= M,,

= 37.02 kN 9 m

and

om,, = Mm,c -- 37.02 x lO‘(99.1) = 99.4 MPa 36.9 x lo6

I,

EXAMPLE 10.2 Finite-Length Beam Supported by Seven Springs

Solution

An aluminum alloy I-beam (depth = 100 mm, I, = 2.45 x lo6mm4, and E = 72.0 GPa) has a length L = 6.8 m and is supported by seven identical springs (K= 1 10 N/mm) spaced at distance 1 = 1.10 m center to center along the beam. A load P = 12.0 kN is applied at the center of the beam over one of the springs.

Using the approximate solution method described in Section 10.2, determine the load carried by each spring, the deflection of the beam under the load, the maximum bending moment, and the maximum bending stress in the beam. The exact solution of this problem has been presented in Example 5.18. The magnitude of the factor p is estimated by means of Eqs. 10.19 and 10.5. Thus, we find k = - K= - - 0.100 N/mm2 ‘lo 1 1.1 x lo3 0.100

s=4/

= 0.000614 mm-l

hj4(72 x 103)(2.45 x lo6) By Eqs. 10.20 and 10.21, we see that 3

a

2 = 1.1ox10 < -

=

a = 1279 mm 4(0.000614) 3 3z L” = 7(1.10x10 ) = 7700mm>- = 3a = 7675 mm 2 p 2(0.000614) 4p

Hence, the limiting conditions on 1 and L” are satisfied. The maximum deflection and maximum bending moment occur under the load where ApZ = Cpz= 1.00. Equations 10.12 and 10.14 give

M,,

= p --

4p

l 2 lo3 = 4.886 x lo6 N mm 4(0.000614)

The deflection ymax(yo = ymaxin Figure E5.18b) occurs at the origin (at the center of the beam under the load). The magnitude of pz for the first, second, and third springs to the right and left of the load are p l = 0.6754, 2pl = 1.3508, and 3pl = 2.0262, respectively. From Table 10.2, Ap, = 0.7 153, A2pr = 0.3094, andA3p, = 0.0605. The deflections of the springs C, B, and A (see Figure E5.18b) are given by Eq. 10.12 as

368

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

yc = \$p,

= 36.84(0.7153) = 26.35 mm

ye = PPA,p, = 36.84(0.3094) = 11.40 mm 2k

y A = \$,pr

= 36.84(0.0605) = 2.23 mm

The reaction for each spring may be computed by means of Eq. 10.18.A comparison of the approximate solution presented here with the exact solution of Example 5.18 is given in Table E10.2. Although the reaction atA is considerably in error, the results in Table E10.2 indicate that the approximate maximum deflection is 5.50% less than the exact deflection, whereas the approximate maximum bending moment is 6.68% greater than the exact bending moment. These errors in the maximum deflection and maximum moment are not large when one considers the simplicity of the present solution compared to that of Example 5.18. TABLE E10.2 Quantity

Reaction A Reaction B Reaction C Reaction D MIX,, Ymax

EXAMPLE 10.3 infinite Beam Subjected to a Couple

Exact solution (Example 5.18)

Approximate solution

-454 N 1216 N 3094 N 4288 N 4.580 kN m 38.98 mm

245 N 1254 N 2899 N 4052 N 4.886 kN m 36.84 mm

A beam of infinite length, attached to an elastic foundation, is subjected to concentrated forces P , and P2, applied as shown in Figure E10.3a. (a) In terms of P I and P,, employ the solution for a point load and derive formulas for the displacement y and the bending moment M of the beam.

I I

(b) Let P , = I P2 1 = P and let 6 + 0, assuming that P 6 + Mo # 0. Derive expressions for the beam displacementy and the bending moment M, resulting from the moment M,.

Foundation modulus = k

YI (a)

FIGURE E10.3a

Solution

(a) By Eqs. 10.12 and 10.14,for a point load P, Y = \$pz,

P

M, = 4-c p PZ’ z > o

Hence by superposition, Eq. (a), and Figure E10.3a, we have

10.3

INFINITE BEAM SUBJECTED TO A DISTRIBUTED LOAD SEGMENT

369

(b) Letting IP , I = IP , I = P,and multiplying Eq. (b) by 6/6, we get

- ( P 6 ) P Ap(z+S)-Apz 6

y = - [ 2k

]

Then letting 6 + 0 and P 6 +Mo in Eq. (d), we obtain, with the definition of the derivative,

S+O

or by Eqs. 10.17 and (e)

Similarly, by Eq. (c),we obtain

The functions for y and Mx are plotted in Figure E10.3b.

FIGURE E10.3b

10.3 INFINITE BEAM SUBJECTED TO A DISTRIBUTED LOAD SEGMENT 10.3.1 Uniformly Distributed Load The solution for the problem of a concentrated load at the center of an infinite beam on an infinite elastic foundation can be used to obtain solutions for distributed loads. Only segments of uniformly distributed loads are considered in this section. Consider an infinite

370

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

beam resting on an infinite elastic foundation and subjected to a uniformly distributed load w over a segment of length L‘ (Figure 10.7). The deflection, slope, bending moment, and shear of the beam can be determined with the solution presented in Section 10.2. Since the maximum values of these quantities generally occur within the segment of length L‘, we obtain the solution only in this segment. Consider an infinitesimal length Az of the beam within the segment of length L‘. In this segment, the beam is subjected to a uniformly distributed load w (Figure 10.7). Hence, a load A P = w Az acts on the element Az. We treat the load A P = w Az as a concentrated load and choose the origin of the coordinate axes under load AP. Next, consider any point H at distance z from the load A P = w Az; note that H is located at distances u and b from the left and right ends of segment L‘, respectively. The deflection AyH at H caused by the concentrated load A P = w Az is given by Eq. 10.11 with P = A P = w Az. Thus, we have

AyH = WAZPe-’z(cospz 2k

+ sinpz)

(10.22)

The total deflection yH caused by the distributed load over the entire length L’ is obtained by superposition. It is the algebraic sum of increments given by Eq. 10.22. Hence, by the integration process, we obtain

YH =

lim Az + 0 a

=

%e-”(

AYH b

cospz + sinpz)dz

0

+I %e-”(

cospz + sinpz)dz

0

(10.23)

Values of slope, bending moment, and shear at point H may also be obtained by superposition. These expressions may be simplified by means of Eqs. 10.16. Thus, we obtain the results

W

MH = -(B

4p2

+Bpb)

(10.26)

pa

Generally, the maximum values of deflection and bending moment are of greatest interest. The maximum deflection occurs at the center of segment L’. The maximum bending moment may or may not occur at the center of segment L’. In general, the location of the maximum bending moment depends on the magnitude of PL’.

10.3

INFINITE BEAM SUBJECTED TO A DISTRIBUTED LOAD SEGMENT

371

L’

AP = wAz

FIGURE 10.7 foundation.

10.3.2

Uniformly distributed load segment on an infinite beam resting on an elastic

/3L’Sw

For PL’ less than or equal to a,the data for Bpz in Table 10.2 indicate that the maximum bending moment occurs at the center of segment L’.

10.3.3

/3L’+a

As PL’ becomes large, 8+0,

M,+O,

V,+O,

and y + z k

(10.28)

everywhere, except near the ends of segment L’. The data in Table 10.2 indicate that the maximum bending moment occurs when either Pa or Pb is equal to n/4.

10.3.4

Intermediate Values of

/3 L’

For PL’ greater than n,the location of the maximum bending moment may lie outside of segment L‘. (See Problem 10.30 and Example 10.4.) However, the maximum moment value outside of segment L’ for the example problem is only 3.0% greater than the maximum bending moment within segment L’. The location of the maximum bending moment can be obtained by trial and error; however, because of the small difference, sufficient accuracy can be obtained by taking the location of the maximum moment to be n/(4P) from either end of the uniformly distributed load within length L‘.

10.3.5

Consider a distributed triangular load over a segment L’ of a beam on an elastic foundation (Figure 10.8).A load A P = W A Zacts on the element A z of the beam. We treat the load A P as a concentrated load and choose the origin of coordinate axes at a point H at distances a and b from the left and right ends of segment L‘. The deflection AyH at H caused by the load A P is given by Eq. 10.12, with P = A P = wAz. Hence,

where, by Figure 10.8, w = WO -(a-z), L’

over length a

372

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

AP = WAZ

YI

FIGURE 10.8 Triangular load over segment L' of an infinite beam on an elastic foundation.

and

w = WO -(a+z), L'

over length b

(c)

With Eqs. (a), (b), and (c), the total deflection at H is obtained by superposition:

Lo

0

0

0

I

Then, with the aid of Eqs. 10.17, integration yields YH =

wo 1 q'fF(cpa - Cpb - 2pL'Dpb + 4Pa)

(10.29)

In a similar manner, by Eqs. 10.13-10.16, we obtain

(10.30)

(10.31 )

(10.32)

EXAMPLE 10.4 uniform/y Distributed ~ o a d on a Segmentof a Wood Beam

A long wood beam (E = 10.0 GPa) has a rectangular cross section with a depth of 200 mm and width of 100 mm. It rests on a soil foundation. The spring constant for the foundation is k, = 0.040 N/mm3. A uniformly distributed load w = 35.0 N/mm extends over a length L' = 3.61 m of the beam (Figure E10.4~).Determine the maximum deflection, maximum flexural stress, and maximum pressure between the beam and foundation. Take the origin of coordinates at the center of segmentl'.

10.3

INFINITE BEAM SUBJECTED TO A DISTRIBUTED LOAD SEGMENT

373

L'

FIGURE E10.4

Solution

The magnitude of p is obtained by means of Eqs. 10.3 and 10.5. Thus, we find

k = bk, = lOO(0.040) = 4.00N/mm

p

=

'/&

2

= 0.001107 mm-'

=

4 l o x lo3 66.67 x 10 The magnitude of PL', needed to determine where the maximum bending moment occurs, is PL' = 0.001 107(3.61 x lo3) = 4.00. Since pL' is greater than n,the maximum bending moment does not occur at the center of segmentL'. With values of pa and p b = 4.00 - pa, values of the quantities y, 8, M,, and Vy under segment L' may be calculated by means of Eqs. 10.24, 10.25, 10.26, and 10.27 and the data from Table 10.2. These quantities are plotted in Figures 10.4, 10.4c, 10.4d, and 10.4e, respectively. Values are also shown for points in the beam outside the distributed load segment where p b = p (a + L') and a is the distance from H to the nearest edge of the distributed load (Figure E10.4~).Equations 10.25 and 10.27, for 0, and V,, respectively, are valid for points away from the distributed load; however, different equations are needed for yH and MH as indicated in Problem 10.30. The maximum deflection occurs at the center Ho of segment L', where pa = p b = 2.00. Equation 10.24, with Dpa = -0.0563 from Table 10.2, gives W 35 ymax = - ( l - D ) = -(1+0.0563) k pa 4

= 9.243mm

The maximum pressure between the beam and foundation occurs at the point of maximum deflection; thus, we find that the maximum pressure isp,,, = y,,,ko = 9.243(0.040) = 0.370 MPa. There are four

374

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

,

possible locations at which the largest bending moment may occur. They are located symmetrically with respect to the center of segment L'. Relative maximum bending moments occur at locations where V, = 0. From Table 10.2,we find that V, = 0 (Cpa= Cpb)when pa = 0.858 and p b = 3.142 and also when pa = 0.777 and p b = 4.777. These conditions locate the position of relative maximum bending moments inside segment L' and outside of segment L', respectively. However, the value of the largest bending moment is located outside of segment L' and is given by the equation indicated in Problem 10.30.Thus, we find (outside of segmentL')

-

35

[0.3223- (-O.O086)] = 2.363 kN m 4(0.001107)2

This value is 3% greater than the bending moment calculated by means of Eq. 10.26 with pa = 0.858 and p b = 3.142. In practice, this difference is not especially significant. The corresponding flexural stress is

If the maximum bending moment is assumed to occur at n/(4p) (see the text preceding Example 10.4),pa = z/4 and p b = 4 - n/4 (inside of segment L'). Substituting these values for pa and p b into Eq. 10.26, we find W

M , = -(Bpu+Bpb) 4d

=

35 [0.3224 + (-O.0029)] 4(0.001107)2

= 2.281 k N * m which is 3.5% less than the largest moment M,,, computed previously. Generally, the value MH for pa = n/4 and p b = PL' - nl4 gives a good approximation of M,,,.

10.4 SEMIINFINITE BEAM SUBJECTED TO LOADS AT ITS END A semiinfinite beam resting on an infinite linearly elastic foundation is loaded at its end by a concentrated load P and positive bending moment M , (Figure 10.2). The boundary conditions that determine the two constants of integration C3 and C4 in Eq. 10.7 are = -M,

dz

z=o

(10.33)

Substitution of Eq. 10.7 into these boundary conditions yields two linear equations in C3 and C4. Solving these equations for C3 and C4, we obtain

10.4

SEMIINFINITE BEAM SUBJECTED TO LOADS AT ITS END

P2M, c, = 27 , c , = 2pp -k - c,

375

(10.34)

Substituting these into Eq. 10.7, we find

Values of slope, bending moment, and shear are obtained by substitution of Eq. 10.35 into Eqs. 10.1. These equations are simplified with the definitions given by Eqs. 10.16. Thus, we have (10.36)

(10.37)

P M , = - - Bp

Pz

+ M0 APz

VY = - P C p z - 2M,pBpz

(10.38) (10.39)

These results are valid, provided that the beam is attached to the foundation everywhere along its length.

EXAMPLE 10.5 I-Beam Loaded at Its End

A steel I-beam (E = 200 GPa) has a depth of 102 mm, width of 68 nun, moment of inertia of I, = 2.53 x lo6mm4, and length of 4 m. It is attached to a rubber foundation for which k, = 0.350 N/mm3. A concentrated load P = 30.0 kN is applied at one end of the beam. Determine the maximum deflection, maximum flexural stress in the beam, and the location of each.

Solution

The spring coefficient k is equal to the product of the beam width and the elastic spring constant k, for the foundation; that is, k = 68(0.350)= 23.8 N/mm2. From Eq. 10.5, we find that

Since

L = 4000mm > 3n -= 3n = 2540 mm 2p 2(0.001852) the beam can be considered to be a long beam. Values for deflection y and moment M , are given by Eqs. 10.36 and 10.38, respectively. The maximum deflection occurs at the end where load P is applied, since Dp, is maximum where pz = 0. The maximum moment occurs at z = n/4p, where Bpz is a maximum. Thus. the maximum deflection is

376

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

I The location of ymaxis at M,,

z = 0. The maximum moment is

= --0.3224P -

P

- 0.3224(30,000) = -5.22

I

and, therefore, the maximum stress is

I

is at z = n/4P = 424 mm. The location of omax

Id\J.

0.001852

10.5 SEMIINFINITE BEAM WITH CONCENTRATED LOAD NEAR ITS END The solution for a semiinfinite beam resting on an infinite linearly elastic foundation with a concentrated load P near its end may be obtained from the solutions presented in Sections 10.2 and 10.4. Consider a beam subjected to load P at distance a from its end (Figure 10.9~). Let the beam be extended to infinity to the left as indicated by the dashed line. For the beam so extended, Eqs. 10.14 and 10.15 give magnitudes for Mx(z= -a) = PCpa/(4P) and VyCz = PDpa/2 at distance a to the left of the origin (Figure 10.9~). Now let the beam be loaded at the left end (Figure 10.9b),by loads Q and M with magnitudes (10.40)

Since the origin of the coordinate axes is distance a to the right of the loaded end, the deflection and bending moment for this loading are given by Eqs. 10.36 and 10.38, respectively, if the coordinate z is replaced by (a + z). Superposing the two loadings for the two beams in Figure 10.9 cancels the moment and shear at the left end. Thus, superposition of the two results yields the solution for a semiinfinite beam loaded by a concentrated load P at distance a from the left end. Using Eqs. 10.12, 10.36, and 10.40,we obtain the deflection y for z 2 -a. Thus, we find the following formula for y:

(b)

FIGURE 10.9 Semiinfinite beam on an elastic foundation loaded near its end.

SHORTBEAMS

10.6

y =

gbZ +

+

377

(10.41)

CpuCp(u+ z ) ]

Similarly,Eqs. 10.14, 10.38, and 10.40 give the bending moment M, for z 2 -a as follows: Mx =

P --[c - q 3 a q 3 ( a + z) - CpaAp(a + z ) ] 4 p pz

(10.42)

Since the quantities Apz and Cpzin Eqs. 10.41 and 10.42 are symmetrical in z, for negative values of z (4I z I 0),we use the conditionsApZ(-z) = Apz(z)and Cp,(-z) = Cpz(z).

EXAMPLE 10.6 I-Beam Loaded near One End Solution

Let the load in Example 10.5 be moved to a location 500 mm from one end of the beam. Determine the maximum deflection, the maximum flexural stress in the beam, and the location of each.

From Example 10.5,k = 23.8 N/mm2 and p = 0.001852 m - l . The deflection y and bending moment = 0.001852(500) = 0.9260, Table 10.2 gives Cpa= -0.0782 and Dpa = 0.2383. Hence,

M, are given by Eqs. 10.41 and 10.42. Since /3a

PP y = --[A 2k pz + 2DpaDp(a + 2) + CpaCp(a+ z)] = 1.1672[Apz+ 0.4766Dp(,

P

Mx = \$Cpz

- 2Dpa’p(a + z)

+

z)

- O.O782Cp(, z,] +

- CpaAp(a+ 2 9

= 4,050,000[Cp2- 0.4766Bp(,

+

z)

+ 0.0782Ap(,

+

z)]

By trial and error, it is found that the maximum deflection ymaxoccurs at 424 mm from the end of the beam, where z = -76 mm [pz = 0.1408 and p(u + z) = n/4 = 0.78541. From Table 10.2, Apz = 0.9816, DpC0 + z ) = 0.3224, and Cpca+ z ) = 0. Thus, Y,,

= 1.1672[0.9816+ 0.4766(0.3224) -0.0782(0)] = 1.3251 mm

By trial and error, it is found that the maximum bending moment M,, occurs at 500 mm from the end of the beam [Pz = 0 and p(u + z) = 0.92601. From Table 10.2, Cpz= 1.0000,Apca+ z ) = 0.5548, and Bpca z) = 0.3165. Hence, +

M,,

= 4,050,000[ 1.oooO - 0.4766(0.3165) + 0.0782(0.5548)] = 3,615,000N*mm

and, therefore,

10.6 SHORT BEAMS The solutions that have been presented in the foregoing sections are good approximations for a beam supported by an elastic foundation and with a length greater than 3 ~ / ( 2 p ) . , short beams, special However, for beams whose lengths are less than 3 ~ / ( 2 p ) so-called

378

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

solutions are required. The reader is referred to the book by M. Hetknyi (1946) for a solution applicable for short beams. For the special case of a concentrated load located at the center of a short beam, the maximum deflection ymax and maximum bending moment Mmaxoccur under the load; their magnitudes are given by the following equations:

- P p coshpL + cospL + 2 - E sinhpL + sinpL

(10.43) (10.44)

in which L is the length of the beam. Magnitudes of the deflection y and bending moment M, for other locations of the concentrated load are beyond the scope of this book. However, solutions have been calculated for several load locations for three short beams and one long beam. The results are presented in Figure 10.10. Design tables for finite-length beams with free ends on a Winkler foundation have been given by Iyengar and Ramu (1979).The cases of simply supported ends and clamped ends may be treated by appropriate superposition techniques. A solution for finite-length beams with elastic end restraints on a Winkler foundation has been given by Ting (1982). This solution can be used to simulate a beam on elastic foundations with various boundary conditions, including initial settlement of an end of the beam. The effect of other structural members connected to a beam on a Winkler foundation can also be assessed by using proper values of the elastic end restraints. The solution is in a form that can be coded easily into computer language.

10.7 THIN-WALL CIRCULAR CYLINDERS The concept of a beam on an elastic foundation may be used to approximate the response of thin-wall circular cylinders subjected to loads that are rotationally symmetrical (Figure 10.11). We use cylindrical coordinates r, 6, z for radial, circumferential, and axial directions. The dimensions of a long thin-wall cylinder may be represented by the mean radius a and wall thickness h. Let a long thin-wall cylinder be subjected to a ring load w having units N/mm, where the length dimension is measured in the circumferential direction. We show that the response of the cylinder is similar to that of a corresponding beam on an elastic foundation subjected to a concentrated load at its center (Section 10.2). In developing an analogy between a thin-wall circular cylinder and a beam on an elastic foundation, we specify the analogous beam and elastic foundation as follows: Cut a longitudinal strip from the cylinder of width a A 6 (Figures 10.12a and 10.12b). For convenience let the width a A 6 be unity. We consider this strip of length L and width a A 6 = 1 as a beam. We consider the remainder of the cylinder to act as the elastic foundation. The spring constant k for the elastic foundation is obtained by imagining the open-ended cylinder to be subjected to an external pressure p 2 . This pressure p 2 produces a uniaxial state of stress for which the only nonzero stress component is oee= ap2/h. Hence, by Hooke’s law, the circumferential strain is eee = oee/E. In turn, by strain-displacement relations, we can express eee in terms of the radial displacement u as follows (see Eqs. 2.85): (10.45)

n

4

2

4

-1.2

-1 .o -0.8 -0.6 -0.4 Mx -0.2 P l o 0.0 +0.2 +0.4 +0.6

+0.8 +1.0 -1.0

I I

1

1

1

0.0

B

+1.0 ~

PPI(2k) +2.0

I L=4 P

Load at left end I

1

1

1

(4 FIGURE 10.10 Bending moment diagrams and deflection curves for a short beam on elastic supports subjected to a concentrated load located as shown on each curve. The ends of the beams are unrestrained (free). ( a )Span = 2 / p . ( b ) Span = 3/p. (c) Span = 4/p. ( d ) Span = 5/p.

Since u is constant along the length of the cylinder, the magnitude of k is given by Eq. 10.28 where u replaces y and w = pz(aA8)= p 2 , since aA 8 = 1. Hence, we have

(10.46)

380

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

w [N/rnrnl

FIGURE 10.11 Ring load on a thin-wall cylinder.

FIGURE 10.12 Thin-wall cylinder.

Note that the narrow strip (Figure 10.12b), which represents the beam on an elastic foundation, has a different state of stress (and strain) than other beams considered in this chapter. The beam in Figure 10.1 was assumed to be free to deform in the x direction, thus developing anticlastic curvature (Boresi and Chong, 2000). Each of the two sides of the beam in Figure 10.12b lies in a radial plane of the cylinder; these sides are constrained to lie in the same planes after deformation much like a flat plate (see Chapter 13). Therefore, since the beam cannot deform anticlastically,EZx in Eq. 10.5 must be replaced by

D =

Eh3 12( 1 - v2)

[see Eq. (f) of Example 3.11. Replacing EZx by D and using Eq. 10.46, we express p in the form

P=

(10.47)

With the value of p given by Eq. 10.47, the solutions for all of the loadings considered in Sections 10.2-10.5 are applicable for thin-wall circular cylinders subjected to circumferential line loads. They may also be used to obtain estimates of the response of a thin-wall cylinder subjected to rotationally symmetric loads that vary along the axis of the cylinder.

10.7

THIN-WALL CIRCULAR CYLINDERS

381

Note: The analogous elastic foundation for the strip taken from a thin-wall circular cylinder is very stiff compared to the usual elastic foundation. Hence, the analogy is applicable even for a cylinder with length less than the radius a. If we assume that v = 0.30, the minimum length L for which the analogy is applicable is L =

!?.

= 3.67~

2P

= 0 . 8 2 ~for - = a 20

(10.48)

Generally for thin-wall cylinders, hla is less than 1/20, and the length L of the cylinder influenced by the concentrated ring load is less than 0.82~.Often, the beam analogy can be employed to obtain estimates of the response of noncylindrical circular shell segments (for instance, conical shells) if the change in radius for a given length L is small compared to the average radius a in the length L.

EXAMPLE 10.7 Stresses in c Storage Tanl

A closed-end thin-wall cylinder is used as an oil storage tank that rests on one of its ends (see Figure E10.7). The tank has a diameter of 30 m, depth of 10 m, and wall thickness of 20 mm. The tank is made of steel for which E = 200 GPa and v = 0.29. Determine the maximum shear stress in the tank if it is filled with oil having a mass density of 900 kg/m3. Consider the following different conditions:

(a) Assume that the bottom of the tank does not influence the circumferential stress in the cylindrical walls. (b) Assume that the radial displacement of the junction between the cylinder and bottom remains zero during loading and that the bottom has infinite rotational stiffness. (c) Assume that the radial displacement of the junction between the cylinder and bottom remains zero and that the bottom plate is sufficiently flexible that the moment at the junction can be considered to be zero.

(a)

FIGURE E10.7

Solution

Thin-wall cylinder oil storage tank.

(a) Choose cylindrical coordinates r, 8,and z. The pressure in the cylinder increases linearly with depth. If the bottom does not exert moments or radial forces on the cylinder walls, wall AB in Figure and E 1 0 . 7 ~deforms into the straight line A*B*. The stresses in the cylinder walls at B* are or,.,oOB, oz2. The radial stress or,.and longitudinal stress ozzat the bottom are small and are neglected comBy the solution for thin-wall cylinders, we find pared to the circumferential stress ooo. Dee =

p a - (10 x 103)(9.807)(900 x W 9 ) ( 15 x lo3) = 66.20 Mpa -h 20

382

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

The maximum shear stress, given by Eq. 2.39,is

(b) In part (b) the bottom of the tank is assumed to have infinite stiffness. As indicated in Figure

E10.76,the bottom prevents both a radial displacement and a change in slope of the cylinder wall at B. Although the cylinder is not uniformly loaded, we consider it to be a uniformly loaded long cylinder with a ring load w applied at its center. The cylinder center is taken as the junction between the cylinder and bottom, and it is cut at this line load. Hence, the bottom of the tank produces a ring load w/2on the upper half of the long cylinder and bending moment to prevent rotation of the cut section. The associated magnitudes of k and p are given by Eqs. 10.46 and 10.47.Thus, we find

Since the cylinder is subject to internal pressure from the oil, it is not uniformly loaded as assumed in the proposed solution. For the analogy to be valid, the minimum uniformly loaded length (Eq. 10.48) needs to be

L ' = L- = - 3K =

2

'

'

4p

3K

4(0.0235)

= 1003mm

which correspondsto the distancell in Figures 10.7~ and 10.76.Thus, only 10% of the cylinder height needs to be unifody loaded; the variation of pressure over this height is considered small enough to be neglected. The radial displacementu of the walls of the cylinder away from end effects is given by Q. 10.45as

Since the radial displacement of the bottom plate of the tank is assumed to be zero, the ring load w causes a radial displacement inward of 4.965mm. The magnitude of w is obtained by substituting the known value of u (equal toy) into Eq. 10.12for p z = 0. Hence, by

we find

w = 75.21 N/mm The maximum bending moment is given by Eq. 10.14for p z = 0. Thus, we obtain

M,, and

=

w -- 75'21 = 8001 N 4p 4(0.00235)

10.7

THIN-WALL CIRCULAR CYLINDERS

383

The radial stress or,is small and is neglected. Since the radial displacement of the cylindrical wall at the bottom is the same as for the unloaded cylinder, the average value of through the wall thickness is zero. However, because of bending, the ratio of 0 0 0 to CT, is proportional to Poisson's ratio [see Eq. (a) of Example 3.11. Therefore, o~~(~ = ,~ )

o ~ ~= (0.29(120.0) ~ , ) = 34.8 MPa

The maximum shear stress at the junction between the bottom of the tank and cylindrical walls of the tank is

which is 81% greater than that found in part (a). The radial displacement u for the junction between the bottom of the tank and cylindrical walls of the tank has been neglected. However, its magnitude may be computed by the following relation:

'bottom

-

w( 1 - v)a 75.21(0.71)(15 x lo3) = o.loo 2 ~ h 2(2oo x 103)(20)

This value is only 2%of the displacement of the unrestrained cylinder wall.

(c) If the bending moment at the junction of the cylindrical walls and tank bottom is zero, the thinwall cylinder can be treated as a beam on an elastic foundation loaded at one end. The bottom of the tank is assumed to prevent a radial displacement as indicated in Figure E10.7~.Let w be the ring load produced by the bottom of the tank. The radial displacement u is given by Eq. 10.36 for pz = 0:

w = 18.80N/mm The maximum moment occurs at a distance z/(4p) = 334 mm from the bottom and has a magnitude given by Eq. 10.38:

This bending stress causes a circumferential stress CTee1. which is part of the resultant circumferential stress:

creel =

~

c

T

= ~0.29(-38.69) ~ ( ~ = -11.22 ~ ~ MPa

Another part of the circumferential stress 0062 comes from the fact that the maximum bending stress occurs at a location (pz = z/4) where the displacement is not maximum. The radial displacement given by Eq. 10.36 is

Since UeO(max)= 66.20 Mpa is the uniform circumferential stress in the thin-wallcylinder when u = 0, the average circumferential stress for u = 0 . 3 2 2 4 is ~~~~

cee2 = ( 1 - 0 . 3 2 2 4 ) ~ ~ e e ( ~=, )0.6776(66.20)

= 44.86 Mpa

384

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

The circumferential stress at the point where ozz(min) occurs is nee = oee,+ oee2= - 11.22 + 44.86 = 33.64 MPa and %lax =

Omax - Omin

2

-

33.64 - (-38.69) = 36.17 MPa 2

which is 9% greater than the value found in part (a). If the maximum shear stress criterion of failure is used, the maximum shear stress indicates the severity of the loading conditions. If the bottom of the tank is rigid (one limiting condition), the maximum shear stress is 8 1% greater than that for unrestrained cylindrical walls. If the bottom does not offer any resistance to bending (a second limiting condition), the shear stress is 9% greater than that for unrestrained cylindrical walls. The actual condition of loading for most flat-bottom tanks would be between the two limiting conditions but nearer to the condition of a rigid bottom. Some experimental measurements of the stresses, in what is reportedly the world’s largest welded steel waterstorage tank, have been given by James and Raba (1991).

PROBLEMS Section 10.2

10.1. By the method used in Example 10.3, derive formulas for the slope 8 and the shear Vy of the beam.

10.8. Solve Problem 10.7 if the steel beam is replaced by an aluminum alloy beam for which E = 72.0 GPa.

10.2. By differentiation of the deflection y obtained in Example 10.3, derive formulas for the slope 8 and the shear Vyof the beam. 10.3. Verify the derivation of Eqs. 10.17. 10.4. Use Eqs. 10.17 to verify Eqs. 10.13-10.15. 10.5. Show that the functions Apz,Bpz, Cpz,and Dpz of Eqs. 10.16 are further related by the formulas

10.9. An infinitely long beam rests on an elastic foundation and is loaded by two equal forces P spaced at a distance L. The beam has bending stiffness EI and the foundation has a spring constant k.

-3 = 2P 2Ap,, d‘D 2= 2P2Bpz

dLC

dz2

dz2

10.6. The ballast and roadbed under railroad rails may vary appreciably from location to location. If the magnitude of k is 50% less than the value in Example 10.1, determine the percentage increase in the maximum deflection and maximum bending moment for the rail for the same wheel load. 10.7. A steel I-beam (E = 200 GPa) has a depth of 127 mm, width of 76 mm, moment of inertia of I, = 5.12 x lo6 mm4, and length of 4 m. It rests on a hard rubber foundation. The value of the spring constant for the hard rubber is ko = 0.270 N/mm3. If the beam is subjected to a concentrated load, P = 60.0 kN, at the center of the beam, determine the maximum deflection and maximum flexural stress at the center of the beam.

a. Find the distance L such that the deflection y under one of the

forces is the same as the deflection midway between the two forces. b. For unit values of P, EI, and k, and with the origin midway between the two forces, write an expression for the deflection y as a function of position z. Evaluate your expression for deflection at z = f L / 2 . c. Plot the expression derived in (b) over the domain - 4.0 I P z I4.0.

10.10. A steel train rail (E = 200 GPa) has moment of inertia I = 36.9 x lo6 mm4 and rests on a subgrade with k = 14.0 N / m * . Find the maximum wheel spacing for the train such that the rail never lifts from the subgrade between any two sets of wheels. 10.11. A heavy machine has a mass of 60,000 kg. Its mass center is equidistant from each of four ground supports located at the four comers of a square 1.5 m on a side. Before it is moved to its permanent location, temporary support must be designed to hold the machine on a level horizontal surface on the ground. The surface layer of the ground is silt above a thick layer of inorganic clay. By the theory of soil mechanics, it is estimated that the spring constant of the soil is ko = 0.029 N/mm3. The machine is placed centrally on two long timber beams

PROBLEMS

( E = 12.4 GPa) that are 200 mm wide and 300 mm deep. The beams are parallel to one another, with centers 1.50 m apart. Determine the maximum deflection of the beams, maximum flexural stress in the beams, and minimum required length L for the beams.

10.12. A 60-kN capacity hoist may be moved along a steel I-beam (E = 200 GPa). The I-beam has a depth of 152 mm and moment of inertia I, = 11.0 x lo6 mm4. The beam is hung from a series of vertical steel rods (E = 200 GPa) of length 2.50 m, of diameter 18.0 mm, and spaced 500 mm center to center.

385

10.16. A long 40-mm diameter steel beam (E = 200 GPa) is supported by a number of semicircular curved beams. (See end view in Figure P10.16.) The curved beams are spaced along the beam with spacing 1 = 550 mm. Each curved beam is made of steel, has a circular cross section of diameter 30 mm, and has a radius of curvature R = 300 mm. A load P = 3.00 W is applied to the center of the long beam located at one of the curved beams. Determine the maximum stress in the long beam and curved beams.

a. For capacity load at the center of the beam, located under one of the rods, determine the maximum stress in the beam and the rods. b. Does 1 satisfy Eq. 10.20? 10.13. After installation of the I-beam of Problem 10.12, it becomes necessary to lower the I-beam 800 mm. This was done by adding 18.0-mm diameter aluminum alloy bars (E = 72 GPa) of length 800 mm to the steel bars. For a 60-kN load at the center of the beam located under one of the composite bars, determine the maximum stress in the beam and the rods. 10.14. A long wood beam (E = 12.4 GPa) of depth 200 mm and width 60 mm is supported by 100-mm rubber cubes placed equidistant along the beam at 1 = 600 mm. The cube edges are parallel and perpendicular to the axis of the beam. The rubber has a spring constant of k, = 0.330 N/mm3. A load P is applied to the center of the beam located over one of the rubber cubes. a. If the wood has a yield stress of Y = 40.0 MPa, determine the magnitude of P based on a factor of safety SF = 2.50. What is the maximum pressure developed between the rubber and beam? b. Does 1 satisfy Eq. 10.20? 10.15. A long 50-mm diameter steel bar (E = 200 GPa and Y = 300 MPa) is supported by a number of pairs of 2-mm diameter high-strength steel wires (E = 200 GPa and Y = 1200 m a ) . An end view of the beam and wires is shown in Figure P10.15. The pairs of wires are equally spaced at 1 = 900 mm. A load P is applied to the center of the long beam at the same location as one pair of wires. a. Determine the magnitude of P if both the beam and wires are designed with factor of safety SF = 2.00.

P

FIGURE P10.16

10.17. The beams in Figure P10.17 are steel I-beams (203 mm deep, I, = 24.0 x lo6 mm4, and E = 200 GPa). If a load P = 90.0 kN is applied to the center of the long beam located over one of the cross beams, determine the maximum flexural stess in the long beam and cross beams. l = 600 mm

u

b. Does 1 satisfy Eq. 10.20? FIGURE P10.17

10.18. Let the curved beams in Problem 10.16 be made of an aluminum alloy (E = 72.0 GPa). Determine the maximum stress in the long beam and curved beams.

t

P

FIGURE P10.15

10.19. Let the long beam in Problem 10.17 be made of an aluminum alloy ( E = 72.0 GPa). Determine the maximum flexural stress in the long beam and cross beams. 10.20. For the beam on a linearly elastic foundation shown in Figure 10.1, replace the concentrated load P by a concentrated

386

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

(counterclockwise) moment M, at point 0. The beam has bending stiffness EZ and the foundation has a spring constant k (force/area). Derive analytical expressions for the deflected

shape y(z), rotation 8(z), internal moment M(z), and internal shear V(z). Sketch each of the four expressions as is done in Figure 10.1 (see Example 10.3).

Section 10.3

10.21. Consider a beam of infinite length, on an elastic foundation, subjected to a uniform load w [F/L] over its entire length. By the method of superposition, determine the displacement, slope, moment, and shear of the beam. 10.22. A beam of infinite length is attached to an elastic foundation and is subjected to a distributed load w(z) [F/L] over a segment L' of the beam (Figure P10.22~2).Consider an element dz of the beam in the loaded region (Figure P10.22b). Derive the equilibrium conditions for the element and show that

the second moment of area I, of the beam required to meet the allowable distributed force.

60 Nlmm

+ + + + + + + t iJ 1 Beam stiffness = Elv

I

I

I

-

I

-

I

Foundation stiffness = k

(a) Note that w(z) = 0 outside the segment L', and then Eq. (a) reduces to Eq. 10.4. Note also that the solution of Eq. (a) consists of a particular solution y p and a general solution yh. The particular solution is any function yp(z) that satisfies Eq. (a). The general solution is the solution of the homogeneous equation EZx(d4y/dz4)+ ky = 0, that is, Eq. 10.6. If w(z) is a simple function, say a polynomial, a trigonometric, or an exponential function, the particular solution is a displacement y , of the same form.

L Y

'

FIGURE P10.23

10.24. In Problem 10.23, let the uniform load be w [F/L] and the maximum allowable distributed force in the foundation be pmax= 4 8 . In terms of k, I, and E, determine the second moment of area I, of the beam. 10.25. An infinite beam on an elastic foundation is subjected to a triangular load over the segment L' = 4 m. Determine the values of y and M, at point A (see Figure P10.25). Use E = 200 GPa, I, = 80 x lo6 mm4, and k = 8.0 N/mm2.

4

Foundation stiffness = k

Foundation stiffness = k

(a)

FIGURE P10.25

Mx

3 -+

+

dM,

? "

b dz (b)

FIGURE P10.22

10.23. An infinite beam on an elastic foundation is loaded uniformly over a segment 1 (Figure P10.23). The maximum allowable distributed force in the foundation at the center of the loaded segment is 15 N/mm. In terms of k, 1, and E, determine

10.26. In Problem 10.25, determine the values of 8 and Vy at point B. 10.27. In Problem 10.25, determine the values of M, and Vy under the centroid C of the triangular load. 10.28. Let the load of 60.0 kN in Problem 10.7 be uniformly distributed over a length of 1.00 m. Determine the maximum deflection and maximum flexural stress in the beam. 10.29. The long wood beam in Problem 10.14 is subjected to a distributed load w over length L' = 3.00 m. Determine the magnitude of w based on a factor of safety SF = 2.00. 10.30. Show that, for point H located outside segment L' (Figure E10.4), the following equations are valid: YH = W(Dp, - Dgb)/2k and MH = --W @pa - Bpb)/(4p2)

PROBLEMS

387

Section 10.4

10.31. Let load P be moved to one end of the beam in Problem 10.7. Determine the maximum deflection and maximum flexural stress in the beam and give the location of the maximum flexural stress. 10.32. Let the hoist in Problem 10.12 be moved to one end of the beam. Each rod supporting the I-beam is a spring exerting an influence over length 1. If the end of the beam is 1/2 = 250 mm from the nearest tension rod, determine the maximum stress in the rods and beam. 10.33. A long rectangular section brass beam (E = 82.7 GPa) has a depth of 20 mm and a width of 15 mm and rests on a hard rubber foundation (Figure P10.33). The value of the spring constant for the hard rubber foundation is 0.200 N/mm3. If the beam is subjected to a concentrated load P = 700 N at the location shown, determine the maximum deflection of the beam and maximum flexural stress in the beam. 10.34. Solve Problem 10.33 forb = 200 mm. 10.35. In Problem 10.33 determine the value of b for which the slope at A is zero. 10.36. A steel I-beam (depth = 102 mm, I, = 2.53 x lo6 mm4, and E = 200 GPa) is long and supported by many springs (K = 100 N/mm) spaced at distance 1 = 500 mm center to center

FIGURE P10.33

along the beam. A load P = 3.50 kN is applied to the left end of the beam at a distance of 2.00 m from the first spring. Determine the maximum flexural stress in the beam and maximum tension load and maximum compression load in the springs. Hint: Mo = -P(2000 - 1/2).

10.37. Solve Problem 10.36 for the case where the steel beam is replaced by an aluminum alloy beam for which E = 72.0 GPa. 10.38. a. In Problem 10.36 show that the spring spacing is sufficiently small to justify the analysis as a beam on an elastic foundation. b. In terms of the functions Cpz and Dpz from Eq. 10.16, derive a formula for the deflection y of the beam.

Section 10.5

10.39. Let the load P = 60.0 kN in Problem 10.7 be moved to one of the quarter points in the beam. Determine the maximum deflection and maximum flexural stress in the beam and locations for each. 10.40. Let the load P = 60.0 kN in Problem 10.7 be moved to a location 500 mm from one end of the beam. Determine the maximum deflection and maximum flexural stress in the beam and locations for each. 10.41. Let the hoist in Problem 10.12 with a capacity load of 60kN be located under the second rod from one end. Since each spring is assumed to exert an influence over a length I = 500 mm, the load acts at distance a = 750 mm from the end of the beam. Determine the maximum deflection of the beam, maximum flexural stress in the beam, maximum stress in the rods, and locations for each.

10.42. Let the hoist in Problem 10.12 with a capacity load of 60 kN be located under the first rod from one end. Since each spring is assumed to exert an influence over a length 1 = 500 mm, the load acts at distance a = 250 mm from the end of the beam. Determine the maximum deflection of the beam, maximum flexural stress in the beam, maximum stress in the rods, and locations for each. 10.43. A four-wheel car runs on steel rails (E = 200 GPa). The rails have a depth of 120 mm. The distance from the top of a rail to its centroid is 69 mm, and its moment of inertia is 17.07 x lo6 mm4. The rail rests on an elastic foundation with spring constant k = 12.0 N/mm2. The two wheels on each side of the car are spaced 2.50 m center to center. If each wheel load is 80.0 kN, determine the maximum deflection and maximum flexural stress when a car wheel is located at one end of the rail and the other car wheel on the same rail is 2.50 m from the end.

Section 10.6

10.44. A steel I-beam (E = 200 GPa) has a length of L = 3.00 m, depth of 305 mm, flange width of 129 mm, and moment of inertia I, = 95.3 x lo6 mm4. The beam rests on a hard rubber elastic foundation whose spring constant is ko = 0.300 N/mm3. If the beam is subjected to a concentrated load P = 270 kN at its center, determine the maximum deflection and maximum flexural stress in the beam.

10.45. The magnitude of p L for the beam in Problem 10.44 is 2.532. Determine the maximum deflection and maximum flexural stress in the beam if the load is moved to one end of the beam. Use linear interpolation with the curves in Figure 10.10.

388

CHAPTER 10 BEAMS ON ELASTIC FOUNDATIONS

Section 10.7 10.46. A steel (E = 200 GPa and v = 0.29) thin-wall cylinder has an inside diameter of 40 mrn and a wall thickness of 1 mm. The cylinder may be considered fixed where it enters the stiffened end of a pressure vessel. The residual stress of installation may be considered negligible. Determine the bending stresses resulting from an internal pressure of 3 MPa. 10.47. A thin-wall cylinder is made of an aluminum alloy (E = 72.0 MPa and v = 0.33), has an outside diameter of 1 m, and has a wall thickness of 5 mm. A split ring with square cross section 20 mm on a side is tightened on the cylinder until the stress in the split ring is 100 MPa. Assume that the split ring applies two line loads separated by the 20-mrn dimension of the ring. Determine the principal stresses at the inner radius of the cylinder below the centerline of the split ring. 10.48. Let the split ring in Problem 10.47 be rounded on the inside surface so as to apply a line load at the center of the ring. Determine the maximum principal stresses at the inner radius of the cylinder.

10.49. A closed-end steel cylinder (E = 200 GPa and v = 0.29) has an inside radius a = 2.00 m, wall thickness h = 10 mm, and hemispherical ends. Since the state of stress is different for the cylinder and the hemisphere, their radial displacements will be different. Show that the length L/2 (see Eq. 10.48) is small compared to a so that the short length of the hemisphere can be considered another cylinder. Determine the shear force w in terms of internal pressure p , at the junction of the cylinder and hemisphere (assumed to be another cylinder). Note that the bending moment at the junction is zero because of symmetry. Determine the maximum in the cylinder, axial stress o,,, and bending stress ozz(bending) circumferential stress o,, at the outside of the cylinder at the location where the maximum bending stress occurs and the ratio of the maximum shear stress at that location to the maximum shear stress in the cylinder at a distance far from the junction.

~

BORESI,A. P., and CHONG,K. P. (2000). Elasticity in Engineering Mechanics, 2nd ed. New York: Wiley-Interscience. BOWLES, J. E. (1995). Foundation Analysis and Design, 5th ed. New York: McGraw-Hill. HET~NYI, M. (1946). Beams on Elastic Foundations. Ann Arbor: Univ. of Michigan Press. IYENGAR, K. T. S. R., and RAMU,S. A. (1979). Design Tables for Beams on Elastic Foundations and Related Problems. London: Elsevier Appl. Sci. F’ubl., Ltd. JAMES,R. W., and RABA,G. W. (1991). Behavior of Welded Steel Water-Storage Tank.J. Structural Eng., 117(1): 61-79. J. (1977). The Vlasov Foundation JONES,R., and XENOPHONTOS, Model. Int. J.Mech. Sci., 19(6): 317-324. KERR,A. D. (1964). Elastic and Viscoelastic Foundation Models. J. Appl. Mech., Trans. ASME, 31, Series E (3): 491498.

LANGHAAR, H. L. (1989). Energy Methods in Applied Mechanics. MelKreiger. bourne, n. SCOTT,R. F. (1981). Foundation Analysis. Englewood Cliffs, NJ: Prentice Hall. SELVADURAI, A. P. S. (1979). Elastic Analysis of Soil Foundation Interaction. London: Elsevier Appl. Sci. Publ., Ltd. TING, B.-Y. (1982). Finite Beams on Elastic Foundation with Restraints. J.Structural Div., 108(ST 3): 61 1-621. VALLABHAN, C. V. G., and DAS, Y. C. (1988). Parametric Study of Beams on Elastic Foundations. ASCE J. Eng. Mech., 114(12): 2072-2082. WESTERGAARD, H. M. (1948). New Formulas for Stresses in Concrete Pavements of Airfields. Trans. Am. Soc. Civil Eng. 113: 425-444.

CHAPTER

I1

THE THICK-W M L CYLINDER 11.I BASIC RELATIONS In this section, we derive basic relations for the axisymmetric deformation of a thick-wall cylinder. Thick-wall cylinders are used widely in industry as pressure vessels, pipes, gun tubes, etc. In many applications the cylinder wall thickness is constant and the cylinder is subjected to a uniform internal pressure pl, a uniform external pressurep2, an axial load P, and a temperature change AT (measured from an initial uniform reference temperature; see Section 3.4) (Figure 11.1).Often the temperature change AT is a function of the radial coordinate r only. Under such conditions, the deformations of the cylinder are symmetrical with respect to the axis of the cylinder (axisymmetric). Furthermore, the deformations at a cross section sufficiently far removed from the junction of the cylinder and its end caps (Figure 1 1.1) are practically independent of the axial coordinate z. In particular, if the cylinder is open (no end caps) and unconstrained, it undergoes axisymmetric deformations owing to pressures p1 and p 2 and temperature change AT = AT(r), which are independent of z. If the cylinder’s deformation is constrained by supports or end caps, then in the vicinity of the supports or junction between the cylinder and end caps, the deformation and stresses will depend on the axial coordinate z. For example, consider a pressure tank formed by welding together hemispherical caps and a cylinder (Figure 11.2). Under the action of an internal pressure pl, the tank deforms as indicated by the dotted inside boundary and the long dashed outside boundary (the deformations are exaggerated in Figure 11.2). If the cylinder were not constrained by the end caps, it would be able to undergo a larger radial displacement. However, at the junctions between the hemispherical caps and cylinder, the cylinder displacement is constrained by the stiff hemispherical caps. Consequently, the radial displacement (and hence the strains and stresses) at cylinder cross sections near the end cap junctions differs from those at sections far removed from the end cap junctions. In this section, we consider the displacement, strains, and stresses at locations far removed from the end caps. The determination of deformations, strains, and stresses near the junction of the thick-wall end caps and the thick-wall cylinder lies outside the scope of our treatment. This problem often is treated by experimental methods, since its analytical solution depends on a general three-dimensional study in the theory of elasticity (or plasticity). For thin-wall cylinders, the stress near the end cap junctions may be estimated by the procedure outlined in Section 10.7 (see Problem 10.49). Consequently, the solution presented in this chapter for thick-wall cylinders is applicable to locations sufficiently far from the end cap junctions where the effects of the constraints imposed by the end caps are negligible. The solution is also applicable to thick-wall cylinders that do not have end caps, so-called open cylinders. Since only axially symmetrical loads and constraints are admitted, the solution is axisymmetrical, that is, a function only of radial coordinate r.

389

390

CHAPTER 11 THE THICK-WALL CYLINDER

e

Y

4

...................... 4-

I I I

4

P2 ---t

P

-

+ + 4 4

P2

I' I1

Cylinder

b

c c

L - f - f - f - f - f - f - f ' r f ~ ' ~ - ~ - ~II End -~-f-~-~~

End cap

+ P2

a I

0 I

-I

- : 1l

p* z

I cap

+

I

+

4

P

4 I_I_I_L_L-L~-~-.J_~_1-1_~_1_1_ I c

Welded junction y c between end cap ;I and cylinder

Welded junction between end cap d and cylinder

7

l

c c

t t t t t t t t t t t t tp2 t t t t t t t t c

(b)

FIGURE 11.1 Closed cylinder with internal pressure, external pressure, and axial loads. ( a )Closed cylinder. ( b )Section e-e.

FIGURE 11.2 Closed cylinder with hemispherical ends.

11.1

BASIC RELATIONS

391

We use cylindrical coordinates r, 6, z for radial, circumferential,and axial directions. Let the cylinder be loaded as shown in Figure 1 1.1. For analysis purposes, we remove a thin m u lus of thickness dz from the cylinder (far removed from the end junctions) by passing two planes perpendicular to the z axis, a distance dz apart (Figure 1 1 . 3 ~ )The . cylindrical volume element dr (r d 6 ) dz shown in Figure 11.3b is removed from the annulus. Because of radial symmetry, no shear stresses act on the volume element and normal stresses are functions of r only. The nonzero stress components are principal stresses o,, oee, and 0,.The distributions of these stresses through the wall thickness are determined by the equations of equilibrium, compatibility relations, stress-strain-temperature relations, and material response data.

11.I.I Equation of Equilibrium We neglect body force components. Hence, the equations of equilibrium for cylindrical coordinates (Eqs. 2.50) reduce to the single equation (11.1)

11.I.2 Strain-Displacement Relations and Compatibility Condition The straindisplacement relations for the thick-walled cylinder (Eqs. 2.85) yield the three relations for extensional strains (11.2) where u = u(r, z ) and w = w(r, z ) denote displacement components in the r and z directions, respectively. At sections far removed from the ends, the dependency on z in u and w is considered to be small. Hence, at sections far from the ends, the shear strain components are

(a)

(b)

FIGURE 11.3 Stresses in thick-wall cylinder. (a) Thin annulus of thickness dz. (The zaxis is perpendicular to the plane of the figure.) (b)Cylindrical volume element of thickness dz.

392

CHAPTER 11 THE THICK-WALL CYLINDER

zero because of radial symmetry; furthermore, we assume that E,, is constant. Eliminating the displacement u = u(r) from the first two of Eqs. 1 1.2, we obtain

(11.3) Equation 11.3 is the strain compatibility condition for the thick-wall cylinder.

11.1.3

Stress-Strain-Temperature Relations

The material of the cylinder is taken to be isotropic and linearly elastic. The stress-straintemperature relations are (see Eqs. 3.38)

E,,=

1

1[or,- V ( Oee + oZz)+ a AT

E

(11.4)

where E, v, and a denote the modulus of elasticity, Poisson’s ratio, and the coefficient of linear thermal expansion, respectively. The term AT in Eq. 11.4 represents the change in temperature measured from a uniform reference temperature (constant throughout the cylinder initially); see Boresi and Chong (2000).

11.1.4 Material Response Data For a cylinder made of isotropic linearly elastic material, the material response data are represented by the results of tests required to determine the elastic constants (modulus of elasticity E and Poisson’s ratio V ) and the coefficient of linear thermal expansion a. To determine the maximum elastic loads for the cylinder, the material data must include either the yield stress Y obtained from a tension test or the shear yield stress zY obtained from a torsion test of a hollow thin-wall tube.

11.2 STRESS COMPONENTS AT SECTIONS FAR FROM ENDS FOR A CYLINDER WITH CLOSED ENDS In this section, we obtain expressions for the stress components o,, Oe,, o,,, for a cylinder with closed ends; the cylinder is subjected to internal pressure pl, external pressure p 2 , axial load P, and temperature change AT (Figure 11.1). We may express Eq. 11.3 in terms of or,.,O g e , o,,and their derivatives with respect to r, by substitution of the first two of Eqs. 11.4 into Eq. 11.3. Since E,, = constant, the last of Eqs. 11.4 may be used to express the derivative do,,/dr in terms of the derivatives of err, 0 8 0 , and AT with respect to r. By means of this expression, we may eliminate do,,/dr from Eq. 11.3 to rewrite Eq. 11.3 in terms of or,.,008, and derivatives of err, Oe,, and AT. Since the undifferentiated terms in O , and 0 8 0 occur in the form o,,- bee,Eq. 11.1 may be used to eliminate O , - Gee. Hence, we obtain the differential expression

11.2

STRESS COMPONENTSAT SECTIONS FAR FROM ENDS FOR A CYLINDER WITH CLOSED ENDS

dr

393

(11.5)

1-v

Incorporated in Eq. 11.5 is the equation of equilibrium, Eq. 11.1, the strain compatibility equation, Eq. 11.3, and the stress-strain-temperature relations, Eqs. 11.4. Integration of Eq. 11.5 yields the result fs,,+Ogg+-

aEAT - 2c1 1-v

(11.6)

where 2C1 is a constant of integration (the factor 2 is included for simplicity of form in subsequent expressions). Elimination of the stress component b e e between Eqs. 11.1 and 11.6 yields the following expression for 6,:

-d( r 2 0 ) = --+2Clr a E AT " 1-v dr

(11.7)

Integration of Eq. 11.7 yields the result

or,= -

[

i

2 aE ATr dr + 1 -\$]Cl r (1-v).

+

2

(11.8)

r

where the integration is carried out from the inner radius a of the cylinder (Figure 11.1) to the radius r, and C2 is a second constant of integration. Substitution of Eq. 11.8 into Eq. 11.6 yields the result

(11.9)

By Eqs. 11.8 and 11.9, we obtain

or,+ O g g

a E AT

= 2c1- -

(11.10)

1-v

Equation 11.10 serves as a check on the computations (see Eq. 11.6). The constants of integration C1 and C2 are obtained from the boundary conditions orr= -pl at r = a and or,= -p2 at r = b (Figure 11.1). Substituting these boundary conditions into Eq. 11.8, we find

f

b

-p,b

b -a

1

J

+-1a- E v [ ATrdr ,

c, = - p l a 2

(11.11)

Hence, Eq. 11.10 may be written as

(1 1.12)

394

CHAPTER 11 THE THICK-WALL CYLINDER

To obtain o,,, we integrate each term of the last of Eqs. 1 1.4 over the cross-sectional area of the cylinder. Thus, we have b

I ~ ~ , 2 a r d=r U

1

E

U

2vy

oz,2ardr - E a

Oee+ Orr 2ar

2

dr +

AT 2zr dr

(11.13)

For sections far removed from the end section, E,, is a constant, and the integral of o,, over the cross-sectional area is equal to the applied loads. Hence, because of pressures p 1 and p 2 and axial load P applied to an end plate (Figure 11.4), overall equilibrium in the axial direction requires 2

2

(11.14)

0,,2ardr = P + a ( p l a - p , b )

If there is no axial load P applied to the closed ends, P = 0. Since the temperature change AT does not appear in Eq. 11.14, the effects of temperature are self-equilibrating. With Eqs. 11.12-1 1.14, the expression for E,, at a section far removed from the ends can be written in the form b

‘zz(c1osed end) -

1 - 2 v ( P l a2 -P,b 2 ) + P + z2 j A2 T r d r E(b - a ) a(b - a ) E b - a

(11.15)

Substitution of Eq. 11.15 into the last of Eqs. 11.4, with Eq. 11.12, yields the following expression for o,,for a section far removed from the closed ends of the cylinder: 2

Ozz(c1osed end)

112 . 1

- Pla -P,b - b2 - a 2

b

2 +

P 2

2

--+a E AT

z(b - a )

2a E IATr dr(11.16) 2 2 (1-Wb -a

Open Cylinder

If a cylinder has open ends and there is no axial load applied on its ends, overall equilibrium of an axial portion of the cylinder (Figure 1 1.5) requires that

P2

FIGURE 11.4 Axial equilibrium of closed-end cylinder.

11.3

STRESS COMPONENTS AND RADIAL DISPLACEMENT FOR CONSTANT TEMPERATURE

Y

395

P2

Free end Section at appreciable distance from free end

I

t t t t t t t t P2t t t t t t P FIGURE 11.5

Self-equilibrating axial stress distribution in an open cylinder.

b

( 1 1.17)

~ 2 w o , , d z= 0 U

Then,byEqs. 11.12, 11.13,andll.l7(alsobyEqs. 11.14, 11.15,andll.l7),theexpression for E,, may be written in the form

‘,,(open

end)

-

(b2-a2)E

+ b -2a 1 A 1 r a r

(1 1.18)

and for o,,, we obtain, by Eqs. 11.4, 11.12, and 11.18,

Ozz(open end)

aE -

cv- a

ATr dr - AT

( 1 1.19)

U

We note, by Eq. 11.19, that if the temperature change AT = 0, then o,, = 0. However, E,, # 0 (see Eq. 11.18) when the Poisson ratio v # 0. Note that if p 1 = p 2 = P = 0 (temperature change still occurs), Eqs. 11.15 and 11.16 are identical to Eqs. 11.18 and 11.19, respectively.

11.3 STRESS COMPONENTS AND RADlAL DISPLACEMENT FOR CONSTANT TEMPERATURE

11.3.1 Stress Components In the absence of temperature change, we set AT = 0. Then Eqs. 11.8-1 1.1 1 and 11.16 can be used to obtain the following expressions for the stress components in a closed cylinder (cylinder with end caps): (1 1.20)

396

CHAPTER 11 THE THICK-WALL CYLINDER

2

08,

=

P l a -P,b 2

b -a 2

=

2

b -a

2

a2b2

+

2

2

P l a -P,b 022

2

2

2 (p1-p2)

(1 1.21)

r(b -a) 2 +

2

2

= constant

(1 1.22)

n(b - a )

(11.23) For an open cylinder in the absence of axial force P, o, = 0 by Eq. 11.19 with AT = 0. Since the sum orr+ 000 and stress 0, are constantsthrough the thickness of the wall of the closed cylinder, by Eq. 11.13or 1 1.15, we see that eZzis constant (extension or compression).

1 1.3.2

Radial Displacement for a Closed Cylinder

For no temperature change, AT = 0. Then the radial displacement u for a point in a thickwall closed cylinder (cylinder with end caps) may be obtained by the second of Eqs. 11.2, the second of Eqs. 11.4, and Eqs. 11.20-1 1.22. The resulting expression for u is

(11.24)

+ ( 1 + v 2) a 2 b 2

n

r

1I.3.3 Radial Displacement for an Open Cylinder Of special interest are open cylinders (cylinders without end caps), since an open inner cylinder is often shrunk to fit inside an open outer cylinder to increase the strength of the resulting composite cylinder. For an open cylinder, in the absence of temperature changes (AT = 0), Eq. 11.19 yields o,,= 0. Hence, proceeding as for the closed cylinder, we obtain

'(open end)

-

2

2

( 1 - W P l a -P,b

2

E(b -a )

2

)

(11.25)

+ ( 1 + v)a2b2 ( P l -P 2 ) ] 2 r

Equation 1 1.25 gives the radial displacement of any point at radius r in an open cylinder. For internal pressure only,p2 = 0. Then, by Eq. 1 1.25,the radialcllsplacementat the inner surface r = a is u,

Pi a 2 +vb 2 = a-+ (b2-u2

1

11.3

STRESS COMPONENTSAND RADIAL DISPLACEMENT FOR CONSTANT TEMPERATURE

397

Similarly, for external pressure only, p 1 = 0, and the radial displacement at the outer surface r = b is

EXAMPLE 11.I Stresses in a Hollow Cylinder Solution

A thick-wall cylinder is made of steel (E = 200 GPa and v = 0.29), has an inside diameter of 20 mm, and has an outside diameter of 100 mm. The cylinder is subjected to an internal pressure of 300 MPa. Determine the stress components Or, and 0 0 8 at r = a = 10 mm, r = 25 mm, and r = b = 50 mm. The external pressure p 2 = 0. Equations 11.20 and 11.21 simplify to a2 ( r2 - b 2) err =

PI

O80'

a 2 ( r 2+ b 2 ) p1 2 2 2 r (b -a )

2

2

2

r (b - a )

Substitution of values for r equal to 10 mm, 25 mm, and 50 mm, respectively, into these equations yields the following results: ~

~~~

Stress

r = 10 mrn

r = 25 rnm

r=50mrn

0,

-300.0 MPa 325.0 MPa

-37.5 MPa 62.5 MPa

25.0 MPa

O00

0.0

EXAMPLE 11.2 Stresses and Deformations in a Hollow Cylinder

A thick-wall closed-end cylinder is made of an aluminum alloy (E = 72 GPa and v = 0.33), has an inside diameter of 200 mm, and has an outside diameter of 800 mm. The cylinder is subjected to an internal pressure of 150 MPa. Determine the principal stresses, maximum shear stress at the inner radius (r = a = 100 mm), and the increase in the inside diameter caused by the internal pressure.

Solution

The principal stresses are given by Eqs. 11.2C11.22. For the conditions that p 2 = 0 and r = a, these equations give

or,.=

a'- b'

a Ozz=

= -pl = -150MPa

b -a

b -a

= 10MPa = 150 400' - 10O2

The maximum shear stress, given by Eq. 2.39, is

398

CHAPTER 11 THE THICK-WALL CYLINDER

The increase in the inside diameter caused by the internal pressure is equal to twice the radial displacement given by Eq. 11.24 for the conditionsp 2 = P = 0 and r = a. Thus,

'(r=a)

-

p2l a 2 [ ( 1 - 2 v ) a Z + ( l + v ) b

E(b -a )

[(

150(100) 1 - 0.66) loo2 + (1 + 0.33)400 72,000(4002 - loo2)

= 0.3003 mm

The increase in the inside diameter caused by the internal pressure is 0.6006 mm.

EXAMPLE 11.3 Stresses in a Composite Cylinder

Let the cylinder in Example 1 1.1 be a composite cylinder made by shrinking an outer cylinder onto an inner cylinder. Before assembly, the inner cylinder has inner and outer radii of a = 10 mm and q = 25.072 mm, respectively. Likewise, the outer cylinder has inner and outer radii of c, = 25.000 mm and b = 50 mm, respectively. Determine the stress components Or, and 0 8 8 at r = a = 10 mm, r = 25 mm, and r = b = 50 mm for the composite cylinder. For assembly purposes, the inner cylinder is cooled to a uniform temperature TI and the outer cylinder is heated to a uniform temperature T2 to enable the outer cylinder to slide freely over the inner cylinder. It is assumed that the two cylinders will slide freely if we allow an additional 0.025 mm to the required minimum difference in radii of 0.072 mm. Determine how much the temperature (in degrees Celsius) must be raised in the outer cylinder above the temperature in the inner cylinder to freely assemble the two cylinders. a = O.ooOo117/"C.

Solution

After the composite cylinder has been assembled, the change in stresses caused by the internal pressure p 1 = 300 MPa is the same as for the cylinder in Example 11.1. These stresses are added to the residual stresses in the composite cylinder caused by shrinking the outer cylinder onto the inner cylinder. The initial difference between the outer radius of the inner cylinder and the inner radius of the outer cylinder is 0.072 mm. After the two cylinders have been assembled and allowed to cool to their initial uniform temperature, a shrink pressurep s is developed between the two cylinders. The pressure p s is an external pressure for the inner cylinder and an internal pressure for the outer cylinder. The magnitude of p s is obtained from the fact that the sum of the radial displacement of the inner surface of the outer cylinder and the radial displacement of the outer surface of the inner cylinder must equal 0.072 mm. Hence, by Eq. 11.25,

[(1 - v)psco+ (1 + v)p,b2] E ( b 2 - c:) co

2

i'

[-(1 - v)p,ci - ( 1 + v)p,a

E(Ci - a )

2

I'

= 0.072

Solving for p,, we obtain p , = 189.1 MPa

The pressurep, produces stresses (residual or shrink-fit stresses) in the nonpressurized composite cylinR R der. For the inner and outer cylinders, the residual stresses or,and 080 at the inner and outer radii are given by Eqs. 11.20 and 11.21. For the inner cylinder,p1= 0, p 2 = p,. a = 10 mm, and b = 25 mm. For the outer cylinder, p1= p,, p 2 = 0,a = 25 mm, and b = 50 mm. The residual stresses are found to be

11.4

Inner cylinder Residualstress

R

r=10mm 0

Orr

R Oao

-450.2 MPa

CRITERIA OF FAILURE

399

Outer cylinder

r=25mm

r = 25 mm

-189.1 MPa

-189.1 MPa

-261.1 MPa

315.1 MPa

r = 50 mm 0

126.0 MPa

The stresses in the composite cylinder after an internal pressure of 300 MPa has been applied are obtained by adding these residual stresses to the stresses calculated in Example 11.1. Thus, we find

Inner cylinder

Outer cylinder

Residual stress

r = 10 mm

r=25mm

r = 25 mm

Orr

-300.0 MPa

-226.6 MPa

-226.6 MPa

Oee

-125.2 MPa

-198.6 MPa

377.7 MPa

r=50mm 0 151.0 MPa

A comparison of the stresses for the composite cylinder with those for the solid cylinder in Example 11.1 indicates that the stresses have been changed greatly. The determination of possible improvements in the design of the open-end cylinder necessitates considerationof particular criteria of failure (see Section 11.4). To have the inner cylinder slide easily into the outer cylinder during assembly, the difference in temperature between the two cylinders is given by the relation AT = T , - T , =

2

=

0.072 + 0.025 0'097 = 331.6"C ra: 25(0.0000117)

= 0 in each cylinder, and since then Eqs. since for uniform temperatures T , , T2,we have or,= bee= oZz 11.2 and 11.4 yield e8e = u / r = a A T , where r = c o =%.

11.4 CRITERIA OF FAILURE The criterion of failure used in the design of a thick-wall cylinder depends on the type of material in the cylinder. As discussed in Section 4.3, the maximum principal stress criterion should be used in the design of members made of brittle isotropic materials if the principal stress of largest magnitude is a tensile stress. Either the maximum shear-stress or the octahedral shear-stress criterion of failure should be used in the design of members made of ductile isotropic materials (see Section 4.4).

11.4.1 Failure of Brittle Materials If a thick-wall cylinder is made of a brittle material, the material property associated with fracture is the ultimate tensile strength ou. At the failure loads, the maximum principal stress in the cylinder is equal to ou.If the maximum principal stress occurs at the constrained ends of the cylinder, it cannot be computed using the relations derived in Sections 11.2 and 11.3. At sections far removed from the ends, the maximum principal stress is

400

CHAPTER 11 THE THICK-WALL CYLINDER

either the circumferential stress bee(,.= or the axial stress ozz. If the cylinder is loaded so that the magnitude of the maximum compressive principal stress is appreciably larger than the magnitude of the maximum tensile principal stress, the appropriate criterion of failure to be used in design is uncertain. Such conditions are not considered in this book.

11.4.2

Failure of Ductile Materials

If excessive elastic deformation is not a design factor, failure of members made of ductile materials may be initiated as the result of general yielding or fatigue. Failure of these members is predicted by either the maximum shear-stress criterion of failure or the octahedral shear-stress criterion of failure.

General Yielding Failure Thick-wall cylinders that are subjected to static loads or peak loads only a few times during the life of the cylinder are usually designed for the general yielding limit state. General yielding may be defined to occur when yielding is initiated in the member at some point other than at a stress concentration. This definition is used in examples at the end of this section (see also Section 4.6). However, yielding may be initiated in the region of stress concentrations at the ends of the cylinder or at an opening for pipe connections. Yielding in such regions in usually highly localized and subsequent general yielding is unlikely. However, the possibility of failure by fatigue still may exist (see Chapter 16). General yielding sometimes is considered to occur only after the member has yielded over an extensive region, such as occurs with fully plastic loads. Fully plastic loads for thick-wall cylinders are discussed in Section 1 1.5. Fatigue Failure In practice, a thick-wall cylinder may be subjected to repeated pressurizations (loading and unloading) that may lead to fatigue failure. Since fatigue cracks often occur in the neighborhood of stress concentrations, every region of stress concentration must be considered in the design. In particular, the maximum shear stress must be determined in the region of stress concentrations, since fatigue cracking usually originates at a point where either the maximum shear stress or maximum octahedral shear stress occurs. The equations derived in Sections l l .2 and l l .3 cannot be used to compute the design stresses, unless the maximum stresses occur at sections of the cylinder far removed from end constraints or other stress concentration regions.

11.4.3

Material Response Data for Design

If a member fails by general yielding, the material property associated with failure is the yield stress. This places a limit either on the value of the maximum shear stress, if the maximum shear-stress criterion of failure is used, or on the value of the octahedral shear stress, if the octahedral shear-stress criterion of failure is used. If the member fails by fatigue, the material property associated with the failure is the fatigue strength. For high cycle fatigue, both the maximum shear-stress criterion of failure and octahedral shearstress criterion of failure are used widely in conjunction with the fatigue strength (see Chapter 16, Example 16.1). The yield stress and fatigue strength may be obtained by tests of either a tension specimen or hollow thin-wall tube. The values of these properties, as determined from tests of a hollow thin-wall tube in torsion, are found to lead to a more accurate prediction of the material response for thick-wall cylinders than the values obtained from a tension specimen. This

11.4

CRITERIA OF FAILURE

401

is because the critical state of stress in the cylinder is usually at the inner wall of the cylinder, and for the usual pressure loading it is essentially one of pure shear (as occurs in the torsion test) plus a hydrostatic state of stress. Since in many materials a hydrostatic stress does not affect the yielding, the material responds (yields) as if it were subjected to a state of pure shear. Consequently, if the material properties are determined by means of a torsion test of a hollow thin-wall tube, the maximum shear-stress criterion and octahedral shear-stress criterion predict failure loads that differ by less than 1% for either closed or open cylinders. The difference in these predictions may be as much as 15.5% if the material properties are obtained from tension specimen tests (Section 4.4). These conclusions pertain in general to most metals. However, the yield of most plastics is influenced by the hydrostatic state of stress. Hence, for most plastics, these conclusions may not generally hold. The deviatoric state of stress (see Section 2.4) in a closed cylinder is identical to that for pure shear. Hence, the maximum shear-stress and the octahedral shear-stress criteria of failure predict nearly identical factors of safety for the design of a closed cylinder if the yield stress for the material is obtained from torsion tests of hollow thin-wall tubes. Let the shear yield stress obtained from a torsion test of a thin-wall hollow tube specimen be designated as zy. If the maximum shear stress for the inner radius of a closed cylinder is set equal to zy, the pressure p y required to initiate yielding is obtained. (The reader is asked to derive the formula for pr in Problem 1 1.17.) For the special case of a closed cylinder with internal pressure only and with dimensions b = 2a, the yield pressure is found to be p y = 0.75 zy; the corresponding dimensionless stress distribution is shown in Figure 1 1.6.

11.4.4 Ideal Residual Stress Distributions for Composite Open Cylinders It is possible to increase the strength of a thick-wall cylinder by introducing beneficial residual stress distributions. The introduction of beneficial residual stresses can be accomplished in several ways. One method consists of forming a composite cylinder from two or more open cylinders. For example, in the case of two cylinders, the inner cylinder has an outer radius that is slightly larger than the inner radius of the outer cylinder. The inner cylinder is slipped inside the outer cylinder after first heating the outer cylinder and/or

FIGURE 11.6 Stress distributions in a closed cylinder at initiation of yielding ( b = 2a).

402

CHAPTER I 1 THE THICK-WALL CYLINDER

cooling the inner cylinder. When the cylinders are allowed to return to their initially equal uniform temperatures (say, room temperature), a pressure (the so-called shrink pressure) is created between the cylinder surfaces in contact. This pressure introduces residual stresses in the cylinders. As a result, the strength of the composite cylinder under additional internal and external pressure loading is increased (Example 11S). For more than two cylinders this process is repeated for each cylinder that is added to form the composite cylinder. A second method for introducing residual stresses consists of pressurizing a single cylinder until it deforms inelastically to some distance into the wall from the inner surface (a process called autofrettage). When the pressure is removed, a beneficial residual stress distribution remains in the cylinder (see Section 11S). For a composite cylinder formed by two cylinders under a shrink fit and subject to internal pressurepl, the most beneficial residual stress distribution is that which results in the composite cylinder failing (yielding or fracturing) simultaneously at the inner radii of the inner and outer cylinders. Consider, for example, a composite cylinder formed by inner and outer cylinders made of a brittle material whose stress-strain diagram remains linear up to its ultimate strength a,. The inner cylinder has inner radius rl and outer radius 1.5-1 + (i.e., the outer radius is slightly larger than 1.5rl).The outer cylinder has an inner radius of 1.51-1 and outer radius of 3rl. See Figure 11.7. Fracture of the brittle material occurs when the maximum principal stress reaches the ultimate strength a,. Since the maximum principal stress in the composite cylinder is the circumferential stress component for the most beneficial residual (dimensionless) stress distribution (Figure 11.7a), failure of the composite cylinder occurs when oee=a,, simultaneously at the inner radii of the inner and outer cylinders (Figure 11.7b). The ideal residual stress distribution requires a specific difference between the inner radius of the outer cylinder and the outer radius of the inner cylinder, which produces a shrink pressure p s (see Problem 11.24). This shrink pressure produces a residual stress distribution (Figure 11.7~)such that the application of an internal pressure p1 produces the (dimensionless) stress distribution of Figure 11.7b at failure.

FIGURE 11.7 Stress distributions in composite cylinder made of brittle material that fails at inner radius of both cylinders simultaneously. (a) Residual stress distributions. ( b )Total stress distributions.

11.4

CRITERIA OF FAILURE

403

1

-1.0

FIGURE 11.8 Stress distributions in composite cylinder made of ductile material that fails at inner radius of both cylinders simultaneously. (a) Residual stress distributions. (b)Total stress distributions.

If the composite cylinder is made of a ductile metal, either the maximum shearstress criterion of failure or the octahedral shear-stress criterion of failure can be used. For example, let the composite cylinder of Figure 11.8 be made of a ductile metal. Based on the maximum shear-stress criterion of failure, the ideal residual stress distribution resulting from the shrink pressure p s is shown in Figure 11.8~1.(In this case, the interference fit is different from the cylinder of Figure 11.7; see Problem 11.23.) For an internal pressure p1 at failure of the cylinder, yield occurs simultaneously at the inner radii of the inner and outer cylinders, and the associated dimensionless stress distribution is shown in Figure 11.8b.

EXAMPLE 11.4 Yield Failure of Thick-Wall Cylinder

The thick-wall cylinder in Example 11.1 is made of a ductile steel whose general yielding failure is accurately predicted by the octahedral shear-stress yield criterion. Determine the minimum yield stress for the steel for a factor of safety of SF = 1.75.

Solution

The stress components calculated in Example 11.1 are for a cylinder that has been designed with a factor of safety of SF = 1.75. Yielding impends in the cylinder when the internal pressure is increased to (SF)p, = 525 MPa. The yield stress Y for the steel is obtained by setting the Octahedral shear stress in the cylinder [when the pressure in the cylinder is (SF)p,] equal to the octahedral shear stress that occurs in a tension specimen made of the steel when the tension specimen axial stress is Y. The octahedral shear stress in the tension specimen is given by the relation (see Eq. 2.22)

1 2 +(O-0) zoct= -Yl(Y-O) 3

2

+(O-Y)

2

=

J5Y 3

404

CHAPTER 11 THE THICK-WALL CYLINDER

~

The octahedral shear stress at any point in the thick-wall cylinder is given by the relation (see Eq. 2.22)

For the open cylinder, the axial stress o,,is zero and the radial and circumferential stresses are

orr= -1.75(300)

= -525 MPa

Oee = 1.75(325) = 568.8 MPa

Substituting these stress components into Eq. (b) and setting Eq. (a) equal to Eq. (b), we obtain

+ 525)2 + (525)2 + (568.8)2

Y = -t/(568.8 1

.h

= 947.5 MPa

EXAMPLE 11.5 Yield of a Composite ThickWall Cylinder

The inner and outer cylinders of the composite thick-wall cylinder in Example 11.3 are made of the same ductile steel as the cylinder in Example 11.4. Determine the minimum yield stress for the steel in the composite cylinder for a factor of safety of SF = 1.75.

Solution

For the composite open cylinder, it is necessary to consider initiation of yielding for the inside of the inner cylinder, as well as for the inside of the outer cylinder. The axial stress o,,is zero for both cylinders. At the inside of the inner cylinder, the radial and circumferential stresses for a pressure (SF)p, are

Note: Equations (a) and (b) in Example 11.4 are valid for this problem also.

or, = (1.75)( 300)

= -525 MPa

Gee = (1.75)(325)-450.2

= 118.6 MPa

Substituting these stress components into Eq. (b) and setting Eq. (a) equal to Eq. (b), we obtain

Y =

1 -J(

h

118.6 + 525)2 + (525)2 + (118.6)2 = 593.3 MPa

At the inside of the outer cylinder, the radial and circumferential stresses for a pressure (SF)pl are

or, = -( 1.75)(37.5) - 189.1 = -254.7 MPa bee=

(1.75)(62.5)

+ 315.1

= 424.5 MPa

Substituting these stress components into Eq. (b) and setting Eq. (a) equal to Eq. (b), we find

Y = -J(424.5 1

.h

+ 254.7)2 + (254.7)2 + (424.5)2

= 594.3 MPa > 593.3 MPa

For the composite cylinder, the yield stress should be at least Y = 594.3 MPa. An ideal design for a composite cylinder should cause the required yield stress to be the same for the inner and outer cylinders. (Note that the above design is nearly ideal.) A comparison of the required yield stress for the single cylinder in Example 11.4 and the required yield stress for the composite cylinders indicates the advantage of the composite cylinder. The yield stress of the single cylinder material must be 59.4% greater than that of the composite cylinder, if both cylinders are subjected to the same initial pressure and are designed for the same factor of safety against initiation of yielding.

11.5

FULLY PLASTIC PRESSUREAND AUTOFRETTAGE

405

11.5 FULLY PLASTIC PRESSURE AND AUTOFRElTAGE Thick-wall cylinders made of ductile material can be strengthened by introducing beneficial residual stress distributions. In Sections 11.3 and 11.4, it was found that beneficial residual stress distributions may be produced in a composite cylinder formed by shrinking one cylinder onto another. Beneficial residual stress distributions may also be introduced into a single cylinder by initially subjecting the cylinder to high internal pressure so that inelastic deformations occur in the cylinder. As a result, an increase in the load-carrying capacity of the cylinder occurs because of the beneficial residual stress distributions that remain in the cylinder after the high pressure is removed. The residual stress distribution in the unloaded cylinder depends on the depth of yielding produced by the high pressure, the shape of the inelastic portion of the stress-strain diagram for loading of a tensile specimen of the material, and the shape of the stress-strain diagram for unloading of the tensile specimen followed by compression loading of the specimen. If the material in the cylinder is a strain-hardening material, a part (usually, a small part) of the increase in load-carrying capacity is due to the strengthening of the material, resulting from strain hardening of the material. If the material exhibits a flat-top stress-strain diagram at the yield point (i.e., elastic-perfectly plastic), all the increase in load-carrying capacity is due to the beneficial residual stress distribution. The process of increasing the strength of open and closed cylinders by increasing the internal pressure until the cylinder is deformed inelastically is called uutofrettuge. The beneficial effect of the autofrettage process increases rapidly with the spread of inelastic deformation through the wall thickness of the cylinder. Once yielding has spread through the entire wall thickness, any further improvement in load-carrying capacity resulting from additional inelastic deformation is due to strain hardening of the material. The minimum internal pressure p1 required to produce yielding through the wall of the cylinder is an important pressure to be determined, since most of the increase in load-carrying capacity is produced below this pressure, and the deformation of the cylinder remains small up to this pressure. For the special case where the stress-strain diagram of the material is flat-topped at the yield point the internal pressure p 1 is called the fully plastic pressure p p We derive the fully plastic pressure by assuming that the maximum shear-stress criterion of failure is valid. If we assume that o,,is the intermediate principal stress (orr< o,,< D e e ) for the cylinder, (Tee - or,= 22,, where zyis the shear yield stress. This result may be substituted into the equation of equilibrium, Eq. 11.1, to obtain do,, = 5 d r r

(11.26)

or, = 2 ~ ~ l+nCr

(11.27)

Integration yields

The constant of integration C is obtained from the boundary condition that or,= -p2 when r = b. Thus, we obtain b

or, = -2zY In-r - p 2

(11.28)

406

CHAPTER 11 THE THICK-WALL CYLINDER

which describes the radial stress distribution at the fully plastic pressure pp. The magnitude of pp is given by Eq. 1 1.28 since the internal pressure is then p1 = pp = -err at r = a. Thus, we obtain b +p2 p p = 2ZYIna

(11.29)

In practice, p2 is ordinarily taken equal to zero, since for p2 = 0 the required internal pressure p1 is smaller than for nonzero p2. The circumferential stress distribution for the cylinder at the fully plastic pressure is obtained by substituting Eq. 1 1.28 into the relation Oge a,, = 22, to obtain (1 1.30) If the material in the cylinder is a Tresca material, that is, a material satisfying the maximum shear-stress criterion of failure, zY = Y/2, and the fully plastic pressure given by Eq. 1 1.29 is valid for cylinders subjected to axial loads in addition to internal and external pressures as long as o,,is the intermediate principal stress, that is, (T, < T(, < Dee. If the material in the cylinder is a von Mises material, that is, a material satisfying the octahedral shear-stress criterion of failure, 2, = Y / & (see column 4 of Table 4.2), the fully plastic pressure given by Eq. 1 1.29 is valid for closed cylinders subjected to internal and external pressures only. For this loading, the octahedral shear-stress criterion of failure requires that the axial stress be given by the relation (11.31)

The proof of Eq. 1 1.3 1 is left to the reader. In many applications, the external pressure p2 is zero. In this case, the ratio of the fully plastic pressure pp (Eq. 1 1.29) to the pressure py that initiates yielding in the cylinder at the inner wall (see Problem 11.17) is given by the relation n

(11.32)

In particular, this ratio becomes large as the ratio b/a becomes large. For b = 2a, Eq. 1 1.32 gives pp = 1.85py;dimensionless radial, circumferential, and axial stress distributions for this cylinder are shown in Figure 11.9. A comparison of these stress distributions with those at initiation of yielding (see Figure 11.6) indicates that yielding throughout the wall thickness of the cylinder greatly alters the stress distributions. If the cylinder in Figure 1 1.9 unloads elastically, the residual stress distributions can be obtained by multiplying the stresses in Figure 1 1.6 by the factor 1.85 and subtracting them from the stresses in FigR at the inner radius is calcuure 11.9. For instance, the residual circumferential stress Oee lated to be OF0 = - 1 . 7 2 ~This ~ maximum circumferential residual stress can be expressed in terms of the tensile yield stress Y as follows: for a Tresca material Ote = -0.86Y and for a von Mises material = -0.99Y. However, one cannot always rely on the presence of this large compressive residual stress in the unloaded cylinder. In particular, all metals behave inelastically (because of the Bauschinger effect) when the cylinder is unloaded, resulting in a decrease in the beneficial effects of the residual stresses. For

bte.

11.5

FULLY PLASTIC PRESSURE AND AUTOFRETTAGE

407

-1.5k

FIGURE 11.9 Stress distributions in a closed cylinder made of a von Mises material at fully plastic pressure ( b = 2a).

example, one investigation (Sidebottom et al., 1976) indicated that the beneficial effect of the residual stresses at the inside of the cylinder (when b = 2a) is decreased to about 50% of that calculated based on the assumption that the cylinder unloads elastically. Consequently, the cylinder will respond inelastically rather than elastically the next time it is loaded to the fully plastic pressure.

EXAMPLE 11.6 I A closed cylinder has an inner radius of 20 mm and an outer radius of 40 mm. It is made of steel that Fully Plastic 1 has a yield stress of Y = 450 MPa and obeys the von Mises yield criterion. Pressure for a (a) Determine the fully plastic internal pressurepp for the cylinder. Cylinder (b) Determine the maximum circumferential and axial residual stresses when the cylinder is unloaded from pp,assuming that the values based on linear elastic unloading are decreased by 50% because of inelastic deformation during unloading. (c) Assuming that the elastic range of the octahedral shear stress has not been altered by the inelastic deformation, determine the intemal pressure p , that can be applied to the cylinder based on a factor of safety SF = 1.80. For SF = 1.80, compare this result with the pressurep, for a cylinder without residual stresses.

Solution

(a)The shear yield stress zy for the von Mises steel is obtained using the octahedral shear-stress yield criterion

The magnitude of ppis given by Eq. 11.29. Thus, we find

b 40 pp = 2zy In- = 2(259.8) In- = 360.21 MPa a 20

408

CHAPTER 11 THE THICK-WALL CYLINDER

The circumferentialand axial stresses at the inner radius for fully plastic conditions are given by Eqs. 11.30and 11.31.Theyare Uee = 22,

o,, =

(1-In-3 = 2(259.8)(1-In-3 = 159.4 MPa 159.4 - 360.2 = 2

Gee+ o r r 2

MPa

(b) Assuming linearly elastic unloading, we compute the circumferential and axial residual stresses at r=aas R

= 159.4-

Pp(b2 + a 2 ) 2

b -a

2

= 159.4-

360.2(402+ 202) 402 - 202

= 440.9 MPa 2

~

u,, R = -100.4 - PPa = -100.4 - 360.2(2o2) = 220.5 2 2 b -a 402 - 202

ma

~

~

The actual residual stresses may be as much as 50% less than these computed values. Thus,

I I

I

uee R = OSO(40.9) = -220.4 MPa

I

I

(a)

R

I

ozz= 0.50(-220.5) = -110.2 MPa

I I I I

I ~

(e) Yielding is initiated in the cylinder at a pressure (SF)pl = 1 . 8 0 ~ If ~ .the residual stresses are neglected, the stresses at the inner radius caused by pressure (SF)pl are

I I

I I I

orr= - ( S F ) ( p I ) = -1.80~1 = ( S F ) b (2 + P 2~= ) ( ~1 . 8 0402 ) (+ 202 ~ , ) ~

b -a

40 -20

= 3.000p1 2

202 o,, = ( S F ) ( P , ) L = (1.80)(P,)2 2 402 - 202 b -U = 0.6000p1 The actual stresses at the inner radius are obtained by adding the residual stresses given by Eq. (a) to those given by Eqs. (b). Thus,

or, = -1.80~1 ~ e =e 3.oooOp1- 220.4 u,, = 0.6000~1-110.2

(c)

The octahedral shear-stressyield condition requires that

J:'

2 2 - - -- :,/(oee-crr)2 +(orr-oz,) +(oZZ-oee)

I

Substitutingthe values for the stress components given by Eqs. (c) into Eq. (d), we find that

(4

11.6

CYLINDER SOLUTION FOR TEMPERATURE CHANGE ONLY

409

p1 = 154.2MPa

is the working internal pressure for the cylinder that was preloaded to the fully plastic pressure. Substituting the values for the stress components given by Eqs. (b) into Eq. (d), we obtain the working internal pressure for the cylinder without residual stresses: p1 = 108.3 MPa

Hence, the working pressure for the cylinder that is preloaded to the fully plastic pressure is 42.4% greater than the working pressure for the elastic cylinder without residual stresses.

11.6 CYLINDER SOLUTION FOR TEMPERATURE CHANGE ONLY Consider the stress distribution in a thick-wall cylinder subjected to uniform internal and external pressures p1 and p 2 , axial load P, and temperature change AT that depends on the radial coordinate r only. The stress distribution may be obtained from Eqs. 1 1.8-1 1.11 and 11.16. The special case of constant uniform temperature was considered in Section 11.3. In this section, the case of a cylinder subjected to a temperature change AT = T(r),in the absence of pressures and axial load, is treated. If internal and external pressures and temperature changes occur simultaneously,the resulting stresses may be obtained by superposition of the results of this section with those of Section 11.3. As in Section 11.3, the results here are restricted to the static, steady-state problem. Accordingly, the steady-state temperature change AT = T(r)is required input to the problem.

11.6.1 Steady-State Temperature Change (Distribution) The temperature distribution in a homogeneous body in the absence of heat sources is given by Fourier’s heat equation

pV2T =

(11.33) at

in which p is the thermal diffusivity for the material in the body, where we consider T = AT to be the temperature change measured from the uniform reference temperature of the unstressed state, and t is the time. For steady-state conditions, dT/dt = 0, and Eq. 11.33 reduces to

VLT = 0

(11.34)

In cylindrical coordinates (r, 6 , z ) , Eq. 11.34 takes the form

(11.35) Since T is assumed to be a function of r only, Eq. 1 1.35 simplifies to d2T - + - - 1 dT = 0 dr2 r d r

(11.36)

410

CHAPTER 11 THE THICK-WALL CYLINDER

The solution of Eq. 11.36 is

T = C , Inr + C ,

(11.37)

where C1 and C , are constants of integration. With Eq. 11.37, the boundary conditions T = Tb for r = b and T = T, for r = a are used to determine C1 and C2.The solution of Eq. 11.37 then takes the form (11.38) where

11.6.2

Stress Components

I f p l = p 2 = P = 0, Eq. 11.38 can be used with Eqs. 11.8-11.11 and 11.16 to obtain stress components for steady-state temperature distributions in a thick-wall cylinder. The results are

066 =

(11.40)

Thus, the stress distributions for linearly elastic behavior of a thick-wall cylinder subjected to a steady-state temperature distribution are given by Eqs. 11.39-1 1.41. When To = T, - Tb is positive, the temperature T, at the inner radius is greater than the temperature Tb at the outer radius. For the case of positive To, dimensionless stress distributions for a cylinder with b = 2a are shown in Figure 11.10. For this case, the stress components Dee and o,,are compressive, so a positive temperature difference To is beneficial for a cylinder that is subjected to a combination of internal pressure p1 and temperature since the compressive stresses resulting from To counteract tensile stresses resulting from p l . The stresses in cylinders subjected to internal pressure p l , external pressure p 2 , axial load P, and steady-state temperature may be obtained as follows: The radial stress is given by adding Eq. 11.20 to Eq. 11.39, the circumferential stress is given by adding Eq. 11.21 to Eq. 11.40, and the axial stress is given by adding Eq. 11.22 to Eq. 11.41.

1I.7

ROTATING DISKS OF CONSTANT THICKNESS

411

-1

d l - v) 1 .o

FIGURE 11.10 Stress distributions in a cylinder subjected to a temperature gradient ( b = 2a).

11.7 ROTATING DISKS OF CONSTANT THICKNESS Consider a circular disk of inner radius a, outer radius b, and constant thickness t or,for all values of a and b (see Eqs. 11.49 and 11.50), then the maximum shear-stress criterion is given by

or

(oee),, = Y = 620 MPa

(b)

Since the disk is traction free at r = a and r = b, the maximum value of (Tee is given by Eq. 11.54 as

416

CHAPTER 11 THE THICK-WALL CYLINDER

With the given data, Eqs. (b) and (c) yield

or

w y = 1021 rad/s (b) When the angular speed increases beyond my, a plastic zone develops at r = a (Figure El 1.8). In other words, the region a < r < r, will be plastic and the region rp < r < b will be elastic, where r = r, is the interface between the plastic and elastic regions. In the plastic region b g e = Y, but orris not known. However, we may obtain orrfrom the equilibrium condition (Eq. 11.45).Thus, with 0 0 8 = Y, we have in the plastic region

1 -+;or,

'or,

dr

Y r

= --pro

2

or, rewriting the left side, we have

Id Y -r-dr ( r o r r ) = -r- p r w

2

Integration yields

orr= Y - - 1p r 2 w2 + c -r 3 For r = a, orr= 0; so by Eq. (f), 1 3 2 C = -pa w -aY 3

(g)

Equations (f) and (g) yield

(

3;

orr= Y 1 - -

--pw

2(

f)

r --

When the disk is fully plastic, r = rp= b. Then, since 6, = 0 at r = b, Eq. (h) yields with the given data

/T

a=(-+=

p(b + a b + a )

Comparing w pto my, we have by Eqs. (e) and (i)

In this case the speed at the fully plastic condition is 32% larger than that at yield.

6)

11.7

ROTATING DISKS OF CONSTANT THICKNESS

417

EXAMPLE 11. Residual Stresst in a Dis

For the disk of Example 11.8, after the fully plastic state is reached, the angular velocity is reduced to zero. Determine the residual stresses and (Oee)R in the disk.

Solutio

As noted in Section 6.10, the residual stresses may be obtained by subtracting the elastic stresses using w = wpfrom the fully plastic stresses. By Eqs. 11.52 with 0 = wp, the elastic stresses are

By Example 11.8, the plastic stresses are

= y

7 )( 1-+ 3 v ) r 2 ]

pw2 1 3 + v)(u2+ b 2 + a2b2

-

8 2

Since wp = 3Y/[p(b2+ ab + a2)],we see by the first of Eqs. (c) that ( o r r ) R = 0 for r = a and r = b. Also, by eliminating wp from Eqs. (c), we may express the residual stresses in terms of Y as follows:

3

I

(Gee)R = Y 1 -

3 [ ( 3 + v)(a2 + b2 + 8(b2+ ab + a 2 )

?)-

(1 +3v)r2]}

sence, with a = 100 mm, b = 300 mm, and v = 0.29, Eqs. (d) yield --

Y

-(Oee)R -

Y

2

- 0.05096154 + 1.7980769r -

0.09230769 0.00854135 2 r +

0.05096154 + 5.39423077r2 - 0.00854135 r

418

CHAPTER 11 THE THICK-WALL CYLINDER

I

As a check, the first of Eqs. (e) yields

for r = 100mm,

=

R=

Y

o

for r = 300 mm, Values of the residual stresses are given in Table E l 1.9 and a plot is shown in Figure El 1.9. Since

o,,= 0, the maximum value of shear stress (see Eqs. 4.14 and 4.15) does not cause yielding upon unloading; that is, I (or,.)R - o,,I < Y, I( o B B ) R - o,,I < K and I ( o e e ) R - ( ~ J RI 1

A slender pinned-end elastic column (one with a large slenderness ratio L / r ) has more than one buckling or critical load, Eq. 12.14.If the column is restrained from buckling into a single lobe by a lateral stop, it may buckle at a load higher than Pcr.For example, a column with pinned ends can buckle in the form of a single sine lobe at the critical load P,, (Figure 12.7~).If, however, it is prevented from bending in the form of one lobe by restraints at its midpoint, the load can increase until it buckles into two lobes (n = 2; Figure 12.7b).By Eq. 12.14,for n = 2, the critical load and critical stress are

p = 4 -7C2Er - 4Pcr, L2

(a1

FIGURE 12.7

Buckling modes: n = 1,2,3.

Ocr(2) =

(b)

(12.17)

432

CHAPTER 12 ELASTIC AND INELASTIC STABILITY OF COLUMNS

where L l r is the slenderness ratio for the column. Similarly, for n = 3,

p = 9 l- -t

2 ~ ~

L2

- 9Pcr,

Ocr(3) =

P

n2E

= 9-

(12.18)

or for any number of lobes n, (12.19)

The buckling modes for n = 1 , 2 , and 3 are shown in Figure 12.7. In summary, the equilibrium method is characterized by the question: What are the values of the load for which the perfect system admits nontrivial, neutral equilibrium configurations?As demonstrated above for the pin-ended column, an infinite number of such values (eigenvalues), n = 1 , 2, 3, ..., 00, exist. However, practically speaking, usually only the smallest value Pc, is significant.

12.3.3 The Imperfection Method In the imperfection method, we acknowledge that a real column usually is loaded eccentrically (the line of action of the compressive force does not lie exactly along the centroidal axis of the column or the column is not exactly straight). Hence, the imperfection method is a generalization of the equilibrium method. A common eccentricity occurs when the line of action of the load is displaced a distance e from the centerline of the column (Figures 12.8a, 12.8c, and 12.84. As an example, consider the column shown in Figure 1 2 . 8 ~ . A free-body diagram of a segment of the column in the displaced position is shown in Figure 12.8b. By the equilibrium of moments about point A , we have x M A = M(x) + Pex/L + Py = 0. Hence,

(0)

(b)

FIGURE 12.8 Eccentrically loaded pinned-end columns.

12.3

THE EULER FORMULA FOR COLUMNS WITH PINNED ENDS

M(x) = -Py-Pe-

X

L

433

(12.20)

Thus, by Eqs. 12.6 and 12.20, we obtain M(x) = + EId2y/dx2= -Py - Pex/L, or dividing by EI, we obtain 2

b + k y2= - - , k e x dx2 L

k 2 = -P EI

(12.21)

The boundary conditions associated with Eq. 12.21 are y = 0 forx = 0 , L

(12.22)

The general solution of Eq. 12.21 is y = A s i n k x + B c o s k x - - ex L

(12.23)

where A and B are constants determined by the boundary conditions. Hence, Eqs. 12.22 and 12.23 yield the solution (12.24)

As the load P increases (Figure 12.8a), the deflection of the column increases. When P reaches the value for which kL = nn, n = 1, 2, 3, ..., the deflection given by Eq. 12.24 becomes infinitely large, since sin kL goes to zero as kL goes to nn. The term sin kL becomes zero for the first time when n = 1. Then, P = P,, = n2EI/L2,the Euler load (Eq. 12.2). Thus, we see that the imperfection method yields the Euler buckling load for the pin-ended column. Other types of eccentricities, such as those shown in Figures 1 2 . 8 ~ and 12.8d, may also be analyzed by the method of imperfections (see Problems 12.12 and 12.13). In summary, the imperfection method is characterized by the question: What is the load for which the deflection of an imperfect system increases without limit?

12.3.4 The Energy Method The energy method is based on the first law of thermodynamics; namely, as a system is moved from one configuration to a second configuration, the work that external forces perform on a system plus the heat energy thatjows into the system equals the increase in internal energy of the system plus the increase in the kinetic energy of the system, For a conservative (elastic) system, the increase in internal energy is equal to the change in strain energy (see Section 5.1). Thus, for a conservative system, the first law of thermodynamics is, in equation form,

W + 6 H = 6U+6K

(12.25)

where 6 W is the work of the external forces as the system is moved from one configuration to a second configuration, 6 H is the corresponding heat energy added to the system, 6U is the corresponding change in the strain energy, and 6K is the corresponding change in kinetic energy. See also Section 3.1.

434

CHAPTER 12 ELASTIC AND INELASTIC STABILITY OF COLUMNS

Application to Column Buckling Consider an elastic colurnn that is subjected to its critical axial load. A slight disturbance will cause the column to “kick out” or buckle into a new equilibrium position. Dynamically, the elastic column will vibrate about the buckled position indefinitely. This vibration represents an increase in kinetic energy. However, for an infinitesimal buckling displacement, the kinetic energy 6K is of a higher order than the energies 6W and D, that is, 6K a, we obtain by transforming the stress components relative to the (a, p) axes (Figure 14.6) into stress components relative to the (x,y) axes (Inglis, 1913)

(15.4) where s is a distance parameter (15.5)

and 2(1 + m ) s -m

+[ (+](??)]

F2(s)= 1 ( 1 + s - m 1 + S - m

(15.6)

s -m

with 1 a-b B = -(a+b), m = 2 a+b

(15.7)

By means of Eqs. 15.4, the stresses along the major axes in the neighborhood of the end of the major axes of an elliptical hole may be examined. By assuming that the radius of curvature p of a crack may be approximated by the radius of curvature of an equivalent elliptical hole (Eq. 14.12), approximations of the stress in the neighborhood of the crack may be obtained, provided p # 0, that is, for a blunt crack.

FIGURE 18.4 Elliptical hole in an infinite plate.

15.2

15.2.1

THE STATIONARY CRACK

553

Blunt Crack

For the elliptical hole, let the radius of curvature be p p. U

U

FIGURE 15.5

Through-thickness crack in an infinite plate.

554

CHAPTER 15 FRACTURE MECHANICS

15.2.2

Sharp Crack

For the sharp crack, we may estimate the stress distribution from that of the elliptical hole by letting b + 0. Then, we have z+J(a)z-l 2B = a , m = 1, s = a x = r+a,

(15.11)

r < < a, b = 0

and by Eqs. 15.6

(15.12)

Hence, 7

(15.13) Clearly, at the crack tip (r = O), the stress is singular (dry+ 00 as r + 0). Alternatively, in terms of x , it may be shown that

(15.14)

/

Again, at the crack tip ( x = a), dryand ox, become infinite. For large values of x , oyy+ Q and ox,+ 0 as expected (Figure 15.5). As we shall see in Section 15.3 in describing crack propagation, it is conventional to introduce the combination oYy f i since this factor remains finite as r + 0. In addition, a factor K is introduced so that

K, = o y y Z r = o K a

(15.15)

The factor KIis called the stress intensityfactor. In certain fracture theories, it is assumed that the material fractures(the crack propagates) if KIexceeds the notch toughness KIc; that is, fracture occurs when

K, =

0,&2

K,,

(15.16)

where 0,is the corresponding critical tensile stress. The term stress intensity factor should not be confused with the term stress concentration factor (Eq.14.1), which represents the ratio between the maximum stress in a region of stress concentration and the average stress. The results of this section are of importance in fracture mechanics, failure theories, and crack propagation studies. (See Section 15.3.) One might question how, in the presence of such a high stress (oyy + m, as r + 0), the material can remain elastic, permitting the application of linear elastic fracture mechanics. In fact, at the tip of a sharp crack, it is

15.3

CRACK PROPAGATION AND THE STRESS INTENSITY FACTOR

555

possible for a state of high hydrostatic stress to exist (in a sufficiently thick member), whereas the maximum shear stress and distortional energy density remain low. Thus, brittle fracture may occur prior to yielding.

15.3 CRACK PROPAGATION AND THE STRESS INTENSITY FACTOR 15.3.1

Elastic Stress at the Tip of a Sharp Crack

In Section 14.2, we noted that the maximum stress at the ends of an elliptical hole in an infinite plate may be quite large. For example, when the plate is subjected to an edge tensile stress o i n the direction perpendicular to the major axis of the elliptic hole, the stress at the edge of the hole is given by Eq. 14.11. Hence, if the ratio u/b = 100, the value of opp(,,,) is 2010; if u/b = 1000, ~ p p c =~20010; ~ ) etc. The elliptical hole becomes very narrow and approaches the shape of an internal line crack as u/b + In this case, ~ P P ( -+~ 0~0, ~and ) we can no longer utilize the concept of stress concentration factor in describing the behavior around the crack tip. Physically, one might expect that when loads are applied to a member that contains a line crack, the extremely large stress at the tips of the crack will cause the crack to extend or propagate. Experiments bear out this expectation in that it has been observed that the crack may propagate when the load attains a critical nominal value.2 In general, under lower values of the applied stress o,the crack may propagate slowly a short distance and stop, whereas under higher values of o,the crack may propagate rapidly and continuously until a catastrophic separation of parts of the member occurs. For a given member made of a given material, cracks may propagate under conditions such that the material is in the ductile state or under conditions such that the material is in the brittle state (Section 15.1). If the dimensions of the member are such that the state of stress over most of the length of the crack tip is plane strain, the crack will propagate with minimum plastic deformation occurring at the crack tip. The material in such members is considered to be loaded in the brittle state. The state of stress outside the small plastic zone is assumed to be characterized by the elasticity solution presented in Section 15.2. In the discussion that follows, we assume that the materials are loaded in the brittle state. Investigators have attempted to explain the mechanism of crack propagation in terms of the distribution of stress in the neighborhood of the crack tip. However, in addition, to help explain the crack propagation, another concept is required. Earlier investigators, particularly Griffith, introduced the concept of strain energy release rate, G. The quantity G represents the amount of strain energy lost by the member per unit area of the newly formed crack as the crack propagates. This strain energy is used up in forming the new surface area of the crack. In other words, the energy required to form the surface area of the extended crack is obtained from the strain energy of the body. Since the dimensions of G may be written [F/L], G is referred to as the crack extension force. Hence, for a given geometry and material, a crack will propagate when the load reaches a level that produces a critical value G, of G. CQ.

'The capacity of the material to absorb relatively large amounts of energy per unit volume by plastic flow before fracture determines the level of nominal stress at which the crack propagates. In mild steel, a crack may not propagate until catastrophic fracture is imminent.

556

CHAPTER 15 FRACTURE MECHANICS

15.3.2 Stress Intensity Factor: Definition and Derivation To examine the stress distribution near the tip of a crack in a flat plate, consider a crack of length 2a, which is very small compared to the width and length of the plate (Figure 15.6). Let the plate be subjected to uniformly distributed stress in a direction perpendicular to the crack length 2a. As noted in Section 15.2, the elastic stress at the tip of the crack becomes infinitely large as the radius of curvature p at the tip goes to zero (Eq. 15.10). As shown in Section 15.2, (see Eq. 15.15 and Figures 15.5 and 15.6), the stress oyyalong the extension of the major axis (the expected path of crack propagation) is given by

- KI OYY -

7%

(15.17)

where r is the distance from the crack tip measured along the x axis and K I is the stress intensity factor for a mode I crack. (See Section 15.2 and Figure 15.1.) Following Irwin (1957), we define the stress intensity factor by means of the following limit: K - hm . -omax ./XP I - p+o 2

(15.18)

where p is the radius of curvature at the crack tip (Figure 15.6), and omax, the maximum stress at the crack tip, is a function of p; see Eqs. 15.9 and 14.13 for the case of an elliptical hole. Consequently, if we consider the line crack to be the limiting case of an elliptical hole, as b + 0, we obtain by Eqs. 14.13 and 15.18

(15.19) for Mode I propagation of an internal crack in a flat plate; see also Eq. 15.15. Values of KI for some other types of cracked members are listed in Table 15.2.

15.3.3

Derivation of Crack Extension Force G

Following concepts proposed by Griffith, one may derive a relationship between the crack extension force G and stress intensity factor K for various modes. For example, for a Griffith crack of length 2a, centrally located in a plate subjected to a uniformly distributed stress CT at edges far removed from the crack (Figure 15.5), the surfaces of the crack undergo a relative displacement of magnitude 2v under a Mode I separation (Figure 15.7). For a condition of plane strain (Paul, 1968), it may be shown that (Knott, 1979)

where v is Poisson’s ratio and E is the modulus of elasticity. The problem is to calculate the strain energy released when a crack of half-length a is extended to a half-length (a + 6a). For constant load CT, the release of potential energy is equal to the release of strain energy as 6a + 0. Alternatively, we may calculate the change in energy in the plate as a whole, by calculating the work done by the surface forces at the crack tip acting across the length Sa when the crack is closed from length (a + Sa) to length a. In other words, we may employ the principle of virtual work.

CRACK PROPAGATIONAND THE STRESS INTENSITY FACTOR

15.3

1

557

L7

t t t t t t t t t t t t t

+++++++++++++ U

FIGURE 15.6 Stress oyyalong major axis of ellipse.

F - - a d a a 4 FIGURE 15.7 Relative displacement of crack surfaces.

In terms of the crack extension force G, the energy change may be expressed in the form

a+Sa

G6a =

aYyvdx

(15.21)

a

where the plate thickness is taken as unity and, by Eq. 15.14, OYY

-

OX

.Jx2 - a 2 , -

a I x 5 a + 6a

(15.22)

and v is given by Eq. 15.20, where we let a + a + 6a and a Ix Ia + 6a. Letting r = x - a, we may write for sufficiently small r (Figure 15.7)

(15.23) 2v = 4 ( 1 - v 2 ) g & a , . / F r E

and, hence, with Eq. 15.21 we have 2 o2 a 6a J ( v ) 1 / z d r

G6a = 2 ( 1 - v )-

(15.24)

E 0

558

CHAPTER 15 FRACTURE MECHANICS

Integration of Eq. 15.24 with the convenient substitution r = 6a sin2 o yields for plane strain 2

2

G = ( 1 - v )nao = ( 1 - v 2 )-K; E E

(15.25)

where KI = o&a is the stress intensity factor for a Mode I opening (Figure 15.1, Table 15.2). For very thin sheets stressed in their plane, a plane stress state exists. Then the factor (1 - v2) is eliminated from the preceding equations. For example, Eq. 15.25 takes the form 2

G = - nao - - - K~ E E

(15.26)

where G and K are the crack extension force and the stress intensity factor for plane stress, Mode I displacement. In plates of “intermediate” thickness, the state of stress changes gradually from plane stress to plane strain as thickness increases (see Figure 15.8). Equation 15.25 (or Eq. 15.26) is usually used to determine the maximum size defect allowable for a given design stress. However, the maximum stress for a given crack length may also be determined by these equations.

15.3.4

Critical Value of Crack Extension Force

As noted in Section 15.1, under certain conditions of loading, a crack in a structural member may gradually increase in length as the load is increased. This period of gradual increase in crack length may be followed by a rapid (catastrophic) propagation of the crack, resulting in complete separation of two parts of the member. In certain fracture mechanics hypotheses, this rapid propagation of the crack is associated with a critical crack length a,. Alternatively, since G, the Griffith crack extension force, is related to the crack length a (Eq. 15.25), the rapid propagation of the crack (say for Mode I) may also be associated with G,c, a critical crack extension force under plane strain conditions, defined by 2

2

2

(1 - v )na,o = ( 1 - v 2 )-KIC GIC = E E

(15.27)

K, I

K IC t \Limiting

Specimen thickness

FIGURE 15.8 Variation of Kc with specimen thickness.

value

15.3

CRACK PROPAGATION AND THE STRESS INTENSITY FACTOR

559

where, analogous to GI,, the factor

KIc =

0Fc

(15.28)

is called the critical stress intensity factor for Mode I opening of the crack (Section 15.1). The factor Krc is also referred to as thefracture toughness (Knott, 1979). Typical values of K,, for several metals are listed in Table 15.1. These values have been obtained for elastic (plane strain) conditions according to ASTM standards and can be used in the design of the members shown in Table 15.2. If the fracture loads for these members are to be calculated with reasonable accuracy, it is necessary that the state of stress at the tip of the crack is plane strain over most of the length of the crack tip. This is ensured (Knott, 1979) by specifying that the crack half-length a (or crack length a when applicable) and thickness t of the cracked member satisfy the relation (see also Section 15.1, Eq. 15.2) 2

a, t 2 2 . 5 k )

(15.29)

The magnitude of the right side of Eq. 15.29 for each metal is listed (in millimeters) in Table 15.1. If the crack half-length a (or crack length a when applicable) is appreciably less than the value indicated by Eq. 15.29, the computed fracture load may be greater than the failure load for another mode of failure (yielding failure, for instance). If the thickness t of the member is small compared to the value given by the right side of Eq. 15.29, the state of s k s s approaches plane stress, appreciable yielding may occur at the crack tip, and the actual fracture load may be as much as several hundred percent greater than the value calculated using KIc.

EXAMPLE 15.2 Brittle Fracture for Combined Tension and Bending

A hook similar to that shown in Figure E15.2 is part of a scarifier used to dig up old road beds before replacing them. Let the tool be made of AISI 4340 steel and heat-treated to the properties indicated in Table 15.1. The dimensions of the tool are as follows: d = 250 mm, 2c = 60 mm, and the width of the rectangular cross section is t = 25 mm. Determine the magnitude of the fracture load P for a crack length of

(a) a = 5 mm and (b) a = 10 mm.

FIGURE E15.2

Solution

Note that both the width t and crack length a satisfy Eq. 15.29; therefore, the hook is assumed to be loaded in the brittle state. At a section through the crack, the hook is subjected to combined axial load (Case 4 of Table 15.2) and bending (Case 6 of Table 15.2). Since a linear elastic analysis is assumed, the state of stress for combined loading can be obtained by superposition of the two states of stress for the two types of loading. Thus,

of(1) =

q f l ( 1 )+ 0 2 f 2 ( &

560

CHAPTER 15 FRACTURE MECHANICS

(a) When a = 5 mm, A = a/2c = 0.083. From Table 15.2 for Cases 4 and 6, we obtainfi(A) = 1.22 and

f2(A)= 1.02. Therefore, P of(n) = -1.22 25(60)

+

3(280p) 1.02 = 0.0195P 2(25)(30)2

This is substituted in the relation

to give P = 5 9 m = 24,1000N = 24.1 kN 0.0195.6 (b) When a = 10 mm, A = 0.167 and

of(a) = -1.33+ 3(280P)(1.05) = 0.0205p 25( 60) 2( 25) (30)' P =

EXAMPLE 15.3 Determination ot Stress Intensity Factor

59m 0.0205

= 16,20ON= 16.2kN

A fracture test is performed on a steel plate with a central crack 2a = 100 mm. The yield stress of the steel is Y = 1500 MPa. The plate has a thickness t = 6 mm and a width of 800 mm. The plate is pulled in a tensile test machine until it fractures at a load of 1 MN.

(a) Use Case 3 of Table 15.2 to determine the value of the stress intensity factor KI at fracture. Assume that Eq. 15.2 is satisfied. (b) Determine whether or not the value of KI determined in part (a) is a valid value for KIP

Solution

(a) By the given data and Table 15.2, a = 50 mm and c = 200 mm. Hence, a/c = 0.25 and, by Case 3, Table 15.2,f(& = 1.045. Also, the nominal stress is o = 1 MN/(0.80 x 0.006 m') or cr= 208.33 MPa. so,

K, = o&af(il)

= (208.33)4=)(1.05)

or

K, = 86.28h4Pah (b) With KI = 86.28 M P a h and Y = 1500 MPa, Eq. 15.2 yields 2

2.5p]

= 0.00827 m

Equation 15.2 is satisfied for a = 0.050 but not for t = 0.006. Since the plate is so thin, a condition of plane strain does not exist at the crack tip. More nearly, a state of plane stress exists and the value KI= 86.28 M P a h is not valid for K,. Rather, the fracture toughness is referred to as Kc for the given parameters (material type, crack geometry, thickness, loading, and temperature). To have a valid KlC test, the thickness would need to be increased so that t > 8.3 mm.

EXAMPLE 15.4 Maximum Allowable Crack in a Thin Sheet

Large grain bins are fabricated with thin sheet metal of low-alloy steel. For a steel of ultimate stress 6,= 1300 MPa, the stress intensity factor is measured in a thin sheet to be 69 M P a h (see Example 15.3). The design code specifies a safety factor of 2.2. Determine the maximum allowable crack length of a central crack in the sheet of steel.

15.4

Solution

FRACTURE: OTHER FACTORS

561

For a thin sheet in plane stress, Eq. 15.26 gives the stress at fracture as

oc

=

KC -

& a Since a safety factor of 2.2 is specified,

o

oc = -!! = 590.0MPa 2.2

Hence, by Eqs. (a) and (b), with K, = 69 M P a h , 69 590.9 = & a or a = 0.00434m=4.34mm

EXAMPLE 15.5 Range of Fracture Stress Solution

Examination of a large number of thin metal sheets used in large grain bins shows that there exist central cracks ranging in length from 30 to 120 mm. Several tests of sheets with 30-mm cracks show that the average fracture stress is 600 MPa. What might we expect the average fracture stress to be for the sheets with 120-mm cracks? By Eq. 15.19,

where C = K I / h is a constant. For the 30-mm crack, 030= 600 MPa. Hence, by Eq. (a) with a = 15 mm, 600 = C(0.015)-’’2 or C = 600(0.015)”2

(b)

For the 120-mm crack, a = 60 mm. Hence, with Eq. (b), 1/2 0120 =

C(0.060)-’/2 = 6 0 0 ~ ~ 0 )

or 0120 =

300 MPa

15.4 FRACTURE: OTHER FACTORS In Sections 15.1-15.3, concepts related to the stationary crack and initiation of crack propagation in metallic materials were introduced for brittle fracture [linear elastic fracture mechanics (LEFM)]. As noted, however, many other factors that influence fracture are being researched today. Many of the factors pertain to secondary effects. Indeed, as noted by Broek (1988), “Too many ‘refinements’in engineering (fracture) solutions pertain to secondary errors; they increase the complexity, but do not improve the solution.” However,

562

CHAPTER 15 FRACTURE MECHANICS

some of these factors are of primary importance. For example, the topics of elastic-plastic fracture mechanics (EPFM; see Parton and Morozov, 1989), crack-growth analysis (fatigue, variable amplitude loading, etc.), load spectra and stress histories (statistical models; see Herrmann and Roux, 1990), testing and experimental data interpretation (Ewalds and Wanhill, 1986; Broek, 1988; Curbishley, 1988; Herrmann and Roux, 1990), environmental effects (Liebowitz, 1968, Vol. 111, 1971; Parton and Morozov, 1989), surface flaws, and residual stresses play important roles in fracture. The ultimate uses of the results of fracture mechanics studies are to control fracture and assess damage tolerances (Kachanov, 1986; Broek, 1988) and to develop fracture control plans that help to minimize the potential for brittle fracture (Barsom and Rolfe, 1999).

15.4.1

Elastic-Plastic Fracture Mechanics

In previous sections of this chapter, we examined conditions in which a crack may propagate. However, cracks or flaws differ in nature. At one extreme, the fracture of a crystal grain initiates from a submicroscopic crack produced when two atomic layers move apart. At the other extreme, the fracture of a pressure vessel may originate from a crack whose length and width are measured in millimeters (macroscopic crack and macroscopic fracture). Macroscopic fracture is due to macroscopic cracks whose dimensions are several orders of magnitude larger than the largest structural constituent of the material. Consequently, the problem can be treated as a problem in continuum mechanics. Thus, if we assume that the material is continuous, homogeneous, isotropic, and linearly elastic, we can use either the theory of linear elasticity or LEFM to compute the stresses in the neighborhood of a crack (Sections 14.3 and 15.2). However, the theory of linear elasticity leads to the conclusion that the stresses for a sharp crack grow without bound at the crack tip. Thus, for a real, brittle material, fracture will occur almost instantaneously at a critical stress. For a real, ductile material, plastic deformation will usually occur before fracture, and then, LEFM is not applicable. In this case, elastic-plastic fracture mechanics (EPFM) must be used (see Liebowitz, 1968,Vol. 111, 1971, Chapter 2; Broek, 1988, Chapter 4; Parton and Morozov, 1989; Hwang et. al, 1990; Clausmeyer et. al, 1991). The topic of EPFM is beyond the scope of this book.

15.4.2

Crack-Growth Analysis

The initiation of crack growth (crack propagation) is predicted by LEFM at a load for which the stress intensity factor KI reaches a critical value (KIc for the crack opening mode, see Section 15.3; see also Liebowitz, 1968, Vol. 111, 1971, Chapter 1; Broek, 1988; Parton and Morozov, 1989, Chapters 1 and 2). However, crack initiation and growth are strongly affected by several factors such as repeated loads (fatigue; see Chapter 16 and also Ewald and Wanhill, 1986), high temperatures (creep; Chapter 17), plasticity, and environmental conditions (see Liebowitz, 1968, Vol. 111; Broek 1988, Chapters 6 and 7).

15.4.3

Load Spectra and Stress History

As employed in Sections 15.1-15.3, LEFM predicts a critical value of load that initiates crack propagation. More generally, members of structures are subjected to load spectra and subsequent stress histories. The word spectra means any statistical representation of loads or stresses (Henmann and Roux, 1990). In the determination of damage caused by crack propagation, one must establish reliable prediction methods to estimate the number of load cycles

15.4

FRACTURE: OTHER FACTORS

563

that will result in a maximum permissible crack size for a given stress history (Broek, 1988, Chapter 6). The type of stress histories (constant amplitude loads, repeated loads, variable amplitude loads, impulse loads, etc.) and methods of obtaining load spectra [say, records obtained by strain-gage readings over long periods of time, power spectrum density analysis, exceedance diagrams from counts (peak, mean-cross peak, etc.) of the records] as well as other factors enter into the design problem of fracture control and the establishment of damage tolerance criteria. To simplify the process somewhat, many industries have established standard spectra for general use for a variety of structures (Broek, 1988).

15.4.4 Testing and Experimental Data Interpretation As noted in Section 15.1, the experimentally determined critical stress intensity Kc depends on the specimen thickness. For a very thin specimen (c1 mm thick), the value of Kc is not exactly certain. For a relatively thin specimen, a state of plane stress exists approximately, and the value of Kc determined experimentally is fairly large. As the thickness of the specimen is increased, there is a transition from a plane stress state to a plane strain state (Figure 15.8). For a given test temperature and loading rate, the value of Kc tends to a limiting (minimum) value. This minimum value of Kc is called the plane strain fracture toughness (e.g., KIc for the opening crack mode). The plane strain fracture toughness is considered to be a material property; however, it is dependent on temperature (Figure 15.3) and loading rate. After several years of testing (in the 1960-1970 period), a standardized plane strain KIc test method was developed for metallic materials by the American Society for Testing Materials (ASTM). Two standard test specimens, the singleedge cracked bend specimen and the compact tension specimen, were proposed (Figure 15.2). The method was first published in 1970, and it is described in ASTM standard E399 (ASTM, 1997). However, like most standards, this standard employs a number of compromises and approximations of data. The interpretation and use of plane strain fracture toughness and problems associated with the use of toughness data are discussed by Broek (1988, Chapter 7). The user of toughness data would be well advised to refer to Broek’s discussion (see also Ewalds and Wanhill, 1986, Chapter 5 ; Curbishley, 1988, Chapter 6; Herrmann and Roux, 1990; Barsom and Rolfe, 1999). In summary, fracture toughness testing and the use of fracture toughness data are still in the developmental stage. Much work still remains before structural integrity and damage tolerance assessments will be fully understood. Because of the limited space allotted here to these topics, our treatment is brief and incomplete. Indeed, the effects of environmental factors, residual stresses, and many current research topics are omitted. For example, fracture mechanics of ceramics, concrete, rock, wood, and masonry materials are not discussed (Mihashi et al., 1989). The interested reader may refer to the excellent references cited. In addition, much of the current research is documented in technical journals devoted exclusively to fracture mechanics. These include Engineering Fracture Mechanics, International Journal of Fracture, and Theoretical and Applied Fracture Mechanics. In addition, other journals contain articles on fracture mechanics, for example, Computer Methods in Applied Mechanics and Engineering, Experimental Mechanics, International Journal of Fatigue, and International Journal of Plasticity.

564

CHAPTER 15 FRACTURE MECHANICS

PROBLEMS Section 15.1

15.1. A circular shaft is made of gray cast iron, which may be = considered to be linearly elastic up to its ultimate strength o,, 145 MPa. The shaft is subjected to a moment M = 5.50 kN m and torque T = 5.00 kN m. Determine the diameter d of the shaft if the factor of safety against brittle fracture is SF = 4.00. 15.2. A piece of chalk of diameter d is subjected to an axial load P and a torque T.Assume that the chalk remains linearly elastic . axial load is P = o,,Ed2/12. up to the ultimate strength o ~The Determine the magnitude of the torque T that will cause brittle fracture. 15.3. A 50-mm-diameter shaft is made of a brittle material. The shaft is subjected to a static torque T = 1.20 kN m. A bending moment M is increased in magnitude until fracture occurs. The fracture surface is found to make an angle of 1.0 rad with a longitudinal line drawn on the shaft. If the maximum principal stress criterion of failure is valid for this material and loading, for the determine the magnitude of M and ultimate strength o,, material. 15.4. A circular shaft is made of gray cast iron, which may be considered to be linearly elastic up to its ultimate strength O, = 150 MPa. The shaft has a diameter of 125 mm and is subjected to a bending moment M = 7.50 kN m. Determine the maximum value for torque T that can be applied to the shaft if it has been designed with a factor of safety of 3.0 for both M and T.

15.5. Let the bending moment for Problem 15.4 be applied by a dead load that is known to remain constant with time. The variation of torque T with time is unknown. Determine the limiting value for T if the factor of safety for M remains 3.0, whereas the factor of safety for T is increased to 5.0. 15.6. A long strip of aluminum alloy 2024-T85 1 has a width of 150 mm and thickness of 8.0 mm. An edge crack of length a =

9.0 mm (Case 4 of Table 15.2) is located at one edge of the strip near the center of its length. Determine the magnitude of the axial load P that will cause brittle fracture.

15.7. The long strip in Problem 15.6 has a double-edge crack with a = 9.00 mm (Case 5 in Table 15.2). Determine the magnitude of the axial load P that will cause brittle fracture. 15.8. A 2024-T851 aluminum alloy pipe is used as a tension member. The pipe has an outside diameter of 100 mm and wall thickness of 8.0 mm. An inspection of the pipe locates a circumferential through-thickness crack having a length of 15.0 mm (Case 3 of Table 15.2). If the axial load P is increased to failure, will the failure be brittle fracture? What is the failure load? 15.9. Let the tension member in Problem 15.8 be made of AISI 403 stainless steel. If the axial load P is increased to failure, will the failure be brittle fracture? What is the lower limit for the failure load? 15.10. A 60.0-mm square beam is made of AISI 4340 steel that has been heat-treated to give the properties indicated in Table 15.1. On the tension side of the beam, a transverse crack has a depth of 8.0 mm (Case 6 of Table 15.2). Determine the magnitude of the moment M that will cause brittle fracture. 15.11. A simple beam has a span of 4.0 m, depth of 250 mm, and width of 100 mm. The beam is made of 6061-T651 aluminum alloy and is loaded by a concentrated load P at midspan. The design load for the beam has been calculated using a factor of safety of 3.0 and assuming the general yielding theory of failure. Determine the magnitude of P. An inspection of the beam located a transverse crack a distance of 1.50 m from one end. The crack has a depth of 24.0 mm. What is the factor of safety for the beam against brittle fracture?

Section 15.3

15.12. a. Show that Eq. 5.22 is approximated by the first of Eqs. 15.23 for r is applied are equal to Pmax(SF)/2= 0.9OPm,,. The reaction 0.90P,, produces a moment and torque of equal magnitude at the critical section at C. Thus, M = T = 0.90Pm,R

= 720P,,

The bending stress o resulting from M and shear stress z resulting from T at C are

The magnitude of P,, Thus,

is obtained by means of Eq. 4.46 when omax = 3 15 MPa is substituted for Y.

P,,

= 260N and Pmin= -216N

(b) For omin = -omax/2,we obtain om= oa/3. Substitution of this value of omalong with values for Y and o,, into Eq. 16.2 gives o,= 282 MPa and om,,= 376 MPa. Since omax is greater than r, failure of the member occurs by general yielding and not fatigue. Substitution of values of 6,Z,and Y into Eqs. 4.44 gives P,, = 285 N and Pmin= -142 N.

16.3

EFFECTIVE STRESS CONCENTRATIONFACTORS OTHER INFLUENCES

575

16.2 EFFECTIVE STRESS CONCENTRATION FACTORS: REPEATED LOADS The value of the stress concentration factor S,, for a notched member subjected to completely reversed repeated loads (fatigue) is obtained by comparison of data taken from two sets of test specimens. One set of specimens (5 to 10 specimens) is notch-free; the other set contains notched specimens. The significant stress in the notch-free specimens is the nominal stress as computed with an elementary stress formula. For the notched specimens, the nominal stress is again computed with the same elementary stress formula as for the notch-free specimens. Both sets of specimens are subjected to the same type of repeated load or fatigue test (say, bending). It is assumed that the failure (fracture) in each set of specimens for a specified number of completely reversed loading cycles N occurs when the stress attains the same value in each set. Since the notch causes a stress concentration, the load required to cause the fracture stress is less for the notched specimens. To illustrate the method of determining S,, for bending fatigue loading, consider the 0-N diagrams of Figure 16.6. The nominal stress is computed by the equation 0,= McJl and plotted as the ordinate in Figure 16.6; the abscissa is the number of cycles of bending stress to which the specimen is subjected. For a given value of N, say 300,000 cycles, the value of S,, is computed by taking the ratio of the failure stress of the notch-free specimen to the failure stress of the notched specimen. Thus, for N = 300,000 cycles, by Figure 16.6, we find S,, =

634.4 268.9

2.36

Likewise, for N = lo7 cycles we find S,,

620.6 = - 2.50 248.2

Thus, the value of S,, varies with N. By Figure 16.6, the value of S,, remains relatively constant for N > lo7, since the curves at N = lo7 are changing very slowly. In fatigue testing, the value of S,, is often based on the endurance limit of the steel (stress at N = lo7). For the specimen with a transverse hole (Figure 14.16), the calculated (elastic) stress concentration factor is S,, = 3.00. However, as shown by the results of fatigue tests for these specimens, the significant stress concentration factor is S,, = 2.5. Thus, there is a difference between the value of S,, and that of Scc, with the value of S,, being smaller. In the following section, additional conditions that influence the value of S,, are discussed.

16.3 EFFECTIVE STRESS CONCENTRATION FACTORS: OTHER INFLUENCES 16.3.1 Corrosion Fatigue Figure 16.6 shows the damaging effects that mechanical notches such as holes and fillets and so-called chemical notches such as corrosion pits are likely to have on the resistance of steel to repeated stress, particularly for alloy steels heat-treated to give high strength. The effect of corrosion that takes place while the material is being repeatedly stressed is much more damaging to the fatigue strength of steel than corrosion that takes place prior

576

CHAPTER 16 FATIGUE PROGRESSIVE FRACTURE

t

m Notch-free specimer n air, d =

specimen,in water

2

300

-Specimen with hole, . in air, d = 6.35 mm p = 0.56 mm, D = 12

200

!sted in water

io5

106

107

108

Cycles for rupture N

FIGURE 16.6 o-N diagrams showing the effect of abrupt changes in cross section and corrosion on the resistance of steel to repeated cycles of completely reversed bending stress. Quenched and tempered SAE 3140 steel was used for all tests. [From T. J. Dolan (1937). Bull. 293, Eng. Exper. Station. Urbana-Champaign, IL: Univ. of Illinois.]

to stressing (called stressless corrosion). This is mainly because in the absence of stress the products of corrosion tend to form a protecting film that excludes the corroding agent from contacting the metal. If, however, the rather brittle film is repeatedly stressed in the presence of the corroding agent, it cracks and allows the corroding agent to continue to attack the metal underneath the film.The effect of corrosion on the fatigue strength of steel is shown by the 0-N diagrams in Figure 16.6. For example, the quenched and tempered S A E 3140 steel tested indicated an endurance limit of approximately 620.5 MPa when tested in air (a relatively noncorrosive medium), and this was reduced to about 68.94 MPa when the specimens were tested in the presence of water; the presence of a small hole

16.3

EFFECTIVESTRESS CONCENTRATION FACTORS OTHER INFLUENCES

577

caused little further decrease in fatigue strength. Also, the shape of the 0-N diagram for stresses above the endurance limit was influenced greatly by the corrosion.

16.3.2 Effect of Range of Stress In Section 16.2, it was assumed that the member or specimen was subjected to repeated cycles of completely reversed stress; that is, in each stress cycle the stress varied from a given tensile stress to an equal compressive stress. If a specimen in which the stress is concentrated is subjected to repeated cycles of stress in which the stress is not completely reversed, it is convenient to consider the cycle or range of stress to be made up of a steady stress and a completely reversed (alternating) stress superimposed on the steady stress (see Section 16.1). There is considerable evidence (Eisenstadt, 1971) indicating that the damaging effect of the stress concentration in such a repeated cycle of stress is associated only with the completely reversed (alternating) component of the stress cycle and not with the mean stress in the cycle. Thus, the stress concentration factor for the particular discontinuity is applied only to the alternating stress component (see Example 16.4).

16.3.3 Methods of Reducing Harmful Effects of Stress Concentrations A problem that frequently arises in engineering is that of reducing the value of a stress concentration below the minimum value that will cause a fatigue fracture to occur or of raising the fatigue strength of the material so that fracture is avoided, rather than that of calculating the effective stress concentration. Some of the methods that have been employed in an attempt to reduce the damaging effects of localized stresses are the following:

1. Reducing the value of the stress concentration by decreasing the abruptness of the change in cross section of the member by use of fillets, either by adding or removing small amounts of material. 2. Reducing the value of the stress concentration by making the portion of the member in the neighborhood of the stress concentration less stiff; this may be done, for example, by removing material in various ways, as indicated in Figure 16.7. Sometimes it may be done by substituting a member made of material with a lower modulus of elasticity, such as replacing a steel nut on a steel bolt by a bronze nut to reduce the stress concentration at the threads of the steel bolt. 3. Increasing the fatigue strength of the material by cold-working the portions of the members where the stress concentrations occur; for example, by the cold rolling of fillets and bearing surfaces on axles, or by the shot blasting or shot peening of surfaces of machine parts. The increased fatigue strength of a member caused by local cold-working of the

(a)

(b)

FIGURE 16.7 Wheel shrunk on an axle subjected to bending (top half of a symmetric cross section). ( a )Stress concentration at A and 6.(b)Stress concentration reduced by removing material in the vicinity of A and B.

578

CHAPTER 16 FATIGUE: PROGRESSIVE FRACTURE

metal at the region of stress concentration in some cases may be due primarily to residual compressive stresses set up in the cold-worked metal by the surrounding elastic material as this elastic material attempts to return to its original position when the cold-working tool is removed, especially if the repeated cycle of stress is not reversed. Likewise, overstraining of the outer fibers of a beam or the inner fibers of a thick-walled pressure vessel or pipe may create favorable residual stresses (see Chapter 11). 4. Increasing the fatigue strength of the material by alloying and heat-treating portions of steel members that resist the high stress, by case hardening, nitriding, flame hardening, etc. In such treatments, however, care must be taken to avoid inducing tensile residual stresses. 5. Reducing the stress concentration by removing surface scratches, tool marks, small laps, and similar stress raisers to create a smooth surface by polishing. 6. Reducing the stress concentration by the prevention of minute surface corrosion pits by protecting the surface from acid fumes or moisture through the use of a corrosionresisting covering, as, for example, by encasing the member in grease or paint.

EXAMPLE 16.2 Slot in a Cantilever Beam

A cantilever beam is made of a flat bar of hot-rolled SAE 1020 steel. The beam contains a slot (Figure C of Table 14.3) with dimensions b = 10 mm, t = 50 mm, p = 5 mm, h = 25 mm, and c = 60 mm. Let the beam be subjected at its free end to a large number of completely reversed cycles of bending moment of maximum amplitude M. (a) Compute the significant value of the stress at the top or bottom of the slot (i.e., at the root of the notch) in terms of M, assume q is given by Figure 14.26.

(b) The maximum utilizable stress for this material under completely reversed cycles of stress is 172 MPa. Compute the allowable moment M based on a factor of safety of SF = 4.0.

Solution

(a) From Figure 14.10,S,, = 2.8, and from Figure 14.26 the value of q, the ordinate of the test data for SAE 1020 steel, is q = 0.94. Hence, by Eq. 14.43, S,, = 1 + 0.94(2.8- 1 ) = 2.70

The nominal stress onat the root of the notch (see Table 14.3, Figure C) is

on=

3Mt 3

3

2h(c - t )

-

3M(50) = 32.97 x 2(25)(603-503)

M

Hence, the significant (or effective) stress is

o, = S,,on

= 2.70 x 32.97 x

(b) The allowable (working) stress is ow= o,,/SF or M = 483,100 N mm = 483.1 N *m.

EXAMPLE 16.3 Long Narrow Slot in a Cantilever Beam

M

= 89.0 x

M

= 172/4.0= 43.0 MPa. Hence, 43.0 = 89.0 X

M

Let the cantilever beam of Example 16.2 be unchanged, except that p = 0.75 mm. Then the slot approaches a long crack in the bar. Compute the significant stress at the root of the notch.

16.3

Solution

EFFECTIVE STRESS CONCENTRATIONFACTORS OTHER INFLUENCES

579

(a) From Figure 14.10, we find that S ,, = 6.1. Figure 14.26 shows that, for fatigue tests of SAE 1020 steel, q = 0.69 when p = 0.75 mm. Hence,

S,, = 1 + 0.69(6.1 - 1) = 4.52

and the significant stress is 0, = S,,G,

= 4.52(32.97 x

M ) = 149.0 x

M

Comparison with the results of Example 16.2 shows that the value of S,, is increased 118%, whereas These the value of S,, is increased 67%, which corresponds to the increase in the significant stress 0,. ,, increases with a decrease in p , so does S,, but to a lesser degree. facts indicate that as S (b) The allowable stress is ow= 43.0 MPa. Hence, 43.0 = 149.0 x 288.6 N m.

M or M = 288,600 N mm =

EXAMPLE 16.4 Fillet in a Bar Subjected to a Range of Load

The filleted tension member in Figure 14.16 is made of 2024-T4 aluminum alloy (E = 72.0 GPa, v = 0 . 3 3 , ~ =" 470 MPa, Y = 330 MPa, and o,, = 190 Mpa for N = lo6 cycles). Perpendicular to the figure, the thickness of the member is 10 mm. The other dimensions are D = 59 mm, d = 50 mm, and t = p = 3.0 mm. The member is subjected to a tensile load ranging from Pmin= 20.0 IcN to P,,,. Assuming that q = 0.95, determine the magnitude of P,,, to produce fracture of the tension member in lo6 cycles. Also determine om,, and urnin.

Solution

The calculated stress concentration factor S,, for the fillet can be read from the curve, fillet t = p , in Figure 14.16, with p/d = 0.06. As read from the curve, S ,,

= 1.90

Since q = 0.95, Eq. 14.43 gives

S,, = 1 +0.95( 1.9- 1) = 1.86 Experimental evidence (Smith, 1942) indicates that S,, should be applied only to the alternating part of the stress. Therefore, it is convenient to work with nominal values of the stresses as follows: nomi= Pmin/A,nominal maximum stress G ~= P,,,/A, ~ nominal ~ ~alternating ) nal minimum stress nominal mean stress on,, and nominal fatigue strength onam = oam/Sce. stress ona, Since 2024-T4 aluminum alloy is a ductile metal, we assume that the Gerber relation, Eq. 16.2, is valid when written in terms of nominal stress values. Thus,

Equation (a) can be interpreted graphically in Figure 16.5; each ordinate to curve AB is reduced in magnitude by the factor I&,. Nominal stress relations are defined as follows:

580

CHAPTER 16 FATIGUE PROGRESSIVEFRACTURE

Substitution of Eqs. (c) and (e) into Eq. (a) gives

on,= 93.9 MPa which when substituted into Eq. (d) gives

crnn(max) = 40.0 + 2(93.9) = 227.8 MPa = Pmax A

P,

= 227.8(50)(10) = 113,900 N = 113.9 kN

The assumption that the effective stress concentration factor should be applied only to the alternating part of the stress defines the maximum and minimum stresses in the member at the stress concentration as

omax = om

+ Sc,on,

= 133.9 + 1.86(93.9) = 308.6 MPa

omin = on, - S,,o,, = -40.8 MPa

(f)

Because the load cycles between a tensile load of 20.0 kN and a tensile load of 114 kN, the negamay be suspect. The maximum and minimum stresses given by Eqs. (f) give the tive sign for omin correct range in stress at the stress concentration for linearly elastic conditions; however, the values given by Eqs. (f) can be only a rough approximation of their true magnitudes. If residual stresses are not present at the stress concentration,linearly elastic analysis gives the maximum stress at the stress concentration as ScZm,/A = 432.8 MPa, which exceeds the yield stress of the material. Plasticity theories and experimental evidence indicate that plastic deformation in the region of the stress concentration produces residual stresses that result in a reduction of the mean stress at the stress concentration. The residual stresses at the stress concentrationhave a sign opposite to the sign of the stresses that caused the inelastic deformation. Thus, the residual stresses decrease the magnitudes of both om,, and omin so that the values given by Eqs. (f) are realistic.

16.4 LOW CYCLE FATIGUE AND THE E-N RELATION 16.4.1

Hysteresis Loop

Figure 16.8 shows the final state of a stabilized stress-strain hysteresis loop. It is obtained by applying a large number of loading and unloading cycles to an axial test specimen (Figure 16.9) under strain-controlled conditions (Morrow, 1965; see also Figure 4.4b for a stress-strain curve for a partial cycle of a strain hardening material). In Figure 16.8, 0, is the stress amplitude, et is the total strain amplitude, eP is the plastic strain amplitude, and E , is the elastic strain amplitude. Modem testing machines may allow either the stress amplitude or the total strain amplitude to be held constant during cycling. In some cases even the plastic strain may be held constant. The area inside the hysteresis loop is the energy per unit volume dissipated during a cycle, usually in the form of heat. The axial test specimens, with circular cross section, usually have minimum diameters between 3 and 10 mm and are finely polished to minimize surface roughness effects (Figure 16.9). For notched specimens subjected to cyclic loads, the material behavior consists of an elastic region that surrounds a plastic zone at the notch. In such cases, the strains can be calculated more easily than the stresses. This fact has led to strain-controlled testing and a finite life design criterion based on relating fatigue life of notched members to the fatigue life of small unnotched specimens that are cycled to the same strain amplitude that exists

16.4

LOW CYCLE FATIGUE AND THE E-NRELATION

Stress

581

I

FIGURE 16.8 Hysteresis loop.

FIGURE 16.9 Typical axial fatigue test specimen with threaded ends.

at the notch root of the member. The material properties required for this procedure have been extensively recorded (SAE, 1975). These properties are obtained from failure tests of small, polished, unnotched axial fatigue specimens (Figure 16.9) under constant-amplitude, full-reversed cycles of strain (Morrow, 1965). Fatigue life can range from about N = 10 cycles to N = lo6 cycles for frequencies from 0.2 to 5.0 Hz. ForN > lo6, because of the small plastic strains and the greater time to failure, higher frequencies are usually required. For N < lo5, the fatigue test data are usually referred to as low cycle fatigue data.

16.4.2

Fatigue-Life Curve and the E-N Relation

Relations between the plastic strain amplitude and the number of cycles to fracture were first presented in early 1950. Papers by Manson (1954) and Coffin (1954) were based on empirical low cycle fatigue data. They related plastic strain amplitude epto the fatigue life N on log-log axes. The Manson-Coffin relationship between epand N can be written in the form E

P

= ~ i ( 2 N ) ~

(16.4)

582

CHAPTER 16 FATIGUE PROGRESSIVE FRACTURE

where E; is the fatigue-ductility coefficient given by the extrapolation of the MansonCoffin formula to the first half-cycle (2N = 1) and c is the slope of the Manson-Coffin curve fitted to experimental data on log-log plots. The exponent c ranges approximately from -0.5 to -0.7, with an average value of about -0.6. Surprisingly, it has been shown that Eq. 16.4 holds for many metals down to a value of ep of the order lop5, which corresponds approximately to N of the order lo7 (Luk& and Klesnil, 1973). It is also of interest to note that experimentally determined o-N curves may be represented by the equation b

oa = of(2N)

(16.5)

In this equation, oi is the fatigue-strength coefficient given by extrapolation of the o-N curve to the first half-cycle (2N = l), and b is the slope of the o-N curve fitted to experimental data plotted on log-log scales. The exponent b varies approximately from -0.06 to -0.14 for most metals, with an average value of about -0.10. For many metals, &. 16.5 fits the experimental data for both low and high cycle regions. Many machine and automobile parts are subjected to constant total strain amplitude E ~ which , consists of two parts: E ~ the , plastic strain amplitude, and E , , the elastic strain amplitude. The elastic strain amplitude in an axial test specimen is related to the stress amplitude oaby Hooke's law (16.6) where E is the modulus of elasticity. Then, in terms of the total strain amplitude, the fatigue life relation is obtained by Eqs. 16.4-16.6 as et =

E, + E

o f

P

= -(2N) E

b

+ E ; (2N)'

(16.7)

Equation 16.7 represents the superposition of the o-N curve (Eq. 16.5) and the MansonCoffin curve (Eq. 16.4). These equations employ true stress and true strain (Boresi and Chong, 2000;see also Section 1.3 and Eq. 1.12), whereas engineering stress and engineering strain are obtained from the hysteresis loop (Figure 16.8). However, since the engineering strains of the hysteresis loop are small (usually less than lo-*; Morrow, 1965), the error in using engineering stress and strain in these equations is small. Strain-life curves may be plotted on log-log scales as shown schematically in Figure 16.10, where N is the number of complete load cycles and 2N is the number of reversals to failure. In Figure 16.10 the total strain amplitude has been resolved into elastic strain E , and plastic strain ep (Eq. 16.7), obtained from the steady-state hysteresis loop (Figure 16.8). It has been found that for many metals the elastic and plastic curves can be approximated by straight lines on log-log plots. For a given life N,the total strain e t is the sum of the elastic and plastic strains (Eq. 16.7 and Figure 16.10). At a certain life 2Nc, the elastic and plastic strains are equal. The value Nc is sometimes called the transitional or cross-over number of cycles. At large strains or short fatigue lives, 2N < 2Nc, the plastic strain component governs; at small strains or long fatigue lives, 2N > 2Nc, the elastic strain component controls, as shown by the straight lines and hysteresis loops at various levels of total strain (Figure 16.10). At 2N = 1, the plastic strain line intercepts the strain axes at E ; , the fatigue-ductility coefficient, and the elastic strain line interceptsthe strain axis at of/E, where ofis the fatigue-strength coefficient and E is the modulus of elasticity.

16.4

I

LOW CYCLE FATIGUE AND THE s-NRELATION

I 2%

1

583

2N

Reversals to failure (log scale)

FIGURE 16.10 Strain-life curves.

Three different failure criteria have been used in the literature: 1. Fatigue life to the occurrence of a small detectable crack

2. Fatigue life to a certain percent decrease in load for constant strain cycling 3. Fatigue life to fracture These three criteria may predict widely different fatigue lives, depending on the type of metal under consideration. Figure 16.11 is a schematic showing general differences in metals subjected to strain-controlled tests of unnotched smooth axially loaded specimens. Many metals have about the same life at low cycles (N = lo3) for a total strain amplitude of et = 0.01. In other words, at a strain amplitude of 1%, the fatigue life of many metals is about N = 1000 cycles. At large strains (Figure 16.11) ductile metals exhibit increased life, whereas at small strains longer life is obtained from high-strength metals. Here, life may be measured by any one of the three preceding criteria.

I I

T

i

g

I 2N = 2000 2N (log scale)

FIGURE 16.11 Relative strain-life curves for different metals.

High h toughness strength High ductility

584

CHAPTER 16 FATIGUE: PROGRESSIVE FRACTURE

In application of the third fracture criterion, the crack may range from about 10% up to 70% of the cross section of the test specimen. Since test specimens have diameters between 3 and 10 mm, strain-life fracture is based on cracks that grow to a depth of 0.10 to 2.3 mm. The actual depth depends on strain amplitude, modulus of elasticity, and fracture toughness. The two other failure criteria are based on cracks of less than 0.10 mm. Such cracks are not easily determined or do not cause sufficient decrease in load amplitude to terminate a test. Hence, in strain-life testing of unnotched smooth specimens, fatigue life to failure may be interpreted as fatigue life (N cycles) to crack lengths between 0.1 and 2.3 mm. The effects of mean stress 6, or mean strain E , on strain-life data are extremely complex (Klesnil and Luc&, 1992; Koh et al., 1999; Lagoda et al., 2001; Kwofie and Chandler, 2001). Many procedures for the evaluation of the effect of mean stress on fatigue life have been proposed. One of them proposed by Landgraf (1970) is widely used, especially for steels, and consists of replacing 0;by (0; - 6,) in Eq. 16.7.

EXAMPLE 16.5 Fatigue Life ol 4340 Steel

The strain-life equation for 4340 steel, based upon test results of eleven specimens (Graham, 1968), is et = ep + E , = 0.58(2N)-

0.57

+ 0.0062(2N)-0'09

(a)

(a) Determine the total strain etC for the case ep= E,, that is, at 2N = 2Nc (see Figure 16.10). (b) Determine the total strain for 2N = lo6 load reversals. (c) Determine the number of cycles N expected for a fatigue test with constant total strain amplitude E t = 0.01.

Solution

(a) From Eq. (a), eP = 0.58(2N)4.57 and

= 0.0062(2N)4.09. So, for ep =

E,

E ~ we .

obtain N , =

6390 cycles. Then, by Eq. (a), etC = 0.58[ 2( 6390)]-0.57 + 0.0062[ 2( 639O)]-O.O9

or etC =

0.00529

(b) For 2N = lo6 load reversals, Eq. (a) yields 6

-0.57

et = 0.58(10 )

6 -0.09 +0.0062(10 )

or Et

= 0.00201

(c) For e t = 0.01, Eq. (a) yields

0.01 = 0.58(2N)-0.57+ 0.0062(2N)-0'09 The solution of this equation is

N = 1184 cycles This result agrees with the fact that, for et = 0.01, the fatigue life of many metals is about N = 1000 cycles,

PROBLEMS

585

PROBLEMS Section 16.1

16.1. A tension member is cycled an indefinitely large number of times from Pmin= -10.0 kN to P,,, = 16.0 kN. The member is made of steel (6,= 700 MPa, Y = 450 MPa, and om = dL= 350 MPa). Using the Gerber relation, determine the diameter of the rod for a factor of safety SF = 2.20. 16.2. Let the tension member in Problem 16.1 be cycled an indefinitely large number of times between Pmin= 0 and P, = 16.0 kN. Determine the diameter of the tension member for a factor of safety SF = 2.20. What is the mode of failure? 16.3. A cast-iron I-beam has a depth of 150 mm, width of 100 mm, and equal flange and web thicknesses of 20 mm. The beam is subjected to lo6 cycles of loading fromMmin= 5.00 kN m to M,,. Consider the cast iron to be a brittle material (6,= 200 MPa and a , , = 90.0 MPa for N = lo6). Using the Goodman relation, determine M,, based on a factor of safety SF = 2.50. 16.4. A thin-wall cylinder is made of 2024-T4 aluminum alloy (6,= 430 MPa, Y = 330 MPa, and o,, = 190 MPa for N = lo6). The cylinder has an inside diameter of 300 mm and a wall thickness of 8.0 mm. The ends are strengthened so that fatigue failure is assumed to occur in the cylinder away from the ends. The pressure in the cylinder is cycled lo6 times betweenpmin= -2.0 MPa and pmax= 7.0 MPa. What is the factor of safety against fatigue failure if design is based on the Gerber relation? 16.5. A shaking mechanism of a machine has a crank shown in Figure P16.5. The crank is made of a stress-relieved coldworked SAE 1040 steel (6,= 830 MPa, Y = 660 MPa, and om = oL= 380 MPa). A completely reversed load P = 500 N is applied for up to 10' cycles to the crank pin, normal to the plane of the crank. Determine the diameter d of the shaft based on a factor of safety SF = 1.75 using the octahedral shear-stress criterion of failure. 16.6. The crank in Problem 16.5 has a diameter d = 15.0 mm and is made of 2024-T4 aluminum alloy (0,= 430 MPa, Y = 330 MPa, and 6, = 160 MPa for N = 10'). Let the load vary between 0 and P,,, = 500 N for 10' cycles. Assume that the Gerber relation (Eq. 16.2) is valid. a. Is the design governed by general yielding or fatigue failure? b. Determine the magnitude of the safety factor SF used in the design based on the octahedral shear-stress criterion of failure. 16.7. The shaft in Figure P16.7 is supported in flexible bearings at A and D, and two gears B and C are attached to the shaft at

80 mm-

%

-7 55 mm

FIGURE P16.5

the locations shown. The gears are acted on by tangential forces as shown by the end view. The shaft is made of SAE 1040 steel (6, = 830 MPa, Y = 660 MPa, and 6, = oL= 380 m a ) . If the shaft is rotated under constant load an indefinitely large number of times, determine the diameter of the shaft for a factor of safety SF = 2.0 for the initiation of fatigue failure.

3.00 kN

A

UA

I f

150mm

6.00 kN

FIGURE P16.7

16.8. A 30.0-mm diameter shaft is subjected to cyclic combined .t~enamg .. ana. torsion . ioaamg . .. such. mat . M._ ---- .- .--= L w r ana 1 = I ~ W , where the magnitude of P varies from Pmin= -O.60Pm, to P,, and length is measured in millimeters. The shaft is made of a stress-relieved cold-worked S A E 1060 steel (6,= 810 MPa, Y = 620 MPa, and om = oL = 410 m a ) . Using a for lo7 cycles of factor of safety SF = 1.80, determine P, loading. Use the octahedral shear-stress criterion of failure and the Gerber relation.

Sections 16.2 and 16.3

16.9. The crankshaft in Figure P16.5 has a diameter d = 13.0 mm. Let a small-diameter hole be drilled in the crankshaft at a location 50 mm from the load P (measured along the axis of the shaft). Determine the magnitude of the completely reversed load P that can be cycled 10' times based on a factor of safety

SF = 1.75. Assume that q = 1.OO.Material properties are given in Problem 16.5. 16.10. The load P in Problem 16.9 is cycled from zero to P,,. Determine the magnitude of P, for 10' cycles based on a factor of safety SF = 1.75. Material properties are given in

586

CHAPTER 16 FATIGUE: PROGRESSIVE FRACTURE

Problem 16.5. Assume that q = 0.90 and that the Gerber relation is valid when expressed in terms of nominal stress values [see Eq. (a) of Example 16.41. Since the state of stress at the hole is uniaxial, we define S,, for the stress concentration as the ratio for the crankshaft with the hole to omax for the crankof omax shaft without the hole.

16.11. A crankshaft has a fillet and minimum diameter of 30 mm. Its critical section is subjected to a bending moment M = 200P and a torque T = 18OP, where P is a completely reversed load. The calculated stress concentrations for the fillet = 2.50 for bending and )\$: = 2.00 for torsion. The are S:)i shaft is made of a stress-relieved cold-worked SAE 1060 steel (E = 200 GPa, v = 0.29, ou= 810 MPa, Y = 620 MPa, and o,, = 410 MPa for lo7 cycles). Determine the completely reversed load P that can be applied lo7 times based on a factor of safety SF = 2.20. Assume q = 0.85. 16.12. Let the crankshaft in Problem 16.11 be subjected to a range of load from zero to P,,,. Determine the completely reversed load P,,, that can be applied lo7times based on a factor of safety SF = 2.20. Assume that the Gerber relation is valid when expressed in terms of nominal stress values [see Eq. (a) of Example 16.41. Use the maximum shear-stress criterion of failin ure; therefore, assume that s,, for the fillet is the ratio,,,z in the crankshaft without the crankshaft with the fillet to, , ,z the fillet. 16.13. A tension member has a hole drilled at its center, similar to the member in Figure 14.16. The dimensions of the member are w = 20 mm perpendicular to the figure, D = 60 mm, and p = 5.0 mm. The member is subjected to a tension load that cycles between Pmin= 30.0 kN and P,,,. The member is made of 2024-T4 aluminum alloy, with properties E = 72.0 GPa, v = 0.33, o,, = 470 MPa, Y = 330 MPa, and o,, = 190 MPa (determined by testing a smooth specimen to N = lo6 cycles).

a. Determine the magnitude of P,

to produce general fatigue fracture of the member in lo6 cycles (see Example 16.4). Assume that fracture occurs at the hole section.

FIGURE P16.14

16.16. For the member in Problem 16.14, determineP,,, if the member fails in 10' cycles of load from Pmin= -100 kN to Pmar

16.17. A rectangular cross section cantilever beam is made of steel (E = 200 GPa, o,= 590 MPa, and o,, = 220 MPa for lo6 completely reversed cycles of load); see Figure P16.17. Determine the magnitude of load P to cause failure at lo6 cycles of completely reversed load, based on a factor of safety of 2.20.

FIGURE P16.17

16.18. Solve Problem 16.17 for the case where the load is ,. (See Example 16.4.) cycled from 0 to P 16.19. The beam in Figure P16.19 is made of 2024-T4 alumi= 470 MPa, and num alloy (E = 72.0 GPa, Y = 330 MPa, o,, o,, = 170 MPa for lo7 cycles of completely reversed load). The beam is subjected to lo7 completely reversed cycles of load P. If h = 200 mm and p = 25.0 mm, determine the magnitude of P, based on a factor of safety of 1.80.

b. Determine the maximum and minimum stresses at the edge of the hole, assuming that the stress concentration factor need be applied only to the alternating component of stress (see Example 16.4).

n

1t

POrnrn

16.14. A rectangular cross section tension member made of a ductile material (Y = 350 MPa and om = oL = 280 MPa at 10' cycles of completely reversed axial load) has semicircular grooves (Figure P16.14). The thickness of the member is 40 mm.

a. Determine the failure load for static loading. b. Determine the failure load for 10' cycles of completely reversed axial load.

16.15. For the member in Problem 16.14, determine P, member fails in 10' cycles of load from Pmin= 0 to P,,,.

if the

250+mm

FIGURE P16.19

16.20. Solve Problem 16.19 for the case where P is cycled lo7 times from 0 to P,,,. (See Example 16.4.) 16.21. The tension member in Figure P16.21 has a thickness of 60 mm. The member is made of 2024-T4 aluminum alloy. The member is subjected to lo6 completely reversed cycles of load-

PROBLEMS

587

ing. The fatigue strength for N = lo6 is o,, = 220 MPa. What is the design load based on a factor of safety SF = 2.20?

16.22. Solve Problem 16.21 for the case where the load is cycled between Pmin= 0 and P,,.

FIGURE P10.21

Section 16.4

16.23. Let engineering stress and strain be denoted by S and e, respectively. Similarly, let o and E denote true stress and true strain. For a uniaxial test specimen subjected to an axial tension load P

e = - A10 ,

I, + Al, E

=

dl

(a)

1, 10

where A, is the original cross-sectional area, A is the instantaneous cross-sectional area, 1, is the original gage length, and Al, is the change in 1., a. Show for constant volume (A1 = Aolo) that

o = S(l +e) E

= ln(l+e)

(b)

b. Determine the differences between d and s and between and e for engineering strains of 1%, 2%, 4%, and 10%.

E

c. For 4340 annealed steel (see Example 16.5), determine the range of engineering strain for which the use of engineering stress and strain in Eq. 16.7 is reasonable.

16.24. From fatigue tests of smooth uniaxial test specimens of i = 1500 MPa, E; = 0.61, b = -0.14, 1040 steel, as forged, o c = -0.57, and E = 200 GPa. Use Eq. 16.7 to determine the following:

a. The plastic, elastic, and total strain amplitudes for lives of N = lo3 cycles, N = lo5 cycles, and N = lo7 cycles

b. 35 Hz (approximate speeds of most modem test machines) c. 160 HZ

test machines)

Note: The majority of conventional high cycle fatigue tests are conducted in the frequency range of 30-300 Hz (Curbishley, 1988).

16.26. To overcome the extensive time and cost required to run fatigue tests, Eq. 16.7 can be replaced by the following relation proposed by Manson (1965) and Muralidharon and Manson (1988), which is known as Manson's universal slope equation:

et = 1.75

(5)

N-O'I2 + O . ~ ( E Y ) N - " ~

(a)

where the slope coefficients b = -0.12 and c = -0.6 are fixed for all materials and where the ultimate tensile strength S,, the modulus of elasticity E, and the true fracture strain E~ are obtained from a single static tension test. For 4340 annealed su = 827 = 200 GPa, and € f = OS7-

a. Rework Example 16.5 using Eq. (a) and compare the results to those obtained in Examule 16.5. b. Comment on any differences in the results and their significance.

16.27. Rework Problem 16.24 using the Manson universal slope equation

b. The total strain amplitude for N = N,, the cross-over or transitional fatigue life

c. The number N of cycles expected for a fatigue test of 1040 steel, with constant total strain amplitude et = 0.01 16.25. Fatigue test data are required in an engineering design for = lo3 = lo5 and = lo7 calculate the time required by the tests in hours (or days) for frequencies of

a. 1 Hz (test speeds of pioneers in fatigue testing)

where the slope coefficients b = -o.12 and = -o.6 are fixed for all materials and where the ultimate tensile strength S,, the modulus of elasticity E , and the true fracture strain E f are obtained from a single static tension test. For 1040 steel, as forged, S, = 621 MPa, E = 200 GPa, and E~ = 0.93.

588

CHAPTER 16 FATIGUE: PROGRESSIVE FRACTURE

REFERENCES ~

(ASM) (1975). Metals Handbook, 8th ed., Vol. 10, Failure Analysis and Prevention, pp. 95-125. Metals Park, Ohio. ANONVMOUS(1967). Wohler’s Experiments on the Strength of Materials. Eng., 207: 10. BORESI,A. P., and CHONG,K. P. (2000). Elasticity in Engineering Mechanics, 2nd ed. New York: Wiley-Interscience. BUCH,A. (1988). Fatigue Strength Calculation, Materials Science Surveys, No. 6. Brookfield, VT:Trans Tech. Publications, Brookfield Publ. BUCH,A,, SFZGER,T., and V O W K D , M. (1986). Improvement of Fatigue Life Prediction Accuracy for Various Realistic Loading Spectra by Use of Correction Factors. Int. J. Fatigue, 8: 175. BUXBAUM, O., KLATSCHKE, H., and OPPERMAN, H. (1991). Effect of Loading Sequence on the Fatigue Life of Notched Specimens Made from Steel and Aluminum Alloys. Appl. Mech. Rev., 44(1): 27. CLARKE, W. L., and GORDON, G. M. (1973). Investigation of Stress Corrosion Cracking Susceptibility of Fe-Ni-Cr Alloys in Nuclear Reactor Water Environments. Corrosion, 29, Part 1: 1-12. C o r n , L. F., JR.(1954). A Study of Cyclic-ThennaI Stresses in a Ductile Metal. Trans. ASME, 76: 931-950. CURBISHLEY, I. (ed.) (1988). Mechanical Testing: Characterization of High-Temperature Materials, Chapter 3. London: Inst. of Metals. EISENSTALYT, M. M. (1971). Introduction to Mechanical Properties of Metals. New York: Macmillan. FUCHS,H. O., and S m m s , R. I. (1980). Metal Fatigue in Engineering. New York Wiley. GAUTHIER, J. P., and m u m , P. (1989). High Cycles Fatigue of Austenitic Stainless Steels under Random Loading. Nucl. Eng. Design, 116: 343-353. GRAHAM,J. A. (ed.) (1968). Fatigue Design Handbook (from a report by J. Morrow), p. 24. New York: SOC.of Automotive Eng. ==NIL, M., and Lu&, P. (1992). Fatigue of Metallic Materials, 2nd revised ed. Materials Science Monograms, 71. New York: Elsevier Science Publ. KLIMAN, V. (1985). Fatigue Life Estimation under Random Loading Using Energy Criterion. Int. J. Fatigue, 7: 39. KNOTT, J. F. (1979). Fundamentals of Fracture Mechanics, 2nd ed. New York Wiley. AMERICAN SOCIETY FOR METALS

~

~~

KOH,S. K., OH, S. J., Li, C., and ELLYIN,F. (1999). Low-Cycle Fatigue Life of Sic-ParticulateReinforced AI-Si Cast Alloy Composites with Tensile Mean Strain Effects. Int. J. Fracture, 21(10): 1019. KWOFIE, S., and CHANDLER, H. D. (2001). Low-Cycle Fatigue under Tensile Mean Stresses Where Cyclic Life Extension Occurs. Int. J . Fatigue, 23(4): 341. LAGODA, T., M.4CH.4, E., and PAWLICZEK, R. (2001). The Influence of Mean Stress on Fatigue Life of lOhnap Steel Under Random Loading. Int. J . Fatigue, 23(4): 283. LANDGRAF, R. W. (1970). The Resistance of Metals to Cyclic Deformations. Achievement of High Fatigue Resistance in Metals and Alloys, ASTM STP 467, p. 3. M. (1973). Strain-Life Applied to High-Cycle LWJ.5, P., and -NIL, Fatigue. Materials Sci. Eng., 11: 345. MiWSON, S. S. (1954). Behavior of Materials under Conditions of Thermal Stress. NACA Tech Note 2933. MANSON, S. S. (1965). Fatigue: A Complex Subject-Some Simple Approximations.Exp. Mech., 5(7): 193. MANSON, S. S. (1981). Thermal Stress and Low-Cycle Fatigue. Melbourne, FL: Kreiger. MORROW,J. (1965). Cyclic Plastic Strain Energy and Fatigue of Metals. Internal Friction, Damping, and Cyclic Plasticiq, ASTM STP 378, p. 45. MURALIDHARAN, U., and MANSON, S. S. (1988). Simplified Life-Cycle Equation. J. Eng. Materials Tech., 110:55. SAE (1975). Technical Report on Fatigue Properties. Society of Automotive Engineers J1099. S m R , B. I. (1972). Fundamentals of Cyclic Stress and Strain. Madison: Univ. of Wisconsin Press. SKELTON, R. P. (1988). Fatigue Crack Growth. In Mechanical Testing (I. Curbishley, ed.), Chapter 3. Brookfield, V T Inst. of Metals. S m , A. I., and NICOLSON,A. M. (1971). Advances in Creep Design. New York: Halsted Press Div. Wiley. S m , J. 0.(1942). Effect of Range of Stress on the Fatigue Strength of Metals. Urbana-Champaign, IL: Univ. Ill., Bull. 334, Eng. Exper. Station. S ~ E D., F. (1977). Fatigue Life Prediction Using Local Stress-Strain Concepts. Exper. Mech., 17(2): 50. WERONSKI, A,, and KUWOWS~,T. (1991). Thermal Fatigue of Metals. New York: Marcel Dekker.

CHAPTER

17

CONTACT STRESSES

17.1 INTRODUCTION Most load-resisting members are designed on the basis of stress in the main body of the member, that is, in portions of the body not affected by the localized stresses at or near a surface of contact between bodies. In other words, most failures (by excessive elastic deflection, yielding, and fracture) of members are associated with stresses and strains in portions of the body far removed from the points of application of the loads. In certain cases, however, the contact stresses created when surfaces of two bodies are pressed together by external loads are the significant stresses; that is, the stresses on or somewhat beneath the surface of contact are the major cause of failure of one or both of the bodies. For example, contact stresses may be significant at the area 1. between a locomotive wheel and the railroad rail, 2. between a roller or ball and its race in a bearing, 3. between the teeth of a pair of gears in mesh, 4. between the cam and valve tappets of a gasoline engine, etc. We note that, in each of these examples, the members do not necessarily remain in fixed contact. In fact, the contact stresses are often cyclic in nature and are repeated a very large number of times, often resulting in a fatigue failure that starts as a localized fracture (crack) associated with localized stresses. The fact that contact stresses frequently lead to fatigue failure largely explains why these stresses may limit the loadcarrying capacity of the members in contact and hence may be the significant stresses in the bodies. For example, a railroad rail sometimes fails as a result of “contact stresses”; the failure starts as a localized fracture in the form of a minute transverse crack at a point in the head of the rail somewhat beneath the surface of contact between the rail and locomotive wheel. This fracture progresses outwardly under the influence of the repeated wheel loads until the entire rail cracks or fractures. This fracture is called a transverse fissure failure. In contrast, bearings and gear teeth sometimes fail as a result of formation of pits (pitting) at the surface of contact. The bottom of such a pit is often located approximately at the point of maximum shear stress. Steel tappets have been observed to fail by initiation of microscopic cracks at the surface that then spread and cause flaking. Chilled cast-iron tappets have failed by cracks that start beneath the surface, where the shear stress is highest, and spread to the surface, causing pitting failure. The principal stresses at or on the contact area between two curved surfaces that are pressed together are greater than at a point beneath the contact area, whereas the maximum shear stress is usually greater at a point a small distance beneath the contact surface. The problem considered here initially is to determine the maximum principal (compressive) and shear “contact stresses” on and beneath the contact area between two ideal elastic bodies having curved surfaces that are pressed together by external loads. Several investigators have attempted to solve this problem. H. Hertz (1895) was the first

589

590

CHAPTER 17 CONTACT STRESSES

to obtain a satisfactory solution, although his solution gives only principal stresses in the contact area.’ See Johnson (1985) for a thorough treatment of contact stresses.

17.2 THE PROBLEM OF DETERMINING CONTACT STRESSES Two semicircular disks made of elastic material are pressed together by forces P (Figure 17.1). The two bodies are initially in contact at a single point. Sections of the boundaries of the two bodies at the point of contact are smooth curves before the loads are applied. The principal radii of curvature of the surface of the upper solid at the point of contact are R , and R;. Likewise, R2 and R; are the principal radii of curvature of the surface of the lower solid at the point of contact. The intersection of the planes in which the radii R , and R, (or the radii R; and R ; ) lie form an angle a.Elevation and plan views, respectively, of the two solids are shown in Figures 1 7 . 2 ~ and 17.2b.The lines v1 and v2, which form the angle a,lie in the plane sections containing the radii R , and R,, respectively. The line of action of load P lies along the axis that passes through the centers of curvature of the solids and through the point of contact. Hence, the line of action of force P is perpendicular to a plane that is tangent to both solids at the point of contact. In other words, it is assumed that there is no tendency for one body to slide with respect to the other and, hence, no friction force is present. The effect of a friction force is discussed in Section 17.9. The effect of the load P is to cause the surface of the solids to deform elastically over a region surrounding the initial point of contact, thereby bringing the two bodies into contact over a small area in the neighborhood of the initial point of contact (Figure 17.2b). The problem is to determine a relation between the load P and the maximum compressive stress on this small area of contact and to determine the principal stresses at any point in

IP

FIGURE 17.1 Two curved surfaces of different radii pressed against each other. ‘In 1881 Hertz published a paper entitled “On Contact of Elastic Solids,” and the following year he published “On the Contact of Rigid Elastic Solids and on Hardness.” See Hertz (1895).

17.3

GEOMETRY OF THE CONTACTSURFACE

591

FIGURE 17.2 Analysis of contact stresses.

either body on the line of action of the load, designated as the z axis. The principal stresses oxx, oyr,.and o,,acting on a small cube at a point on the z axis are shown in Figure 1 7 . 2 ~ . The maximum shear stress at the point is , ,z = 51 (o,, - oyy), where o,,and oyyare the maximum and minimum principal stresses at the point. The detailed development of the solution of the problem will not be presented here. However, the main assumptions made in the solution are given so that the limitationson the use of the results may be understood. A brief discussionis given to explain and justify the assumptions.

17.3 GEOMETRY OF THE CONTACT SURFACE 17.3.1

Fundamental Assumptions

The solution of the problem of the contact stresses in the neighborhood of the point of contact of two bodies is based on the following two assumptions.

(a)Properties of Materials The material of each body is homogeneous, isotropic, and elastic in accordance with Hooke’s law, but the two bodies are not necessarily made of the same material.

592

CHAPTER 17 CONTACT STRESSES

(b) Shape of Surfaces near Point of Contact Before Loading If two bodies are in contact at a point, there is a common tangent plane to the surfaces at the point of contact. In the solution for contact stresses, an expression for the distance between corresponding points on the surfaces near the point of contact is required; corresponding points are points that lie on the surfaces of the bodies and on a line perpendicular to the common tangent plane. Equations that express the two distances zl, z2 from corresponding points to the common tangent plane are needed to determine the deformations of the two bodies near the initial point of contact. In the analysis, an equation that approximates the total distance d = z1 + z2 between corresponding points on any two surfaces is used. This equation is 2

d = A x +By

2

(17.1)

in which x and y are coordinates relative to the y and x axes with origin at the point of contact (these coordinates lie in the tangent plane) and A and B are (positive) constants (Hertz, 1895) that depend on the principal radii of curvature of the surfaces at the point of contact. The derivation of Eq. 17.1 is discussed later in this section. Figures 17.2d and 17.2e illustrate the fact that the curve representing Eq. 17.1 for a given value of d is an ellipse. This will be important in considering the shape of the area of contact between the two bodies.

17.3.2

When the loads P are applied to the bodies, their surfaces deform elastically near the point of contact so that a small area of contact is formed. It is assumed that, as this small area of contact forms, points that come into contact are points on the two surfaces that originally were equal distances from the tangent plane. According to Eq. 17.1, such equidistant points on the two surfaces lie on an ellipse. Hence the boundary line of the area of contact is assumed to be an ellipse whose equation is 2

2

x_+L =

1

(17.2)

a* b2 where x and y are coordinates referred to the same axes as were specified for Eq. 17.1. The contact area described by Eq. 17.2 is shown in Figure 17.2b. Equation 17.1 is of sufficient importance to warrant further discussion of its validity, particularly since a method of determining the constants A and B is required in the solution of the problem of finding contact stresses.

17.3.3

Justification of Eq. 17.1

To obtain Eq. 17.1, an expression is derived first for the perpendicular distance z1 from the tangent plane to any point on the surface of body 1 near the point of contact, by assuming that the bodies are free from loads and in contact at a point. A portion of body 1 showing the distance z1 is illustrated in Figure 17.3a. Let the points considered lie in the planes of principal radii of curvature. Let u1 and v1 be axes in the tangent plane that lie in the planes of principal radii of curvature of body 1. The distance z1 to point C or D is found as follows. From triangle ODD' 1 1 z* = ultan-p = -ulp

2

2

(17.3)

GEOMETRY OF THE CONTACT SURFACE

17.3

593

X

Z

H

d=

Tangent plane

D'

u1

d=

FIGURE 17.3

Geometry of contact surface.

since the angle p is small. From triangle HKD (17.4) since the radius R; is approximately equal to HK. Substitution of the value of p from Eq. 17.4 into Eq. 17.3 gives (17.5) In a similar manner, the distance z1 to the points E and F lying in the plane of radius Rl is found to be (17.6) On the basis of these results, it is assumed that the distance z1 to any point G not lying in either plane of principal curvature may be approximated by

594

CHAPTER 17 CONTACT STRESSES

z1 =

2 u1

2 v1

-+2R;

(17.7)

2R1

This assumption seems justified by the fact that Eq. 17.7 reduces to Eq. 17.6 for u1 = 0 and to Eq. 17.5 for v1 = 0. In particular, we note that if z1 is constant for all points G , Eq. 17.7 is an equation for an ellipse. Attention is directed now to the second body. The distance z2 from the tangent plane to any point in the surface of body 2 near the point of contact is obtained in the same way as z1 in Eq. 17.7. It is 0

0

L

z2 =

L

-+u2

v2

2R:

2R,

L

(17.8)

L

where u2 and v2 are coordinates with respect to axes lying in the tangent plane and also in the planes of the principal radii of curvature R; and R2, respectively. The locations of the axes u l , v1 and u2, v2 are shown in Figure 17.3b, which is the same view of the bodies as in Figure 17.2b. The axes v1 and v2 subtend the angle a,that is, the angle between the lines v1 and v2 of the bodies as shown in Figure 17.2b. The distance d between points on the two surfaces near the point of contact is the numerical sum of z1 and z2 given by Eqs. 17.7 and 17.8. Hence, we find 2

2

2 u2

d = z 1 + z 2 = -+-+7+u1 v1

2R;

2 “2

2R1 2R2

2R2

(17.9)

Equation 17.9 may now be transformed into the form of Eq. 17.1. The first transformation is the elimination of the coordinates u2 and v2 by the relationships

u2 = u l c o s a + v l s i n a (17.10)

v2 = - u l s i n a + v l c o s a When Eqs. 17.10 are substituted into Eq. 17.9, there results 2

d = A’ul

+ 2H’ulv1 + B’vl2

(17.11)

where 2A’ =

1 1 + -cos

R;

R;

2

1 2 a+ -sin a R2

2H’ = ( k - - ~ ) . i n a c o sa 2B‘ =

1 1 . 2 1 + --ysltl a+ -cos Rl

R2

(17.12) 2

a

R2

Equation 17.11 is the equation of an ellipse, as shown in Figure 17.3b, with center at point 0. To find the equation of the ellipse referred to axes x and y, which coincide with the major and minor axes of the ellipse, the value of the angle A through which the axes u1 and v1 must be rotated to eliminate the product term ulvl in Eq. 17.11 is required. The transformation is

GEOMETRY OF THE CONTACT SURFACE

17.3

595

u , = xcosil-ysinil

= xsinil+ycosil

(17.13)

If Eqs. 17.13 are substituted into Eq. 17.11 and the value of the angle iltaken to eliminate the product term u1vlrEq. 17.11 becomes 2

d = Ax + B y

2

(17.14)

which is identical in form to Eq. 17.1. In the process of making the transformation, it is found that A and B are the roots of a quadratic equation and have the following values:

-+-+-+-

R2 R ;

R;

(17.16)

The constants A and B depend on the principal radii of curvature of the two bodies at the point of contact and on the angle a between the corresponding planes of the principal curvatures.

Note: With the definition for radii of curvature in Figure 17.2, it is possible for the ratio B/A to be greater than or less than 1. If a = 0 and B/A > 1, the major axis of the ellipse of contact is along the x axis and is said to be in the direction of rolling. If a = 0 and B/A < 1, the minor axis of the ellipse of contact is along the x axis (in the direction of rolling). In this latter case, it is convenient to let R , and R2 be radii of curvature in the plane of rolling (the x-z plane; Figure 17.2e) so that B/A > 1.

17.3.4 Brief Discussion of the Solution It was pointed out earlier in this section that Eq. 17.1 is used to estimate the displacement of points on the surfaces of the two bodies that eventually lie within the contact area. In Figure 1 7 . 3 the ~ solid outline shows the two bodies of Figure 17.1 in contact at one point, before the loads are applied, and the dashed lines show the new positions of the two bodies after the loads P are applied and the two bodies are in contact over an area around the original point of contact 0. The centers of the bodies move toward each other by amounts of 6, and 6, respectively, which means that the distance between points on the bodies not affected by the local deformation near 0 is decreased by an amount 6, + 62= 6. Let w1 denote the displacement, caused by local compression, of point Q , (Figure 17.3~).We take w1 positive in the direction away from the tangent plane, assumed to remain immovable during local compression. Similarly, let w 2 denote the displacement,

596

CHAPTER 17 CONTACT STRESSES

caused by local compression, of point Q,, where w2 is taken positive in the direction away from the tangent plane. These positive directions of w1 and w2 conform to the positive directions of displacement in a small loaded region on a part of the boundary of a semiinfinite solid; that is, the positive displacement is directed into the solid. Hence, the distance between two points, such as Q , and Q2 in Figure 17.3, will diminish by 6 - (wl + w2). If, finally, due to the local compression, points Q , and Q2 come in contact, we have

With the expression ford, given by Eq. 17.14, we may write 2

w1+w2 = 6 - A X - B y

2

(17.17)

Equation 17.17 has been obtained from geometrical considerations only. To compute the displacements (w,, w2), local deformation at the surface of contact must be considered. Under the assumption that the surface of contact is very small compared to the radii of curvatures of the bodies, the solution obtained for semiinfinite bodies subjected to spot loads may be employed to determine w1 + w2 (Thomas and Hoersch, 1930; Timoshenko and Goodier, 1970). Hertz noted that Eq. 17.17 has the same form as that of the Newtonian potential equation for the attraction of a homogeneous mass M in the shape of an ellipsoid on a unit of mass concentrated at a point P some distance from the ellipsoid. This Newtonian potential function satisfies the same differential equationsthat are required to be satisfied by the theory of elasticity.The problem is solved by placing into the potential equation the stresses at the contact surface instead of the mass, etc., and the constants are evaluated (Thomas and Hoersch, 1930). The solution is given in terms of elliptic integrals. The results are summarized in the following sections.

17.4 NOTATION AND MEANING OF TERMS The following notation and interpretations of terms are needed for an understanding of subsequent equations: P = total force exerted by body 1 on body 2 and vice versa. E l , E2 = tensile (or compressive) moduli of elasticity for bodies 1 and 2. vl, v2 = Poisson's ratio for bodies 1 and 2. a = semimajor axis of ellipse of contact. b = semiminor axis of ellipse of contact.

k = bla = cos 8; k I 1. 2

k'= J ( l - k ) = sine. R , , R ; = principal values of the radii, respectively, of the surface of body 1 at the point of contact. The plane sections in which R , , R [ lie are perpendicular to each other. (See Figure 17.1.) The signs of R l and R ; are determined as follows: If the center of curvature lies inside the body (i.e., if the body surface is convex at the point of contact), the radius is positive. If the center of curvature lies outside the body (i.e., if the body surface is concave at the point of contact), the radius is negative. For example, in Figure 17.1, the radii R , , R ; are positive. R,, R; = same as R , , R ; , but for body 2; in Figure 17.12c, R2 is negative.

17.5

EXPRESSIONS FOR PRINCIPAL STRESSES

597

a = angle between planes of principal curvatures at point of contact (see Figure 17.2b). k(z/b) = relative depth below the surface of contact to a point on the z axis at which stresses are to be calculated. The depth is expressed in terms of k(z/b) rather than by z directly so that, in evaluating the integrals obtained in the mathematical solution of the problem, the term k( zlb) can conveniently be replaced by a trigonometric function, for instance, cot Cp = k( zlb). z, = distance from surface to point on z axis at which maximum shear stress occurs in either body. In the expressions for the principal stresses, two integrals (called elliptic integmls) are found that involve Cp, 8,and k‘. These integralsare denoted as F(Cp, k’) and H(@,k’ ). Likewise, two integrals involving k’ alone, denoted as K(k’) andE(k’), are required. These elliptic integrals are F(Cpl k’) =

[email protected] 0

H ( @ ,k’) = i

do

1-k J

sin8 m

d

8

0

K(k’) = F ( 5 , k‘)

I d~

nl2 0

d8 2 . 2

l-k‘sm

8

0

These integrals have been tabulated and are readily available in most mathematical handbooks.

17.5

EXPRESSIONS FOR PRINCIPAL STRESSES The analysis involving the assumptions and limitations indicated in Section 17.3 yields the following expressions for the principal stresses ox,,oyu, and ozzat a point on the z axis. The point is at the distance z from the origin, which lies on the surface of contact of the two elastic bodies. The stresses act on orthogonal planes perpendicular to the x, y, and z axes, respectively. The solution of this problem is (Thomas and Hoersch, 1930) b oxxx = [M(Q,+ vQ:)lA

(17.18)

oYv= [M(Qy+ v Q ’ ) ] -b

(17.19)

ozz= in which

-[(.)I:

Y A

M 1 2 n

(17.20)

598

CHAPTER 17 CONTACT STRESSES

whereA and B are constants given by Eqs. 17.15 and 17.16, and where

52, = - !Z! 2

+ k z [ F ( @ ,k') - - H ( @ ,k')] b

52; = - - +n l + k z [ ( + ) H ( & k ' ) - F ( @ , k ' ) ] k2

b k

i2 = - l+ - - l- + knY

2n

2 k2

-H(#,k')-F(@,k') ilk;

52; = - l + n + k Z [ F ( @ , k ' ) - H ( @ , k ' ) l b Also, v = v1 for a point in body 1 and v = v2 for a point in body 2. We note that the stresses depend on the variables A, B, k, k', vl, v2,E l , E2, b, and z. The first four variables depend only on the shape of the surfaces near the point of contact. Of these four, A and B 2

are found from Eqs. 17.15 and 17.16, and from Section 17.4, k' = J 1 - k . Therefore, one additional equation is needed for determining the value of k. This equation is

B - -A

K ( k ' ) - E(k')

(17.21)

The second group of four variables, v1, v2,E l , and E,, depend only on the properties of the two bodies in contact and are found by tests of the materials. The variable b, the semiminor axis of the area of contact, depends on the eight variables previously listed, but it is important to note that it also depends on the load P. The equation expressing this fact is

(17.22) Values of the variable z, which represent the distance of a point Ji-om the surface of contact, may be chosen. Then the three principal stresses at any point on the z axis may be obtained.

17.6 METHOD OF COMPUTING CONTACT STRESSES 17.6.1

Principal Stresses

In Section 17.5 it is noted that the values of A and B must be computed first and that in Eq. 17.21 the ratio B/A determines the value of k (and k'). It should be remembered that the values of A and B are related to the geometric shape and configuration of the two bodies. For example, if two cylinders are crossed so that they are in point contact with their longi-

17.6

METHOD OF COMPUTING CONTACT STRESSES

599

tudinal axes perpendicular, the value of B/A = 1, but if these cylinders are arranged so that their longitudinal axes are parallel (line contact), BIA = 00. With the values of the four quantities A , B , k, and k’ known, the terms in the brackets in Eqs. 17.18-17.20 can be evaluated for a selected value of Poisson’s ratio v. Fortunately, the value of v in these bracket terms has only a small influence on the final values of the stresses. Consequently, we take a value of v = 0.25 to compute these terms. The actual values of v1 and v 2 of the two bodies are used later in computing A. Thus, since the terms within the brackets do not depend strongly on the elastic constants of the two bodies or the load P, their magnitudes can be computed and tabulated for use as coefficients in the determination of the ratio b/A. For example, let a value of the ratio B/A = 1.24 be chosen. From Eq. 17.21, k = 0.866 and hence k’ = 0.5. For specified values of the ratio kz/b, required coefficients can be found for determination of the stresses at a distance z from the area of contact. The results of these computations are given in Figure 17.4, in which the coefficients of b/A are plotted as abscissas and the values of kzlb to the point at which the stresses occur are plotted as ordinates. The curves representing oxx, oyy, and o,,show that their largest magnitudes occur when z = 0 (at the center of the surface of contact) and that all three stresses decrease as z increases. The principal stress having the greatest magnitude is o,,and, hence, at each In this example, in which B/A = 1.24, the value of om,= 0.67bJA. The point, om,,= oZz. coefficient 0.67 of b/A is found at z = 0 from the curve for o,,.

17.6.2

Maximum Shear Stress

The maximum shear stress at any point is , ,z = 51 (omax - omin). In Figure 17.4 the curves show that the magnitudes of ox,and oyydecrease more rapidly than that of o,,at points just beneath the surface of contact. Because of this, the maximum shear stress at points just beneath the surface of contact increases in magnitude and reaches its maximum value 21 (o,,, - oyus) at z,, as shown by the curve marked Z.In this example in which B/A = 1.24, the value of zmax= 0.22b/A, and the depth kz,/b = 0.44; that is, z, = 0.44bJ0.866 = 0.5 1b. The coefficient 0.22 of b/A is the ordinate to the z curve at the depth z,.

17.6.3

Maximum Octahedral Shear Stress

The octahedral shear stress zoct(see Eq. 2.22) is

The values of zocthave been computed by this equation for several points along the z axis and are plotted as ordinates to the curved marked zoCpIn this example, for B/A = 1.24, the maximum value of the octahedral shear stress is z ~ ~= 0.21b/A, ~ ( ~and~it occurs ) at the same z, = 0.51b as the maximum shear stress. The coefficient 0.21 of b/A is the ordinate to the roctcurve at z,.

17.6.4

Maximum Orthogonal Shear Stress

As previously noted, the maximum shear stress and maximum octahedral shear stress occur in the interior of the contacting bodies at points located equidistant from the tangent plane on a line perpendicular to the center of the contacting area. These maximum values are considered to be the significant stresses in certain failure criteria associated with initiation of yielding (Chapter 4). Other shear stress components that are considered to be

600

CHAPTER 17 CONTACT STRESSES

Values of principal stresses and shear stress

4-

m

c 0

E

e

Y-

In V

m *

.-

0

B k = 0.866;- = 1.24

A

Compressive stresses are negative

FIGURE 17.4 Curves showing variation in principal stresses, maximum shear stress, and octahedral shear stress with variation in distance from the contact surface; v = 0.25.

significant in the fatigue failure of bearings and other rolling elements (e.g., cylinders) in contact are shear stresses that occur on planes perpendicular and parallel to the plane tangent to the contact area. For example, with reference to Figures 17.2b and 17.2d, orthogonal shear stress components ox,and oyzact on a plane perpendicular to the z axis; they are called orthogonal shear stresses since they act also on planes x-y and y-z, which are perpendicular (orthogonal)to the plane of contact. These shear stress components are zero on the z axis, where, , ,z occurs. We choose the x axis in the direction of rolling and consider only those problems for which the x axis coincides with either the major or minor axes of the contacting ellipse. The maximum orthogonal shear stress zo is defined as oxz(max), which occurs at points in the interior of the contacting bodies located in the x-z plane equidistant from the z axis at some distance from the contacting surface.

17.6

METHOD OF COMPUTING CONTACT STRESSES

601

Although rois always smaller than Zmm, 2, for a given point in a contacting body changes sign as the rolling element (the contact area) approaches and leaves the region above the point. Therefore, the range of the maximum orthogonal shear stress is 22,, and for most applications this range is greater than the range of the maximum shear stress rmm.Note that byz(max) may be greater than r0; however, oyz("t. does not change sign which is less than 22,. The during rolling so that the range of oyzis equal to oyyr(max). range in orthogonal shear stress is considered to be important (Moyar and Morrow, 1964) in studies of fatigue failure resulting from rolling contact. The location of the point (perpendiculardistance to the point from the tangent plane at the contact area) at which Z , occurs, as well as the magnitude of z , is a function of the ellipticity (values of a, b) and orientation of the contact ellipse with respect to the rolling direction (Moyar and Morrow, 1964). In particular, for toroids under radial loads (Figure 17.5) Fessler and Ollerton (1957) have derived expressions for the orthogonal shear stress components o,,,oyz(Figure 17.6). Their results are, with the notations of Sections 17.4 and 17.5, 2 na

( 17.23)

where

(17.24)

FIGURE 17.5

Toroids in contact.

602

CHAPTER 17 CONTACT STRESSES

J

FIGURE 17.6 State of stress of an element. Compressive stresses are negative.

and

11

-

(17.25)

a +c

b +c

where c2 is the positive root of the equation X

2

+-+-Y 2

Z

2

a 2 + c 2 b2+c2 c

2

= 1

(17.26)

The maximum values of ox,and oyzoccur in the planes of symmetry, y = 0 and x = 0, respectively. For the plane of symmetry y = 0, we get

(17.27) oyz= 0

and for the plane of symmetry x = 0, we have

(17.28)

In particular, we note that along the z axis (x = y = 0), ox,= oyz= 0.

17.6

METHOD OF COMPUTING CONTACT STRESSES

603

As noted earlier, in rolling contact problems, the perpendicular distance from the tangent plane at the contact area to the point at which the maximum range of zo occurs (as the roller passes over a given region) and the magnitude of zo depend on the ellipticity and orientation of the contact ellipse with respect to the rolling direction. Consequently, the geometric configuration of the contacting rollers is an important factor. For example, for contacting toroids (Figure 17.5), the distance ,z, from the contact surface, at which the maximum orthogonal shear stress zo = D ~ ~occurs ( ~ is plotted ~ ) in Figure 17.7; note that the contact ellipse semiaxis in the rolling direction is equal to b for e < 1 and a for e > 1. The magnitude of zo is plotted in Figure 17.8 (Fessler and Ollerton, 1957). The range of the maximum orthogonal shear stress 27, is considered to be important in rolling fatigue problems as long as 22, is greater than the range of the maximum shear stress . , ,z Fessler and Ollerton (1957) found that 2z0 > , ,z for e < 2.25 when v = 0.25 for e < 2.85 when v = 0.50 for both bodies. Poisson's for both bodies and that 2z0 >, z

e=

Contact ellipse axis in rolling direction Contact ellipse axis perpendicular to rolling direction

FIGURE 17.7 Distance z, at which the maximum orthogonal shear stress occurs.

e=

Contact ellipse axis in rolling direction Contact ellipse axis perpendicular to rolling direction

FIGURE 17.8 Magnitude of maximum orthogonal shear stress.

604

CHAPTER 17 CONTACT STRESSES

ratio for most isotropic materials falls between these two values. Furthermore, the contour surfaces for most rolling contact problems result in values of e that are less than 2.25. Fatigue failure of members under rolling contact depends on the magnitude of 22, for e c 2.25; however, the magnitude of the range of the orthogonal shear stress 22, for fatigue failure for a specified number of cycles is not equal to the range of maximum shear stress (for the same number of cycles of loading) in specimens (tension-compression or reversed torsion) that are generally used to obtain fatigue properties (Moyar and Morrow, 1964). The high hydrostatic state of compressive stress in contact problems strengthens the material against fatigue failure. The usual procedure is to obtain the magnitude of 2, at which fatigue failure initiates for a specified number of cycles for one orientation of the contact ellipse and one value of e and assume that fatigue failure for another rolling contact stress problem having a different value of e will occur for the same number of cycles when z, has the same magnitude. Since om, is generally calculated for all contact stress problems, it is not necessary that zo be calculated if the ratio 220/om,, is plotted versus e (Figure 17.9). The curve in Figure 17.9 has been plotted for v = 0.25. Since om, depends on v, whereas Z, does not, the curve in Figure 17.9 is moved slightly for other values of v. The ratios 2z0/2,, or 2 ~ ~ / 2versus ~ ~e could ~ ( also ~ be ~ plotted; ) however, only one plot is needed and om,,is more often calculated than,,z or z ~ ~ ~ ( ~ ~ ) . To illustrate the use of Figure 17.9 in the analysis of rolling contact stress fatigue problems, let fatigue properties for rolling contact stress be determined using two cylinders that roll together. Since the major axis of the contact ellipse is large compared to the minor axis b, e is assumed to be equal to zero. Let om,, be the maximum principal stress in the cylinders when fatigue failure of the contact surface occurs after N cycles of load. From Figure 17.9 we read 22, = o.50om,,. Let the toroids in Figure 17.5 be made of the same material as the cylinders. Let the radii of curvature be such that e = 1.3; for this value of e we read 22, = 0.400m,2 from Figure 17.9. The magnitude of om,, such that fatigue failure of the toroids occurs after the same number of cycles N as the two cylinders is = 1.250,,,. This obtained by setting the two values of 22, equal. Thus, we obtain omm2 result is based on the assumption that the fatigue strength of the material is the same for both types of loading. Moyar and Morrow (1964) indicate that the fatigue strength is not the same because of the size effect. Because of the larger volume of material under stress for the cylinders than the toroids, the fatigue strength for the toroids should be larger than

e=

Contact ellipse axis in rolling direction Contact ellipse axis perpendicular to rolling direction

FIGURE 17.9 Ratio of range of maximum orthogonal shear stress to omax (v = 0.25).

17.6

METHOD OF COMPUTING CONTACT STRESSES

605

for the cylinders. Thus, the magnitude of 2r0 for the toroids should be larger than for the , , a = cylinders to produce fatigue failure in the same number of cycles. Our result that, 1 . 2 5 0 , ~ ~is therefore conservative. If fatigue properties for materials are obtained fore = 0, the use of Figure 17.9 without correction for the size effect predicts conservative results.

17.6.5 Curves for Computing Stresses for Any Value of W A The preceding example in which B/A = 1.24 (k = 0.866) shows that for any value of B/A (or k), a set of curves may be drawn representing the values of the principal stresses on,oyy, and a , along the z axis at small distances z from the surface of contact. These curves may be used to find the magnitude and location of the maximum shear stress and maximum octahedral shear stress. Curves may also be constructed for a wide range of values of the ratio B/A. For each value of B/A, the maximum values of stresses may be found from the equations

(17.29)

where the values of the coefficients cg, c7, and cG may -5 read from the curves shown in Figure 17.10. In the example in which B/A = 1.24, the values of the coefficients were given

Values of BIA

FIGURE 17.10 Stress and deflection coefficients for two bodies in contact at a point.

606

CHAPTER 17 CONTACT STRESSES

as cg = 0.67, c7 = 0.22, and cG = 0.21. In Figures 17.10 and 17.11, values of these coefficients for use in Eq. 17.29 are given as ordinates to the curves marked cg, cz, and cG for a range of values B/A from 1 to 10,000. The values of k that are required in computing the semimajor axis a and semiminor axis b of the area of contact are given as ordinates to the curved marked k. The value of b that may be computed by using Eq. 17.22 is found as follows: Equation 17.22 is rewritten as b = cb3KA

(17.30)

in which cb = v3kE(k')/2a. The values of k (and k') as found from the curve marked k are used to compute the value of the coefficient cb. These values of cb are given as ordinates to the curve marked cb. The length of the semimajor axis is a = b/k. The distance z, from the surface of contact to the location on the z axis of the point at which the maximum stresses , ,z and zoct(m,)occur is (17.31)

zs=c b *S

The coefficient cZsis plotted in Figures 17.10 and 17.11. The examples following Section 17.7 illustrate the use of Figures 17.10 and 17.11.

5 JZ U

m E

I I 0.001 200

I I11111 400 600 1000

I

I I

I I

3~ ' 1 0 ~

I l l 10 x 103

FIGURE 17.11 Stress and deflection coefficients for two bodies in contact at a point.

17.7

17.7

DEFLECTION OF BODIES IN POINT CONTACT

607

DEFLECTION OF BODIES IN POINT CONTACT An expression for the distance 6 = 6, + S2through which two bodies in contact at a point

move toward each other when acted on by a load P (Figure 17.3~)is given by Eq. 17.17. The deflection 6 is sometimes called the approach because it expresses the sum of the “deflections” of the two bodies as they approach each other. The expression for the value of 6 is given by the following equation due to Hertz (1895):

6 = 3kPK(k’) A + B

(17.32)

where P is the load, K(k’) is the complete elliptic integral described in Section 17.4, and A , B, k, A, and b are defined in Sections 17.4 and 17.5. For convenient use of Eq. 17.32, the substitution of C6 =

3kK(k’) 2

(17.33)

is made to obtain

(17.34)

In Eq. 17.33, the value cgdepends only on k (and k’), and since from Eq. 17.21 there is a value of BIA corresponding to each value of k, there is a value of c6 corresponding to each value of BIA. In Figures 17.10 and 17.11 values of this coefficient have been computed by Eq. 17.33 and plotted as ordinates for the curve marked c6. Equation 17.34 gives approximate results since the elastic strains in the two bodies away from the contact region are neglected.

EXAMPLE 17.1 Contact Stresses Between Two Semicircular Disks

Let the two semicircular disks in Figure 17.1 be made of steel (El = E2 = 200 GPa and v, = v2 = 0.29). The radii of curvature of the two surfaces at the point of contact are R , = 60 mm, R; = 130 mm, R2 = 80 mm, and R; = 200 mm. The angle a between the planes of minimum curvature is a/3rad. If the load P = 4.50 kN, determine the maximum principal stress, maximum shear stress, and maximum octahedral shear stress in the disks and state the location of the point where each of these stresses occur. Determine the approach 6 for the two disks because of load P.

Solution

All stress and displacement calculations require first that values be obtained for& A, and A; these are given by Eqs. 17.15,17.16,and 17.20a.

= 0.01255 mm-’

608

CHAPTER 17 CONTACT STRESSES

- 4 ( L - L)(L- L ) s i 2

60

130 80 200

41”’

= 0.00838 mm-’ 2

A = -2(1-v 1 ( A+ B ) E = 438 x

A

i

2 1 - (0.29)’]

-

(0.01255 + O.O0838)(200 x lo3) mm3/N

= 1.50

The coefficientsneeded to calculate b, omax, ,,,,z z , ~ z,~ and ( ~the ~deflection ~ ~ are read from Figure 17.10 for the ratio B/A = 1.50. Hence, by Figure 17.10 we obtain the following coefficients: cb = 0.77, c g = 0.72, cT = 0.24, cG = 0.22, cZs= 0.53, and c6 = 2.10. For known values of cb, P, and A , Eq. 17.30 gives 3

= 0.965 mm

b = c b F A = 0.77 d(4.5 x 103)(438x

from which

-b -- 0.965 A 438x

= 2203 MPa

,,,z zOctlmax), z,, and 6 are obtained by substituting known values of the coefficients Values of om,,,, into Eqs. 17.29, 17.31, and 17.34:

omax = -c0 b = -0.72(2203) = -1586 MPa

zmaX= c b = 0.24(2203) = 529 MPa

‘oct(max)

=A = cG b = 0.22(2203) = 485 MPa A

z S = c b = 0.53(0.965) = 0.51 mm ZS

x lo3) 0.01255 + 0.00838

(

2203

= 0.029 mm ~

The maximum stress om,,= -1586 MPa occurs at the contact surface under the load. The maximum shear stress and maximum octahedral shear stress occur at z, = 0.51 mm from the surface of contact.

17.7

EXAMPLE 17.2 Contact Stresses in a Steel Bali Bearing

DEFLECTION OF BODIES IN POINT CONTACT

609

A steel ball bearing consisting of an inner race, an outer race, and 12 balls is shown in Figure E17.2 (E = 200 GPa, v = 0.29, and Y = 1600 MPa). A rated load of Po = 4.2 kN is given in a manufacturer's handbook for this bearing when operated at 3000 rpm. An empirical relation (Allen, 1945) is used to determine the load P on the topmost ball that bears the largest portion of the load; P = 5 P d n = 1.75 kN in which n is the number of balls. (a) At the region of contact between the inner race and topmost ball, determine the maximum principal stress, maximum shear stress, maximum octahedral shear stress, dimensions of the area of contact, maxi-

mum orthogonal shear stress, and distance from the point of contact to the point where these stresses occur. (b) What is the factor of safety against initiation of yielding based on the octahedral shear-stresscriterion of failure?

(0)

FIGURE E17.2

Solution

Contact load in ball bearing.

(a) Let the ball be designated as body 1 and the inner race as body 2, so R, = R ; = 4.76 mm, R, = -4.86 mm, and R; = 18.24 mm. We substitute these values in Eqs. 17.15 and 17.16 to obtain values for A and B . The following results are obtained:

B = 0.13245 mm-', A = - - -2 A

+

= 68.0 x

1-v

2

A = 0.00216 mm-',

A

= 61.3

2( 1 - 0.29,)

-

(0.13246 + 0.00216)(200 x lo3) m3/N

By Figure 17.10, with BIA = 61.3, we obtain the following values for the coefficients: cb = 0.32, k = 0.075, c, = 1.00, c g= 0.30, cG = 0.27, and cZs= 0.78. Hence,

6l o

CHAPTER 17 CONTACT STRESSES 3

b = c b w A = 0.32J1.75 a = -b= - 0.1574 - 2.099 k 0.075

-A

0'1574 68.0~

-c"x

Om,

=

zm,

= c

X

103(68.0x

= 0.1574 mm

= 2315 MPa

=

-1.00(2315) = -2315 h4Pa

b - = 0.30(2315) = 695 h4Pa ZA

b z ~ ~ ~ ~=~cG , )= 0.27(2315) = 625 MPa A The maximum principal stress occurs under the load at the contact tangent plane. The maximum shear stress and maximum octahedral shear stress are located at a distance z s = c, b = 0.78(0.1574) = 0.123 mm S

from the contact tangent plane directly under the load. The magnitude of the maximum orthogonal shear stress is obtained from Figure 17.8. Since b is in the direction of rolling, e = b/u = k = 0.075. From Figure 17.8, we obtain T o = - -0.486b -

"

0.486(0.1574) = 556MPa 2(68.0 x

The location of the maximum orthogonal shear stress from the contact tangent plane, obtained from Figure 17.7, is z0 = 0.41b = 0.41(0.1574) = 0.065 mm

(b) Since contact stresses are not linearly related to load P, the safety factor is not equal to the ratio of the maximum octahedral shear stress in the specimen used to obtain material properties and the maximum octahedral shear stress in the ball bearing. The magnitude of the yield load P y for a single ball may be obtained from the relation

(T,,.~)~ =

A -Y 3

h

= -1600 3

b - c c 3 K A = cG A G b T

1-1

= 0.27(0.32)

68.0 x from which

P , = 3076N The safety factor SF is equal to the ratio of P , to P:

SF =

5 = 3076 = 1.76 P 1750

17.8

17.7.1

STRESS FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL TO CONTACT AREA

6 11

Significance of Stresses

In the preceding examples, the magnitude of the maximum principal stress is quite large in comparison with the value of this stress usually found in direct tension, bending, and torsion. In these problems, as in all contact stress problems, the three principal stresses at the point of maximum values are all compressive stresses. As a result, the maximum shear stress and maximum octahedral shear stress are always less than one-half the maximum principal stress; we recall that, for a state of uniaxial stress (one principal stress), the maximum shear stress is one-half the principal stress. In fact, by a comparison of the values of c,, c,, and cG for various values of BIA in Figures 17.10 and 17.11, we see that when BIA = 1, c, = 0 . 3 2 and ~ ~ CG = 0.30~,, and when BIA = 100 or larger, C , = 0 . 3 0 and ~ ~CG = 0 . 2 7 ~ ~ Thus, ,,T and T ~ ~are ~always ( ~slightly ~ )smaller than one-third of the maximum principal stress om,.This fact is of special importance if the maximum shear stress or the octahedral shear stress is considered to be the cause of structural damage (failure) of the member; if the shear stresses are relatively small in comparison to the maximum principal stress, very high principal stresses can occur. However, the maximum utilizable values of the maximum shear stress or maximum octahedral shear stress are not easily determined, because in many problems involving two bodies under pressure at a small area of contact, such as occurs in rolling bearings, there are additional factors that affect the behavior of the material, for example, sliding friction, the effect of a lubricant, the effect of repeated loads, the effect of variation in the metal properties near the surface of contact such as that caused by case hardening, and the effects of metallurgical changes that often occur in parts such as the races of ball bearings as the result of the repeated stressing.

17.8 STRESS FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL TO CONTACT AREA If two cylindrical surfaces are in contact, the contact region is approximately along a straight-line element before loads are applied. Figure 1 7 . 1 2 ~illustrates contact between two circular cylinders, the line of contact being perpendicular to the paper. Figure 17.12b also shows a line contact of a circular cylinder resting on a plane. Figure 17.12~shows a line contact of a small circular cylinder resting inside a larger hollow cylinder. In these cases, the radii R; and R ; , which lie in a plane perpendicular to the paper, are each

(a)

FIGURE 17.12

(b)

Line contact between cylindrical bodies.

(4

6 12

CHAPTER 17 CONTACT STRESSES

infinitely large so that 1/R; and 1/R; each vanish identically and the angle a = 0 (Figure 17.3b). Therefore, from Eqs. 17.15 and 17.16 the expressions for B andA are

where R , and R2 are the radii of curvature of the cylindrical surfaces (Figure 17.12). Note that R2 is negative in Figure 17.12~.Hence, the value of the ratio B/A is infinitely large, and from Eq. 17.21 the corresponding value of k approaches zero. However, k is the ratio of the semiminor axis b of the area of contact to semimajor axis a (Eq. 17.22) and, therefore, a must be infinitely large, which is the case of contact along a line between two bodies. The area of contact, when a distributed load of w (force per unit length) is applied, is a long narrow rectangle of width 2b in the x direction and length 2a in the y direction. When k = 0, Eqs. 17.18-17.20 for the stresses at points on the z axis at various distances z/b from the contact surface do not involve elliptic functions. In this case,

(17.35)

b-

c

(17.36)

1 (17.37)

The value of b from Eq. 17.22 for the limiting case in which k = 0 is

(17.38) in which w is the load per unit length of the contact area. The value of A is (Eq. 17.20a)

(17.39)

where R , and R, are the radii of curvature of the cylindrical surfaces as shown in Figure 17.12. The values of the stresses at a point on the line of contact are obtained from Eqs. 17.35-17.37 by setting z = 0.

17.9

STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA

17.8.1

6 13

Maximum Principal Stresses: k = 0

It is seen from Eqs. 17.35-17.37 that the principal stresses o ,, oyy, and ozzhave their maximum numerical value when zlb = 0, that is, at the surface of contact. These stresses are b oxx= -A’

17.8.2

b A

OYY

(17.40)

Maximum Shear Stress: k = 0

The shear stress at any point on the z axis is z = 51 (oxx - o,,).If the expressions for ox, and a,, from Eqs. 17.36 and 17.37 are substituted in this equation for z and the first derivative of z with respect to z is equated to zero, the value of z (or zlb) found from the resulting equation is the distance from the contact surface at which the greatest value , ,z of the shear stress occurs. The value thus found is z,lb = 0.7861. At this point, the principal stresses are, from Eqs. 17.35-17.37, oxx= -0.1856(2),

ory= -0.9718- vb A (17.41)

ozz= -0.7861(2) Hence, 1 zmax= -(oxxoZz) = 0.300 2

(17.42)

At zJb = 0.7861, the magnitude of ox, is smaller than that of oyyfor values of v greater than about 0.19.

17.8.3 Maximum Octahedral Shear Stress: k = 0 The maximum octahedral shear stress occurs at the same point as the maximum shear oyy, and o,,from Eq. 17.41 into Eq. stress and is found by substituting the values of oxx, 2.22. The result is b (17.43) Zoct(rnax) = 0*27A We note that the coefficients for determining the quantities om,, zmax,zoct(,,), and z, as obtained from Figures 17.10 and 17.11 for values of B/A greater than about 50 are 1.00, 0.30,0.27, and 0.78, respectively, and these are the same coefficients found for the case of line contact between two bodies. This means that when the ratio BIA is about 50 or larger, the area of contact between the two bodies is very nearly a long narrow rectangle.

17.9 STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA In the preceding sections, the contact stresses in two elastic bodies held in contact by forces normal to the area of contact were found. Frequently, the normal force is accompanied by a tangential (frictional) force in the contact area such as occurs when the teeth

614

CHAPTER 17 CONTACT STRESSES

of spur gears come into contact or when a shaft rotates in a bearing. The frictional force that results from the sliding contact lies in the plane of the area of contact in a direction perpendicular to the normal force. The presence of frictional force causes the maximum values of the contact stresses in the two elastic bodies to become substantially larger than those produced by a normal force acting alone. Furthermore, the presence of a frictional force combined with a normal force causes certain changes in the nature of the stresses. For example, when a normal force acts alone, the three principal stresses are compressive stresses at every point in the body near the contact area, and this makes it difficult to understand how a crack can form and progressively spread to cause a separation type of failure such as occurs in pitting failures of some bearing surfaces. However, when a frictional force is introduced, two of the three principal stresses are changed into tensile stresses in the region immediately behind the frictional force (see Figures 17.14b and 17.14~).If the coefficient of friction for the two surfaces of contact is sufficiently large, these tensile stresses are relatively large. However, if these tensile stresses are nominally small, as they probably are on well-lubricated surfaces, their values may be raised by stress concentrations that result from surface irregularities or small microscopic cracks that usually exist in the surfaces of real materials. These tensile stresses, when considered in conjunction with the many other factors involved, such as wear, nonhomogeneity of the material, and type of lubrication, help in explaining why a crack may develop and progressively spread in the surface of contact of such parts as gear teeth or roller bearings. The addition of a frictional force to a normal force on the contact surface also causes a change in the shear stresses in the region of the contact surface. One important change is that the location of the point at which the maximum shear stress occurs moves toward the contact area. In fact, when the coefficient of friction is 0.10 or greater, this point is located in the contact surface. The foregoing remarks also apply to the maximum octahedral shear stress. The facts described here may be illustrated for an elastic cylindrical roller pressed against the plane surface of another elastic body.

17.9.1

Roller on Plane

Let Figure 1 7 . 1 3 represent ~ the cross section of a long roller of elastic material that rests on a flat surface of a thick, solid elastic body. The roller is subjected to a distributed load w (force per unit length), which presses it against the body over a long narrow area of contact whose width is 2b. A laterally distributed loadf(force per unit length) causes the roller to slide on the body. If the coefficient of sliding friction is designated as p, thenf= pW. In Figure 17.13b, a part of the solid body is shown with the distributed loads w and f acting on the contact area. In Figure 17.13c, which is an enlarged view of the part near the contact area, the ordinates to the ellipse show the distribution of normal stresses over this area and the maximum stress is o,,= -b/A (Eq. 17.40). Mindlin (1949) found that, when sliding occurs, the shear stress on the contact area owing to the frictional forcefis distributed as ordinates to an ellipse as shown in Figure 17.13d, and the maximum shear stress o,,at the center is o, = P(b/A).Figure 17.13e shows the distribution of the combined normal and friction stresses on the contact surface. Liu (Smith and Liu, 1953) derived the equations for the stresses o,,,oxx,oru, and o,, at any point in the body. These equations are

17.9

STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA

615

FIGURE 17.13 Tangential (shear) forces in addition to normal forces on the contact area.

2 nx (17.44)

"

+p

Oi'X

\$1 =

(X - b

"{

-Z

z242 + p[(b2+ 2 x 2 + 2 z 2 ) f 4 + - 2 x 5 - 3 x z q 2 b b

-- - nA

n(M +N ) 9

MNd2MN

+ 2x2 + 2z2 - 2b2

42 =

nM-N MNd2MN

+ 2x2 + 2z2 - 2b2

where M = and N = . The values of stress as given by Eqs. 17.44 do not depend on y because it is assumed that either a state of plane strain or plane stress exists relative to the (x,z ) plane. - /A

6 16

CHAPTER 17 CONTACT STRESSES

17.9.2 Principal Stresses In Eqs. 17.44 oyyis a principal stress, say 03, but o,,and oXxare not principal stresses because of the presence of the shear stress o,, that acts on these planes. Let the other two principal stresses at any point be designated by o1and o2 These two stresses may be found from stress theory (Section 2.4) with the values of o,,, oxxr and ozxfor the point. The principal stresses ol, 02, and o3for points on the surface2 and at a distance z = b/4 from the surface have been computed by this theory for a value of friction coefficient of 0.333, and their values have been plotted in Figures 17.14a-c. Each principal stress has its maximum value in the surface of the body at a distance of about 0.3b from the center of the area of contact in the direction of the frictional force. These maximum values, all of which occur at the same

r1

Friction coefficient = 0.333

-At

surface

---At

b z =4

(a)

I

I

-4

-3

-2

-1

+3

+2

+1

+4

c2

Friction coefficient = 0.333

-At

surface

----------.-

1-

b

t FIGURE 17.14 Effect of tangential force on principal stresses.

*A special method of evaluating Eq. 17.44 may be used when solving for the stresses on the surface where z = 0 (Smith and Liu, 1953).

17.9

STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA

617

point, are ol = - 1.4b/D, o2= -0.72b/D, and o3= -0.53b/D. These values may be compared with oI= -b/D, o2= - b/D, and o3= - 0.5b/D, as found from Eq. 17.40 for the normal distributed load w only. This comparison shows that the frictional force corresponding to a coefficient of friction of 0.333 increases the maximum principal stress by 40%. Furthermore, the curves in Figure 17.14 show that the principal stresses o2and o3are tension stresses near the edge of the contact area, opposite the direction of the frictional force. The largest magnitudes of these stresses are 0.667(b/D) and 0.167(b/D), respectively, but these values are sometimes quite large. The presence of the tensile stresses on the surfaces aids in understanding the occurrence of fatigue failure by pitting and other mechanisms of bearing surfaces subjected to repeated loads.

17.9.3

Maximum Shear Stress

From the values of maximum and minimum principal stresses at a point in the surface of contact, the maximum shear stress at the point on the surface is found to be ( 17.45)

To determine whether or not this value of the shear stress is the maximum value occurring in the body, it is necessary to compute the maximum shear stress at all other points, and especially at points inside the body under the contact area, since in all previous results presented in this chapter the maximum shear stress was found to be a subsurface shear stress. The values of shear stress at points on the surface and from the surface a distance of z = b/4 (where the maximum subsurface shear occurs) have been computed by making use of the principal stresses in Figure 17.14 and are represented as ordinates to the curves in Figures 17.15u-c. There are three extreme values of shear stresses at each point; they are

r1

1

= 2 4 0 1-

1 1 - 03) q, z2 = 2-(ol - o,), r3 = -(02 2

( 17.46)

From Figures 17.1% and 17.15c, we see that the ordinates to the curves representing z1 and z3at distance z = b/4 from the surface are everywhere smaller than at the surface. This is true of the curves for these values at all distances from the surface. However, in Figure 17.15b, the curve for z2 at z = b/4 rises above the curve representing values of r 2at the surface. Such curves for values of z2have been plotted for several different distances from the surface, and it is found that the largest value of z2is 0.36blD. This value occurs at a distance of about b/4 from the surface. Therefore, the value of z1 = -0.43b/D as given by Eq. 17.46 is the maximum shear stress, and it occurs at a point in the contact area about 0.3b from the center of the area. In Eq. 17.46 the maximum value of z2, which always occurs away from the surface, does not exceed z1 until the coefficient of friction has a value less than 0.10.

17.9.4 Maximum Octahedral Shear Stress In Figure 17.16 the ordinates to the curves represent the values of the octahedral shear stresses zoctthat have been computed at each point from Eq. 2.22 by substitution of values of the principal stresses obtained from Figure 17.14.The maximum value is zoct(max) = 0.37b/D, and this value occurs on the contact area at the same point that the maximum principal stress and maximum shear stresses occur (Figures 17.14 and 17.15).

618

CHAPTER 17 CONTACT STRESSES

-0.4

-0.3

-0.2

-0.1

+1

0

+2

-+ X

+3

+4

b

\,

72

-At

Friction coefficient = 0.333

\

surface

b

---At,=-

I +3

I

-4

-3

-2

-1

+1

0

0.3

-+ X

I +4

b

r

73

Friction coefficient = 0.333

-At

r,

t(

+2

---

surface b 4

Atz=-

L

/

-4

-3

-2

-+ FIGURE 17.15 Effect of tangential force on maximum shear stresses.

17.9.5

Effect of Magnitude of Friction Coefficient

The magnitude of the coefficient of friction determines the size of the distributed frictional loadffor a given value of w and, therefore, of the values of the maximum principal stresses, maximum shear stresses, and maximum octahedral shear stress. The changes in the maximum contact stresses with the coefficientof friction are given by Table 17.1. The increases in the maximum values of the tensile and compressive principal stresses caused by the frictional distributed load are very nearly proportional to the increases in the friction coefficient.

17.9

STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA

-At surface

Friction coefficient = 0.333

-0.4

-0.3

-0.2

6 19

-0.1

0

+1

-+ X

+3

+2

+4

b

FIGURE 17.16 Effect of tangential force on octahedral shear stress.

TABLE 17.1 Values of Contact Stresses Between Two Long Cylindrical Bodies Sliding Against Each Other While in Line Contact (Normal and Friction Forces)

Kind of stress and its location

Values of stress in terms of blA corresponding to the friction coefficients below

0

0.083

0.111

0.167

0.333

Maximum tensile principal stress that occurs in surface at x = -b

0

2b --

128

2--b 9A

2--b 6A

2-b 3A

Maximum compressive principal stress that occurs in the surface between x = 0 and x = 0.3b

b --

b -1.09A

b -1.13A

b -1.19A

b -1.40A

Maximum shear stressa

0.300-b A

0.308-b A

b 0.310A

b 0.339A

b 0.435A

b 0.272A

b 0.265A

b 0.255-

b 0.277A

b 0.368A

Maximum octahedral shear stressa

A

A

aNote that these stresses occur at the surface when the friction coefficient is 0.10 or larger.

For small values of the friction coefficient, the values of shear stress are increased only slightly by an increase in the friction coefficient, whereas there is a small decrease in octahedral shear up to a friction coefficient of 0.167. For the case of a disk in rolling contact with a cylinder and for p = 0.333, Mitsuda (1965) noted that the range of maximum octahedral shear stress is 26% larger than the range of maximum orthogonal shear stress.

17.9.6 Range of Shear Stress for One Load Cycle The magnitude of the maximum shear stress or maximum octahedral shear stress serves to indicate if yielding has taken place or to determine the factor of safety against impending yielding. However, in the case of fatigue loading,the runge of shear stress on a given plane in a given direction in that plane is more commonly used to indicate the severity of a given loading. In the absence of friction, the runge of the orthogonal shear stress for two cylinders in rolling contact is

620

CHAPTER 17 CONTACT STRESSES

2%= OSOb/A[% = 0&-)];this range is greater than either the correspondingrange of maximum shear stress (0.30b/A) or the corresponding range of octahedral shear stress (0.27b/A). The presence of friction has little influence on the range of the orthogonal shear stress. However, the ranges of shear stress on certain planes increase with the coefficient of friction; the maximum range is as large as 0.67b/A for p = 0.333. Furthermore,this range occurs for points at the free surface of the contacting bodies where fatigue failures are more likely to be initiated. For rolling cylinders in contact, Smith and Liu (1953) have determined the principal state of stress for a point in the surface of one of the rolling cylinders for the special case of the coefficient of friction p = 0.333. The principal stresses are indicated in Table 17.2 TABLE 17.2 Principal Stresses at Fixed Point 0 as Contact Surface Moves Relative to 0 Position of contact surface relative to fixed point 0

Direction of principal stresses of fixed point 0

Zl

a3 = 0

0Ul

0,a, = 0

a, = 0 b b A u2= -0.17- A u1= -0.67--,

b

(TI

= -1.33-

@

b

u1= -1.39b

= -0.67; A

X

u1= -1.33 -

A

03

=0

0

b A

-

A

= -0.7*-: A

&a2

= -0.51

u1= 0,a, = 0

~ 3 = - 0 . 5 3bA

~ 3 = - 0 . 5 0bA

17.9

STRESSES FOR TWO BODIES IN LINE CONTACT: LOADS NORMAL AND TANGENT TO CONTACT AREA

62 1

for a volume element located at a point 0 for several locations of point 0 relative to the contact surface. For each location of point 0, the shear stress and octahedral shear stress attain maximum values on certain planes passing through point 0. The largest values of these maxima,,z,[ and z,,,~(,~)] occur for the volume element located at point 0 in Figure (d) of Table 17.2. Smith and Liu noted the two sets of planes on which the largest values of, , z and z~ ,(~), occur and determined the magnitude and sense of the shear stress acting on these planes for various locations of point 0. They also defined the maximum range of shear stress on either set of planes to be the magnitude of the maximum diameter of the shear stress envelope. (These maximum ranges were found to be 0.53blA and 0.63blA; Smith and Liu, 1953). Note that in Figure ( b) of Table 17.2 the maximum shear stresses for these two states of stress occur on the same planes and they are opposite in sign; the range of shear stress for these planes is 0.67blA. Only four sets of the infinite number of planes through point 0 [including planes perpendicular to the x and z axes on which z, = ozx(max) occurs] were investigated; therefore, the range of shear stress (0.67blA) may not be the largest that occurs. However, the results do indicate that a tangential component of force at the contact surface increases the probability of fatigue failure, particularly if the coefficient of friction approaches a value of 0.333.

EXAMPLE 17.3 Contact Stress in Cylinders with Friction

Solution

A fatigue testing machine has two identical steel disks (E = 200 GPa and v = 0.29) rolling together. The identical disks have a radius of curvature of 40 mm and width h = 20 mm. For rolling without , , = 1445 MPa,, , ,z = 433 MPa, and friction, a load P = 24.1 kN produces the following stresses: b z~ ,(~), = 361 MPa. Let the cylinders be subjected to a load P = 24.1 kN and be rotated at slightly different speeds so that the roller surfaces slide across each other. If the coefficient of sliding friction and z o c i ~ m a x ~ is 0.11 1, determine o,,,(tension), o,,,(compression), ,,,,z From Table 17.1 the value of the stresses are found as follows: o,,(tension)

=

2b --

9A

b A zmaX= 0.310-b A

omax ( compression)

= -1.13-

The magnitudes of A and b are given by Eqs. 17.39 and 17.38:

b = E = , /

- - 1447MPa

A

2(24.1 x 103)(0.0003664) = o.5301 mm 20n

622

CHAPTER 17 CONTACT STRESSES

Therefore, we have the following results: o,,(tension) o,,(compression) Zmax

2 = -(1447) = 322 MPa 9 = -1.13( 1447) = -1635 MPa = 0.310(1447) = 449 MPa = 0.255( 1447) = 369 MPa

The friction force (for a coefficient of sliding friction of 0.1 11) increases the maximum compression stress by 13.1%,maximum shear stress by 3.7%, and maximum octahedral shear stress by 2.2%.

PROBLEMS Section 17.7

17.1. A steel railway car wheel may be considered a cylinder with a radius of 440 mm. The wheel rolls on a steel rail whose top surface may be considered another cylinder with a radius of 330 mm. For the steel wheel and steel rail, E = 200 GPa, v = 0.29, and Y = 880 MPa. If the wheel load is 110 kN, determine CT,,,, z ,, z ~22,, and ~ the factor ~ of safety ( against ~ initia~ tion of yielding based on the maximum shear-stress criterion. 17.2. Determine the vertical displacement of the center of the wheel in Problem 17.1 caused by the deflections in the region of contact.

17.8. A cast-iron push rod (E = 117 GPa and v = 0.20) in a valve assembly is operated by a steel cam (E = 200 GPa and v = 0.29) (Figure P17.8). The cam is cylindrical in shape and has a radius of curvature of 5.0 mm at its tip. The surface of the push rod that contacts the cam is spherical in shape with a radius of curvature 4. ~0m so that ~ the rod and cam are in point contact. If the ailowable maximum principal stress for cast iron is -1400 m a , determine the maximum load P that may act on the rod.

17.3. In terms of P compute the maximum principal stress, maximum shear stress, and maximum octahedral shear stress in two steel balls (E = 200 GPa and v = 0.29) 200 mm in diameter pressed together by a force P. 17.4. Solve Problem 17.3 for the condition that a single steel ball is pressed against a thick flat steel plate. (For unit of length, use millimeters.) 17.5. Solve Problem 17.3 for the condition that a single steel ball is pressed against the inside of a thick spherical steel race of inner radius 200 mm. 17.6. A feed roll (a device used to surface-finish steel shafts) consists of two circular cylindrical steel rollers, each 200 mm in diameter and arranged so that their longitudinal axes are parallel. A cylindrical steel shaft (60 mm in diameter) is fed between the rollers in such a manner that its longitudinal axis is perpendicular to that of the rollers. The total load P between the shaft and rollers is 4.5 kN. Determine the values of the maximum principal stress and maximum shear stress in the shaft. Determine the distance from the plane of contact to the point of maximum shear stress. Use E = 200 GPa and v = 0.29 for the shaft. 17.7. The longitudinal axes of the two feed rollers in Problem 17.6 are rotated in parallel planes until they form an angle of n/6 radians. The steel shaft is then fed between the two rollers at an angle of a/12 radians with respect to each of the rollers; again, P = 4.5 kN. Determine the maximum principal stress, maximum shear stress, and distance from the plane of contact to the maximum shear stress.

mm

FIGURE P17.8 Contact load in valve tappet.

17.9. A fatigue testing machine used to determine fatigue life under rolling contact consists of a steel toroid (body 2) rolling on a steel cylinder (body I), where R, = 32 mm, R ; = 00,R, = 32 mm, and R; = 20 mm. For steel, E = 200 GPa and v = 0.29. a. Determine an expression for omax in terms of P.

b. Fatigue test results indicate that fatigue failure occurs at approximately N = lo9 cycles with om,, = -2758 MPa. Determine the applied load P. Since a = 0 and R , and R, lie in the x-z plane (see Figure 17.5), b (the minor semiaxis of the contact eclipse) is in the direction of rolling.

REFERENCES

17.10. In the fatigue testing machine of Problem 17.9, the same cylinder is used, but the toroid is replaced by a second toroid, where R , = 00, R; = 32 mm, R, = 12.8 mm, and R; = 32 mm. Use the same steel properties as in Problem 17.9.

om, for fatigue failure at approximately N = lo9 cycles. Neglect size effects and assume that fatigue failure is governed by the maximum range 2r0 of the orthogonal shear stress. a. Determine

b. Determine the required load P. Since a = 0 and R; and R; lie in the x-z plane (see Figure 17.5), a (the major semiaxis of the ellipse) lies in the direction of rolling.

623

17.11. A hard steel ball (E = 200 GPa and v = 0.29) of diameter 50 mm is pressed against a thick aluminum plate (E = 72.0 GPa, v = 0.33, and Y = 450 m a ) . Determine the magnitude of load P , required to initiate yield in the aluminum plate according to the octahedral shear-stress criterion of failure. 17.12. For Problem 17.1 1 use a safety factor SF = 1.75. a. Recalculate the required load.

b. For this load, determine the displacement (approach) 6 of the ball relative to the plate.

Section 17.8

17.13. A fatigue testing machine rolls together two identical steel disks (E = 200 GPa and v = 0.29), with radii 40 mm and thickness h = 20 mm. In terms of the applied load P, determine omax, rmaxt Toct(rnax)? and re 17.14. Test data for the disks of Problem 17.13 indicate that fatigue failure occurs at approximately lo8 cycles of load for om,,= -1380 MPa. a. Determine the corresponding value of load P.

b. For a fatigue failure at lo8 cycles and a factor of safety SF = 2.50, determine the value of omax.

17.15. The rail in Problem 17.1 wears in service until the top is flat with a width h = 100 mm. a. For other conditions given in Problem 17.1 remaining con-

stant, determine the values of om,,and rma,. b. Using the maximum shear-stress criterion of failure, determine the safety factor SF against initiation of yield.

17.16. A cylindrical steel roller, with diameter 30 mm, is used as a follower on a steel cam. The surface of the cam at the contact region is Cylindrical with radius of curvature 6 mm. Under no load, the follower and cam are in line contact over a length of 15 mm. For a value om,= -1000 MPa, determine the corresponding applied load P (E = 200 GPa and v = 0.29).

Section 17.9

17.17. Two cylindrical steel rollers (E = 200 MPa and v = 0.29), each 80 mm in diameter and 150 mm long, are mounted on parallel shafts and loaded by a force P = 80 kN. The two cylinders are rotated at slightly different speeds so that the roller surfaces slide across each other. If the coefficient of sliding friction is p = 0.333, determine the maximum compressive principal stress, maximum shear stress, and maximum octahedral shear stress.

a. Determine the load P that can be applied to the cylinders to cause fatigue failure after lo9 cycles (p = 0).

b. Determine the load P that can be applied to the cylinders to cause fatigue failure at approximately lo9 cycles for p = 0.333. Assume that om,,to cause fatigue failure is inversely proportional to the range of shear stress on a given plane and that the maximum range of shear stress is 0.67b/A for p = 0.333.

17.18. The two cylinders in Problem 17.17 are hardened. It is found that fatigue failures occur in the cylinders after lo9 cycles for om,= -1500 MPa when p = 0.

ALLEN,R. K. (1945). Rolling Bearings. London: Pitman. FESSLER, H.,and OLLERTON, E. (1957). Contact Stresses in Toroids under Radial Loads. Brit. J. Appl. Phys., S(10): 387. HERTZ,H. (1895). Gesammetlte Werke, Vol. 1. Lepzig. [For an English translation, see Hertz, H.(1896). Miscellaneous Papers. New York: Macmillan.] JOHNSON,K. L. (1985). Contact Mechanics. Cambridge: Cambridge Univ. Press. MINDLIN,R. D. (1949). Compliance of Elastic Bodies in Contact. J. Appl. Mech., 16(3): 259. T. (1965). An Investigation of Pitting and Shelling Failure in MITSUDA, Univ. Ill., Dept. TheoretiRolling Contact. UrbandChampaign, E. cal and Appl. Mech., Ph.D. thesis, p. 16 and Table 1 .

MOYAR, G. J., and MORROW,J. D. (1964). Surface Failure of Bearings and Other Roller Elements. UrbandChampaign, IL: Univ. Ill., Eng. Exper. Station, Bull. 468. SMITH, J. O., and LIu, C. K. (1953). Stresses due to Tangential and Normal Loads on an Elastic Solid with Applications to Some Contact Stress Problems. J. Appl. Mech., 20(2): 157. H. R., and HOERSCH, V. A. (1930). Stresses due to the PresTHOMAS, sure of One Elastic Solid on Another. UrbandChampaign, I L Univ. Ill., Eng. Exper. Station, June 15, Bull. 212. TIMOSHENKO, S., and GOODIER, J. (1970). Theory ofElasticity, 3rd ed. New York: McGraw-Hill.

CHAPTER

18

CRE’EP:TZME-DEPENDENT DEFORMATION

18.1 DEFINITION OF CREEP AND THE CREEP CURVE At ordinary temperatures and in the absence of a corrosive environment, a properly designed member will support its static design load for an unlimited time. However, at socalled elevated temperatures, the life of the member may be severely limited, even for loads less than the design load. At elevated temperatures, a sustained load may produce inelastic strain in the material that increases with time. Hence, the material is said to creep, creep being defined as time-dependent inelastic strain under sustained load and elevated temperature. If creep occurs for a sufficiently long time, excessive deflection (creepfailure) or fracture (creep-fracture) occurs. The combination of temperature, load, and time that produces creep and possibly creep-failure or creep-fracture of a member depends on the material and the environment. Consequently, creep, creep-failure, and creepfracture of a member may occur over a wide range of temperature and load. Creep will occur in any metal subjected to a sustained load at a temperature slightly above its recrystallization temperature. At this temperature, the atoms become quite mobile. As a result, time-dependent alterations of the metal’s structure occur. It is often stated that “elevated temperature” for creep behavior of a metal begins at about one-half the melting temperature T, of a metal measured in Kelvins. However, this is a rule of thumb that greatly oversimplifies a very complex behavior. The temperature at which a member’s function is limited by creep rather than, say, yield strength is not directly related to T,. In reality, the meaning of elevated temperature must be determined individually for each material on the basis of its behavior. As noted in the American Society for Metals’ Handbook (ASM, 1976), elevated temperature behavior for various metals occurs over a wide range of temperature, for example, at 205°C(400°F)for aluminum alloys, 540°C(1000°F)for austenitic, iron-based high-temperature alloys, and 980” to 1540°C (1800” to 2800°F) for refractory metals and alloys. In contrast, for certain plastics, asphalt, concrete, lead and lead alloys, and wood and wood composites, elevated temperatures for creep behavior may lie in the range of “ordinary temperatures,” say, from 0”to 50°C (32”to 122°F). The original observations of creep in materials are lost in antiquity. A simple form of creep in nature is the slow, almost imperceptible downslope movement of soil particles and rock debris under the influence of gravity. Early humans may have observed the creep of rocks that formed the sides and roofs of caves or of ice in the walls and roofs of igloos. The fact that windows in old churches in Europe are thinner at the top than at the bottom has been attributed to the creep of the glass under the effect of gravity. Today, engineers and scientists confront creep in energy-producing systems such as power-generating plants (coal, gas, and nuclear plants). Creep also occurs in energy conversion systems,

624

18.1

DEFINITION OF CREEP AND THE CREEP CURVE

625

such as thermionic converters, and in modem-day applications of electronic packaging that involve the heat transfer and cooling of microcircuits [microelectronic chips, electronic circuit boards, surface-mounted electronic components, solder joints, etc.; see, e.g., the Journal of Electronic Packaging (ASME)]. Unfortunately, we cannot provide in the space available here an exhaustive historical development of creep analysis, even for metals, let alone other materials. However, such developments may be found in previously published treatises. For example, the creep of wires of hardened iron at room temperature was observed and studied quantitatively as long ago as 1834 by the French engineer L. J. Vicat (1834). He observed, among other things, the first part (primary range) of the classical form of the strain-time plot (creep curve; Figure 18.1). Vicat’s interest was focused mainly on the use of wire for load-carrying members in suspension bridges. However, it was not until the beginning of the twentieth century that the entire creep curve of Figure 18.1 was developed for iron wire and for several other materials (Phillips, 1905; Andrade, 1910). Much of the history of creep of metals has its origins in the industrial revolution that led to the operation of machines at the highest possible temperatures to achieve the greatest thermal efficiencies. One of the first comprehensive studies of the purposes and techniques of stress analysis and design in creep problems was made by Bailey (1935). In the late 1950s and 1960s,there was a great resurgence in creep studies, resulting in part from the interest in nuclear reactor power generation and the high temperatures used in such systems. During this period, several books dealing with stress analysis of creep were published in various countries. One of these books (Finnie and Heller, 1959) summarized many of the earlier creep studies and the associated stress analysis techniques. Other publications during this period include books by Kachanov (1960), Lubahn and Felgar (1961), Odqvist and Hult (1962), Odqvist (1966), Hult (1966), Rabotnov (1969), and Penny and Maniott (197 1). Several surveys were also published during this period (e.g., ASTM, 1959; ASTM, 1965). A review of creep of metals under multiaxial states of stress, including an extensive list of references up to 1971, was given by Boresi and Sidebottom (1972). More recently, the book by Kraus (1980) presents an introduction to design problems of creep; the book by Boyle and Spence (1983) treats basic methods of stress analysis of creep; the book edited by Bernasconi and Piatti (1979) covers a wide range of creep problems from basic concepts to experimental techniques; Cadek (1988) explores high-temperature creep as affected by

P

FIGURE 18.1 Creep curve.

t

626

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

metallurgical mechanisms (e.g., motion of dislocations, dislocation structure, dislocation creep in pure metals); the volume edited by Curbishley (1988) discusses tensile testing (T. G. F. Gray, Chapter 1) and creep testing (M. S. Loveday, Chapter 2). In this chapter, we are concerned mainly with mathematical equations used to represent creep strain (Figure 18.1) as a function of stress, temperature, and time and the use of these equations to study the effects of creep. Therefore, we assume that an elevated temperature for a material exists so that the material may creep. A phenomenological approach is taken to describe the physical processes that alter the metallurgical structure of a material, allowing creep to occur. Furthermore, we do not attempt to describe in any detail various creep models (viscoelastic, elastic-plastic, etc.) that have been proposed. Rather, we base our study on the typical creep curve (plot of strain versus time; Figure 18.1) and mathematical modeling of the creep curve. Creep curves are ordinarily obtained by tests of bars subjected to sustained axial tension (Loveday, 1988). Standards for creep tests have been established by several technical organizations (ASTM, 1983; BSI, 1987; ISO, 1987). In Section 18.2, we briefly describe the tension creep test for metals. In Sections 18.3 and 18.4,we present one-dimensional creep formulas for metals subjected to stress and elevated temperature. In Sections 18.5 and 18.6, the creep of metals subjected to multidimensional states of stress is considered. Some applicationsto simple problems in creep of metals are discussed in Section 18.7. In Section 18.8,a few observations relative to creep of nonmetals are given.

18.2 THE TENSION CREEP TEST FOR METALS The creep behavior of various materials is often based on a one-dimensional (tension)test. Various standards for creep testing [email protected] the geometric design of test specimens (ASTM, 1983; BSI, 1987; ISO, 1987). Careful control of machined dimensions is specified (Loveday, 1988). During the test, the tension specimen is subjected to sufficientlyhigh stress d and temperature T to produce time-dependent inelastic strain (creep). Highly sensitive creep-testing systems have been developed to measure load (stress) and temperature to ensure accurate creep data over long periods of time (Loveday, 1988). In the creep test, the strain in the specimen varies with time. For an appropriate constant stress and elevated temperature, a strain-timeplot (creep curve) is shown in Figure 18.1. This creep curve exhibits three distinct ranges. Beginning at time t = 0, the strain is 6 due to the initial loading. The strain 6 may be partly elastic and partly plastic, depending on the level of load and temperature. In the first interval of time, the primary range of the creep curve, the strain rate (the slope of the creep curve), decreases,until it reaches some minimum rate. During the next interval of time, the secondary range, this minimum rate is maintained, more or less, until a time at which the strain rate begins to increase, the beginning of the tertiary range. In the tertiary range, the strain rate continues to increase under the sustained stress and temperature until, at time t = tR, the specimen is pulled apart (point x in Figure 18.1). In the following section, various formulas that have been used to approximate one-dimensional curves are discussed.

18.3 ONE-DIMENSIONAL CREEP FORMULAS FOR METALS SUBJECTED TO CONSTANT STRESS AND ELEVATED TEMPERATURE As noted in Section 18.1, by creep we mean the inelastic strain that occurs when the relationship among stress, strain, and elevated temperature is time dependent. In general, creep behavior is a function of the material, stress, temperature, time, stress history, and

18.3

ONE-DIMENSIONAL CREEP FORMULAS FOR METALS SUBJECTED TO CONSTANT STRESS AND ELEVATED TEMPERATURE

627

temperature history. Creep behavior includes the phenomenon of relaxation, which is characterized by the reduction of stress in a member, with time, while total strain remains constant. It also includes recovely, which is characterized by the reduction of inelastic strain with time after the stress has been removed (see Kraus, 1980, Chapter 3). However, the topics of relaxation and recovery lie outside the scope of our discussion. Creep of metals at elevated temperatures is characterized by the fact that most of the deformation is irreversible; that is, only a small part of the strain is recovered after removal of load. In addition, the dependence of creep rate on stress is nonlinear. As a consequence, linear theories of viscoelasticity do not ordinarily apply to metals (Rabotnov, 1969). Thus, the theory of creep of metals, the objective of which is to describe time-dependent irreversible deformation, is patterned after the general theory of plasticity. At elevated temperatures, plastic deformation of metals is usually accompanied by creep. Therefore, in real situations of creep, the concepts of creep and plasticity intertwine. However, in the representation of creep data by empirical formulas, creep deformation is separated from plastic, and likewise elastic, deformation. For one-dimensional states, the classical creep curve for a material is obtained from a tensile test at constant stress d and temperature T (Figure 18.1). As noted in Section 18.1, the creep curve for metals usually exhibits three regions in which the creep deformation takes on a different character (curve C,, Figure 18.2). With reference to curve C,, interval OA represents the instantaneous deformation that occurs immediately as the load is , Depending on the stress level CT and temperaapplied. This strain is denoted by E ~ ( C T T). ture T, e0 may include both elastic and plastic parts. The intervalAB represents the primary (initial) stage of creep deformation. In this interval, the creep deformation is changing (is transient) at a decreasing strain rate. It is for this reason that investigators often represent the creep behavior in the primary time stage by formulas that express the creep strain rate EC as a function of stress CT, temperature T, and time t, where the dot denotes derivative with respect to time. The interval BC represents the second stage of creep in which the

0

Time

FIGURE 18.2 Creep curve illustrating instantaneous deformation and primary, steady-state (secondary),and tertiary stages.

628

CHAPTER 18 CREEP: TIME-DEPENDENT DEFORMATION

creep rate reaches a minimum value. If in this region the creep rate remains constant, the creep strain rate is a function of stress CT and temperature T only; that is, ic =f(o, T ) , and the creep strain eC is a linear function of time t. The interval CD represents the third (tertiary) creep stage, in which the creep strain rate increases rapidly. If the load is sustained in this region, creep rupture will occur (point D on curve ABCD). Although the division of the creep curve into three intervals is conventional for many metals, depending on the metal, stress, and temperature, a variety of creep curves may be obtained as a consequence of the complexity of the metallurgical processes involved. For example, for materials different from that used to generate curve Cl and for the same load and temperature for curve C1(Figure 18.2), the strain-time response may be given by curves C,, C,, or C,. Or if the material used to generate curve C1 is subjected to a lower load and/or temperature, its response may be given by curve C,, for which the tertiary range of creep is never reached. If the material of curve C1 is subjected to a higher stress and/or temperature, its response may be given by curve C , (for which the primary range of creep is suppressed) or curve C, (for which both the primary and secondary ranges of creep are bypassed and for which fracture occurs in a relatively short time). For example, for annealed SAE 1035 steel at a constant temperature of 524"C, Figure 18.3 illustrates the change in the creep curve that is produced by increasing the stress level in steps of approximately 20 MPa from 83 to 164 MPa. Similar increases in the creep strain also occur with temperature for constant stress. Additionally, it is difficult to determine the instantaneous deformation e0 precisely, since it depends on the method of loading. Much of the published creep data ignore this quantity, and creep curves are simply plots of ec versus time (partABCD of curve C,, Figure 18.2). Because of the extreme complexity of creep behavior, the analysis of creep problems is often based on curve-fitting of experimental creep data. These representations generally attempt to represent the creep strain q or creep strain rate EC as functions of stress 0,temperature 7',and time t. Usually, such equations have been developed by one of three methods: 1. by

0.03

0.02 uzz = 148 MPa c .-

e

z

0.01 uzz= 124 MPa

a,,= 103 MPa a,, = 83 MPa

0

FIGURE 18.3

25

75 Time ( m i d

50

Constant-stress tension creep curves for annealed SAE 1035 steel at 524°C.

18.3

ONE-DIMENSIONAL CREEP FORMULAS FOR METALS SUBJECTEDTO CONSTANT STRESS AND ELEVATEDTEMPERATURE

629

deriving empirical formulas that model experimental data (Rabotnov, 1969, Chapter IV), 2. by deriving equations based on metallurgical creep mechanisms (Dorn, 1962; Cadek, 1988),or 3. by a combination of methods 1 and 2 (Kennedy, 1962). In these methods, attempts have been made to separate various influences for each stage of creep. For example, in the first method, one may represent any one of the three stages separately by an empirical formula; or one may represent two stages by a single formula, say, the primary and secondary stages, or all three stages by a single formula. Alternatively,in method 2, one may consider the effect of a particular creep-producingmechanism, say, dislocations (Cadek, 1988),on the various stages of creep and attempt to relate various parameters in the strain-stress-temperature-time relations to the properties of the dislocations. In Table 18.1, we list a number of formulas that have been used to represent one-dimensional creep curves. Many of these formulas are discussed in the references listed in the table. Following Kennedy (1962), we separate the equations into time-, temperature-, and stress-dependent parts. We also indicate combinations of time, stress, and temperature components. The time-dependence formulas are sometimes of the form E = e0 + cC, where EC = E X + ESC + E ~ CE, is the total strain, q, is the instantaneous strain, eC is creep strain, and epC,eSC,and eTCdenote primary, secondary, and tertiary creep, respectively. The various components of the total strain E are selected to fit creep data at constant stress and temperature (method 1). If practical interest does not extend to the tertiary stage, the effects of eTCare not included in some of the formulas. Generally, e0 is a constant, CPc is a monotonically decreasing function of time, eSCis a linear function of time, and iTcis a monotonically increasing function of time, where a dot denotes derivativewith respect to time. The temperature dependency of creep is often related to thermodynamics and rate processes of solid-state physics (Dorn, 1962; Cadek, 1988). Consequently, the temperature dependency is often of exponential form. Also, experimental evidence indicates that the creep rate in the secondary stage of creep increases more rapidly with temperature increases than does the creep rate in the primary stage of creep. Finally, since stress is a tensor (Chapter 2), whereas temperature and time are scalars, introducing stress dependency into creep formulas is a more difficult task. Therefore, more than one function of stress has to be employed, if creep behavior over a wide range of stress is to be fitted accurately. In general, to model creep curves (Figures 18.1-18.3), one needs expressions of the wherefis a general function of time t, temperature T, and stress 6. It form eC = f ( t , T, 6), is customary to assume that the effects oft, T, and CT are separable. Then, in general,fmay be taken as a sum of n products oft, T, and 6, and E~ may be written in the form

Thus, experiments for one-dimensional creep behavior are usually run allowing only one of the variables (t, T, 6)to change (see Figure 18.3, where d is varied for constant temperature T and a given time t). The formulas in Table 18.1 reflect the separation of stress, temperature, and time. It should be noted that, in practice, the determination of the time dependence of creep for a complex metal (alloy) that exhibits large structural change with time at elevated temperature is very difficult. It requires extensive curve-fitting procedures (see Conway, 1968, 1969; Penny and Marriott, 1971; Kraus, 1980). Consequently, Eqs. (a) through (i) are not generally applicable. Any one of them may hold for a certain metal and for certain test conditions. However, many of them are not conveniently adapted to include effects of temperature and stress. By combining the time, temperature, and stress representations, Eqs. (bb) through (gg) in Table 18.1, the entire functional behavior of creep may be approximated by a

630

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

TABLE 18.1 Empirical One-Dimensional Creep Formulas Equation form

References Time Dependence

Rational ec = at/(l + bt) Logarithmic c = a + b In(t) e=a+bln(l +ct) Exponential c = a + bt - c exp(-dt) ec = at + b[1 - exp(-ct)] Power eC = bt"; 113 < n < 112 Power series ec = atm+ bt"; r n > 1,0 < n < 1 ec = at, + bt,, + ctp + ... Combined exponential power eC = a ( l + bt1I3)exp(kt) - a Combined logarithmic power ec = a In(t) + bt" + ct

(Freundenthal, 1936) (PhiIIips, 1905) Modification of (b) (McVetty, 1934) (McVetty, 1934; Soderberg, 1936) (Bailey, 1935) (de Lacombe, 1939) (Graham, 1953) (Andrade, 1910) (Wyatt, 1953)

Temperature Dependence

Exponential kc = a exp(-Q/Rl) ec = a[ t exp(-Q/Rl)] 6 , = aTexp(-Q/RT) Rational cc = a ~ * " f ( t ) ec = aTf(t) ec = f { T [ a+ In(t)l} ec = f [ ( T - a)lln(t- b)] Hyperbolic exponential gc = a exp(-Q/RT) sinh(b/RT) Other ec = cot(T- T'1-31

(Mott, 1953) (Dorn, 1962) (Stowell, 1957) (Mott and Nabarro, 1948) (Smith, 1948) (Larson and Miller, 1952) (Manson and Haferd, 1953) (Feltham, 1953) (Warren, 1967) Stress Dependence

Exponential ec = af(t)exp(bo) gc = a exp(b + co) Pc = a[exp(bo) - 11 Power cc = af(t)ob eC = at"ub;O< n < I, b > I; Bailey-Norton law Hyperbolic gC = a sinhfbo) kc = a sinh(bo/RT) Other Pc = ao exp[f(o)l

(Dorn, 1962) (Nadai, 1931) (Soderberg, 1936) (Dorn, 1962) (Bailey, 1935; Norton, 1929)

(Ludwik, 1908; McVetty, 1943) (Feltham, 1953) (Kanter, 1938)

Equation

18.4

ONE-DIMENSIONALCREEP OF METALS SUBJECTED TO VARIABLE STRESS AND TEMPERATURE

631

TABLE 18.1 Empirical One-Dimensional Creep Formulas (continued) Equation form

References

Equation

Combined TimeTemperatur4tress Dependencies Gc = Texp(-a/T- b + ca) ec = a exp(-AIT)a"tk

(Nadai, 1931) (Pickel et al., 1971)

q = a exp(-AIT)sinh(ao)tk

(Pickel et al., 1971) (Pickel et al., 1971) (Odqvist, 1953)

ec = a exp(-AIT) x [sinh(bo)lrntk cC = a exp(-A/T)(o/b)C + (o/det n

ec =

C C p a @ J i ;Q = t(T' - TI+'

(Graham and Walles, 1955)

(bb) (cc) (dd) (ee) (ff)

(gg)

i= 1

single equation. An extensive discussion of the application of Eq. (gg) is given by Kennedy (1962).The successful use of these equations generally requires numerical methods (Kraus, 1980) such as finite element methods. Many of the formulas in Table 18.1 may be applied to multiaxial stress states through the use of the concept of effective stress (Section 4.3) and the corresponding concept of effective strain rate (Section 18.6). Kennedy (1962) also discusses at length strain-stress-temperature-time relations based on quasiempirical methods and metallurgical (microstructure) observations. The distinguishing feature of microstructure formulations is that an attempt is made to relate the parameters in the creep relation to creep-producing microstructure mechanisms such as grain boundary displacement, slip, and subgrain size (see Cadek, 1988). In Table 18.1, E denotes total strain, eC creep strain, d stress, T temperature, t time, In the natural logarithm, exp the exponential e, and a, b, c, ... , A , B, C , ... parameters that may be functions of 6,t, Tor may be constants. Time derivative is denoted by a dot over a symbol (e.g., +). The notationf(x) denotes a function of x.

18.4 ONE-DIMENSIONAL CREEP OF METALS SUBJECTED TO VARIABLE STRESS AND TEMPERATURE 18.4.1 Preliminary Concepts As indicated by Loveday (1988), there are many designs for creep-testing machines. They differ mainly in the method of measuring deformation and the methods of heating and controlling temperature. Several of these machines are of the lever type that ensures constant load. However, during a constant-load creep test, a creep specimen enlongates and its cross-sectional area decreases. Consequently, the stress is not truly constant; that is, for a constant applied force, the stress increases during the test. Some attention has been devoted to the fact that the stress is not constant, and various machines have been designed to maintain constant stress (Loveday, 1988). In the design of these machines, it is assumed that the volume of the creep specimen remains constant and that the change in cross-sectional area can be determined from the elongation of the specimen. Lubahn and Felgar (196 1, Chapter 6) give an interesting discussion of the difference between constant-load and constant-stress creep tests. Also,

632

CHAPTER 18 CREEP TIME-DEPENDENTDEFORMATION

Andrade (1910) found that the elongation of lead wire for constant-load testing was considerably larger than for constant-stress loading, particularly at stress levels near the ultimate strength. He also found that under constant load, the creep curve for lead wire exhibited three stages of creep (primary, secondary, and tertiary), whereas for constant stress, the creep curve exhibited only the primary and secondary stages (Figure 18.4). Lubahn and Felgar (1961, p. 136) observe that for a metallurgically stable material subject to a tensile creep test at constant stress, the creep rate continues to decrease indefinitely, this effect being caused by strain hardening (see Section 4.2). If the load is kept constant, the creep rate will tend to increase after sufficient creep has occurred, because of the reduction of cross-sectional area of the specimen. Since the strain-hardening effect tends to decrease with increasing deformation and the reduction of cross section increases with increasing deformation, a strain is eventually reached at which the effect of reduction of area dominates, the strain rate begins to increase rapidly, and the creep curve exhibits an inflection point (the start of the tertiary stage). This balance between reduction of cross section and strain hardening is similar to the balance of necking down and strain hardening in the static tension test (Chapter 1). Therefore, it may be regarded as a structural instability that leads to fracture. For many metals this instability occurs at about the same strain in the creep test as it does in the tension test. At temperatures where creep is important, metals are often metallurgical unstable; that is, their properties change either gradually or abruptly with time. Because of these metallurgical changes, or the lack of them, the creep rate of a metal may remain constant for long periods of time, it may increase continuously from the beginning of the creep test, or it may remain constant for a brief time and then increase rapidly (even for a constant-stress creep test) to fracture. Thus, one should not assume that all metals always exhibit three distinct regions of primary, secondary, and tertiary creep. In machines and structures, ordinarily only small creep strains on the order of 1% or 2% are permitted. In addition, high-strength, heat-resistant alloys fracture at relatively small deformations. Consequently, much creep testing is restricted to small strains. For constantstress creep tests of a metallurgically stable metal, creep strain in the secondary stage appears to vary almost linearly with time (Figure 18.1); that is, the creep rate is constant. For this reason, the secondary stage of creep is referred to as steady-state creep, and straight-line

32

30

28 v

54

26

24

22

I 100

I

I

200 300 Time (rnin)

I 400

5

FIGURE 18.4 Creep tests of lead wire. Initial loads and initial lengths were the same. (From Andrade, 1910.)

18.4

ONE-DIMENSIONALCREEP OF METALS SUBJECTEDTO VARIABLE STRESS AND TEMPERATURE

633

approximations of this stage are used. However, early published results of tests (Robinson, 1943) that lasted 12 years (100,000 hr) showed that the creep rate changed continuously throughout this time. Nevertheless, over a particular period of time, experimentally determined straight-line approximations can be used with sufficient accuracy for many purposes. More recently, Evans and Wilshire (1985) questioned the steady-state ideas that have dominated theoretical studies of creep for over the past half-century. Although Evans and Wilshire acknowledge that the concept of steady-state creep has led to progress, they believe that further development depends on new concepts based on the view that the steady-state creep condition is not attained even at high temperatures. These new concepts are based on experimental data obtained using high-precision constant-stress machines, rather than constant-load machines. Evans and Wilshire (1985) explored the idea that most materials exhibit a minimum rather than a steady-state creep rate and have developed new formulas and computer programs to study creep. Their work may be particularly important in the case of large creep deformations that lead to rupture. However, these concepts and procedures lie outside the scope of our study here. Therefore, we employ the concept of steady-state creep and consider mainly the primary and secondary stages of creep.

18.4.2

Similarity of Creep Curves

The similarity of creep curves has been used by many authors in the development of phenomenological theories of creep (Rabotnov, 1969; Boresi and Sidebottom, 1972). Similarity of creep curves means that the creep deformation is representable in the form

Thus, for a given temperature, the stress dependency F ( o ) is separable from the time dependencyf(t). For example, for isothermal conditions a common form of Eq. 18.1 is the power form [the Bailey-Norton equation; Eq. (x), Table 18.11 eC = at

n b CT

(18.2)

Experimentally, the separation of time and stress dependencies is fairly well justified for the initial part of the creep curve. Indeed, for many metals, Eq. 18.2 is valid for the initial part of the creep curve. A series of creep curves may be considered as a graphical representation of the equation E

=

E ( Q , 2)

(18.3)

with one (E, t) curve for each value of CT (Figure 18.5). Alternatively, the relation among E, Q, and t may be expressed by plotting Q versus E for given times tl, t2, ... (Figure 18.6). Curves of (6, E), for given times tlr t2, ..., are called isochronous creep curves. For some materials, isochronous creep curves are similar. Thus, by analogy to Eq. 18.1, isochronous creep curves may be represented by the relation

However, the conditions of similarity of isochronous creep curves are very different from ordinary creep curves; see Eq. 18.1 (see Rabotnov, 1969). In Eq. 18.4, if we set g(0) = 1, then Q = G ( E )is the instantaneous deformation relation. In published experimental data on creep, the data for the initial stage of creep are

634

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

t=O

FIGURE 18.5

ti

12

t

Constant-stress creep-time curves.

0

FIGURE 18.6

(3

E

Isochronous stress-strain diagram.

sometimes unreliable, since the instantaneous strain e0 that occurs on applying the load is not recorded accurately. Consequently, creep curves for very small values of t frequently are not accurate (Evans and Wilshire, 1985). By selecting g ( t ) appropriately, we can obtain the instantaneous curve o = G(E)by extrapolation. However, we have no guarantee that the actual instantaneous curve is obtained. Rabotnov (1969) has represented the function g(t) by the formula g(t) =

1

b

(18.5)

1 +at

and from experimental data has estimated that b = 0.3. Comparison of analytical and experimental creep results indicates that very small changes in stress produce a large change in creep rate and, consequently,the time required to achieve a particular strain. Small differences in microstructure or chemical composition of material specimens also greatly affect creep rate. Consequentfy, in experiments to determine the time required to attain a given creep strain at a fixed stress level, the scatter of results for a given set of specimens may be quite large. However, if we determine experimentally the stress at which a particular strain is reached in a given time, the scatter is small. On this basis, Rabotnov (1969) noted that there is some experimental evidence of accurately predicted creep deformation that confirms the similarity of isochronous creep curves (Eq. 18.4). However, much experimental evidence does not fully confirm Eq. 18.4. In some cases, similarity is clearly not valid, but if it exists, it can be used to simplify calculations.

18.4

ONE-DIMENSIONAL CREEP OF METALS SUBJECTED TO VARIABLE STRESS AND TEMPERATURE

18.4.3

635

Temperature Dependency

The effect of temperature on creep response may be summarized by noting that an increase in temperature results in an increase of creep rate. Hence, at a given stress level, a given strain is obtained more quickly at higher rather than at lower temperatures. In general, all creep parameters are affected by temperature. Consequently,a correlation of the temperature effects on the parameters that occur in the numerous creep equations that have been proposed (Table 18.1) is not feasible. Physical concepts are usually employed to predict the temperature dependence of creep curves (Evans and Wilshire, 1985; Cadek, 1988). The results have been reasonably successful. Formulas that have been used to predict the temperature dependency of creep curves of metals are listed in Table 18.1 [Eqs. (k) through ( s ) ] . Ordinarily, in practice, the temperature dependency of creep curves is required mainly for interpolation over a fairly narrow range of temperatures; extrapolation far outside of the range is not particularly important to the engineer. In general, it is reasonable to use a simple formula for temperature dependency, even though the formula may have no physical relationship to a physically based formula that requires complicated calculations.

18.4.4

Variable Stress and Temperature

The objective of elementary creep theory based on a phenomenological model is to determine the strain as a function of time, given stress and temperature as functions of time. By elementary, we mean theories that include all the results of one-dimensional creep tests at constant stress and temperature. Alternatively, the objective is to develop an equation or a system of equations that accurately relate measured values of stress, strain, temperature, and time. The form of the stress-strain-temperature-time creep relation may be chosen to fit only certain parts of the creep curve. For example, for a creep test in the secondary range of creep, the creep rate may be approximately constant for constant stress and temperature. If the creep test is run at a higher stress level, the creep rate increases. Thus, for constant-temperaturetests in the secondary range, the creep rate EC may be expressed as a function of stress level 0:

+ = €sc(o)

(18.6)

where EsC is the secondary-stage creep rate. Equation 18.6 is sometimes applied to creep of metals that undergo long-time use in which most of the creep occurs at a constant rate (see curve C ,, Figure 18.2), or to short-time creep at very high temperature and very high stress (curve C, Figure 18.2). The use of Eq. 18.6 ignores the primary and tertiary stages of creep (Figure 18.2). Hence, the creep deformation eC is approximated by straight lines (Figure 18.7). Creep models that employ Eq. 18.6 are called steady-state creep models. Steady-state creep models are incapable of describing relaxation phenomena, since they do not include unloading effects properly. There have been several modifications of steady-state models. For example, to allow for the effect of initial elastic deformation on steady-state creep, Soderberg (1936) proposed the equation

.

E

& E

.

= - + E S C ( 0)

(18.7)

where 6 is the total strain rate, 6 is the stress rate, gSc is the steady-state creep rate, and E is the modulus of elasticity. Equation 18.7 ignores primary creep. Experiments and the predictions of Eq. 18.7 do not ordinarily agree well, since the primary creep strain is often as large or larger than the elastic strain. Odqvist (1953)

636

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

FIGURE 18.7 Straight-line approximation of creep curves.

proposed an equation for steady-state creep that approximates the effect of elastic strain, instantaneous plastic strain, and primary creep on the secondary creep rate. It is (18.8)

where e0 is elastic strain plus instantaneous plastic strain plus primary stage creep, and the prime denotes derivative with respect to O.Equation 18.8 generally can be made to agree well with experimental creep curves. The creep model curve associated with Eq. 18.8 starts at time t = 0 and is a straight line, asymptotic to the steady-state creep curve (Figure 18.8). One may represent the creep curve for constant temperature as a relationship of the type

which is a general form of Eq. 18.1. It is tempting to assume that this relationship holds true when stress varies with time. However, on the basis of invariance relative to time, Eq. 18.9 leads to contradictions (Rabotnov, 1969). Models in which stress, strain, temperature, and time are related functionally as in Eqs. 18.1 and 18.9 are called aging (time) models. Since these models are applied mainly to primary and secondary ranges of creep and in these regions the creep rate decreases (i.e., the resistance to creep increases or the material hardens), they are also called time-hardening models. In a modified form of aging (time hardening), the creep strain rate ic is taken as a function of stress and time. In particular, in a form analogous to Eq. 18.9, the creep rate is taken as

FIGURE 18.8 Approximation of steady-state creep stage.

18.4

ONE-DIMENSIONAL CREEP OF METALS SUBJECTED TO VARIABLE STRESS AND TEMPERATURE

€c =

€---

b = f(o,t) E

637

(18.10)

The time-hardening model of Eq. 18.10 is more logically acceptablethan that of Eq. 18.9, since instantaneouschange in stress does not produce an instantaneouschange in creep straiq rather, it produces an instantaneous change in creep strain rate. Predictions based on the time-hardening model of Eq. 18.10 also agree well with experimentsfor small changes in stress levels. The time-hardening model of Eq. 18.10 is particularly easy to apply for similar creep curves (Eq. 18.1).Then,

€c = E.- - b = F ( o ) f ( t ) E

(18.11)

If we change the time scale and takefit) as the independent variable rather than t, we may write Eq. 18.11 in the form

(18.12) This form is particularly suited to the relaxation problem, since then E = constant (refer to the first paragraph in Section 18.3). For E = constant, Eq. 18.12 yields

(18.13) For thermally stable materials (i.e., for materials whose structure and properties do not change under prolonged exposure to test temperatures in the absence of load), it is natural to assume the existence of an equation of state that relates the creep rate to the applied stress and accumulated creep strain. Such an assumption uniquely relates the degree of strain hardening to the amount of plastic deformation in a manner analogous to the way that work hardening in the theory of plasticity is related to plastic deformation (Section 4.2). Thus, for a strain-hardeninghypothesis, the equation of state is represented as

F ( i C , o ,eC,T ) = 0

(18.14)

Equations of state were employed early in the study of plasticity (Ludwik, 1908; Nadai, 193 1). However, Davenport (1938) was one of the first to introduce the concept of strain hardening. Strain-hardening theory can be checked most simply by a creep test in which stepwise changes in stress are made (Pickel et al., 1971). Generally speaking, stepwise changes in stress (load) are easy to make. Also, theoretical predictions of various hardening theories show wider differences for stepwise loading than they do for relaxation tests. Consequently, stepwise loading tests serve as a better check on the accuracy of hardening models than relaxation tests (Boyle and Spence, 1983). For example, let us examine creep tests with a stepwise change in stress. To illustrate the differences between predictions of a time-hardening model and strain-hardening model, consider two creep curves for two stress levels: o1,02,and o1< o2(Figure 18.9). Assume that the creep curves can be represented by the relation E~ = aobtn (Eq. 18.2), a common representation of creep in the primary and secondary creep ranges for isothermal conditions. The creep rate form of this equation is b n-1

eC = n u 0 t

(1 8.15)

638

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

Equation 18.15 is a time-hardening model of the creep rate, since 0 < n < 1 and therefore the creep rate decreases (creep resistance hardens) with time. Equation 18.15 can be written in a form independent of time t by eliminating t between Eqs. 18.2 and 18.15; then,

.

EC =

nu

(l/n)

(b/n) 0 ( 1 - n)/n

(18.16)

Equation 18.16 indicates that the creep strain rate decreases (resistance to creep strain hardens) with increasing creep strain eC. Thus, Eq. 18.16 is called a strain-hardening model, since the hardening phase is modeled using the creep parameter ec. Time- and strain-hardening models can be developed similarly for more complex creep functions. Equations 18.15 and 18.16 give the same strain rate for constant stress. Let us assume that Eq. 18.2 can be applied to varying stress conditions, although it was developed for constant-stress states. For varying stress, we find that time and strain hardening give different creep rates. For example, let us subject a metal specimen first to stress ol. The creep is predicted by the lower curve in Figure 18.9. At time t = tlr let the stress level be increased instantaneously to 0,.Deleting the instantaneous elastic strain , find that the new creep curve leaves the o1creep curve (since we plot creep strain E ~ ) we at point P. Depending on the hardening model used, predictions for the new curve differ. For example, if the time-hardening model is used (Eq. 18.15), the creep rate at point P depends solely on the time tl and stress level 02. Hence, by the time-hardening model, the new creep curve will leave point P with a creep rate of curve 0,at time tl (point B) and continue parallel to BC of curve 0,.However, for a strain-hardening model, the new creep rate depends on the stress level o2 and accumulated creep eCA.Hence, by the strainhardening model, the new creep curve will leave point P with the creep rate of curve 0,at point A and will continue parallel to ABC of curve 0,.Thus, as observed in Figure 18.9, appreciable differences in the two predictions are apparent. Quite often, strain-hardeningmodels give more accurate predictions of experimental results for stepwise changes of stress. Unfortunately, strain-hardening models do not always yield accurate predictions, particularly when several step changes in stress occur in the same test (Rabotnov, 1969). Furthermore, the strain-hardening model is unable to

FIGURE 18.9 Models of creep hardening.

18.4

ONE-DIMENSIONAL CREEP OF METALS SUBJECTED TO VARIABLE STRESS AND TEMPERATURE

639

accurately predict behavior resulting from structural instabilities (Pickel et al., 1971). Nevertheless, for structurally stable metals, generally predictions by the strain-hardening model are fairly reliable and the model is relatively easy to use. Finally, the equation-of-state approach (Eq. 18.14) has been used by many authors to describe various processes in the behavior of metals. As in the theory of plasticity, it has been assumed that ec is the total plastic strain and ic is therefore the rate of plastic strain. If one accepts these assumptions, for a fixed temperature T, Eq. 18.4 may be considered a surface in space with coordinates ic, eC, and o;then the instantaneous plastic deformation curve should be given by the intersection of this surface with the plane ic = 00. Rabotnov (1969) has shown that this procedure is not generally valid, and the problem of instantaneous plastic strain must be solved by other means. Accordingly, the equation-ofstate approach to hardening (Eq. 18.14) is best suited to those situations involving structurally stable metals in which a predominant creep mechanism exists and in which only instantaneous elastic deformation o/Eexists. Then the total strain is E = o/E+ eC. See Evans and Wilshire (1985) for another approach to varying stress effects on creep that does not directly use either time- or strain-hardening models. A more general hardening hypothesis is that the creep rate depends on stress, temperature, and a number of parameters (pl, p 2 , ...,p N )that characterize the creep processes (Rabotnov, 1963).Then, Eq. 18.14 becomes F ( i C , o,T , pi) = 0 , i = 1 , 2 , ..., N

(18.17)

The time-hardening hypothesis is characterized by N = 1, p1 = t , and the strain-hardening hypothesis is given by N = 1, p1 = ec. By selecting N > 1 and different pi,other hardening models may be obtained (Taira, 1962). In applications, many special forms of Eqs. 18.14 or 18.17 have been used. In particular, analytical forms have been chosen to represent Eq. 18.14, with the objective of including the effect of the principal mechanism of creep. Often, the condition of similarity of creep curves is assumed. Then, for constant temperature, Eq. 18.14 is represented by (see Eq. 18.1)

(18.18) Iff is a power function of eC/S,we may write

i c = EC-P h ( o )

(18.19)

where p is a constant. Integration of Eq. 18.19 yields (Rabotnov, 1969, p. 210) EC

(18.20)

= g (o )t"

where II = 1/(1 + p). Various forms of g ( o ) have been used, for example, a power function b

g(0) = A D ,

b > -1 n

(18.21)

(9

(18.22)

or an exponential function g ( o ) = B exp

-

640

CHAPTER 18 CREEP: TIME-DEPENDENT DEFORMATION

Equation 18.22 is unsuitable for small values of stress, since g ( o ) must tend to zero as o goes to zero. An improvement, g(0) =

(1 8.23)

C[2shh(;)]b

was suggested by Garofalo (1963, but this expression is more complicated to use in practice. More generally, to adequately describe both the primary and secondary creep of metals, it is necessary to broaden Eq. 18.18 into the form

i, = m & o )

(18.24)

where H(+) behaves like E’; for small values of eC and tends to a constant for the secondary range of creep. Rabotnov (1969) suggests the form H(EC)

= EC-P

+c,

(1 8.25)

where C , is a constant. For p = 2, Eqs. 18.24 and 18.25 are equivalent to Andrade’s law in the primary range, since creep deformation is then proportional to the power of time [see Eq. (i), Table 18.11. Techniques for the experimental determination of the constants in creep equations, such as Eqs. 18.20-18.25, are discussed by Conway (1968) and by Evans and Wilshire (1985). The creep parameters A and b in Eq. 18.21 or B and c in Eq. 18.22 generally depend on temperature Z see, for example, Eq. (cc), Table 18.1. If the temperature range is sufficiently small, b (or c) is practically constant. However, A (or B) varies considerably with T. To express the effects of temperature T, the parameters A and B are often taken in the form

4

(1 8.26) where U is activation energy (Cadek, 1988) and R is the universal gas constant. Thus, a general form of the strain-hardening law that includes temperature effects is (18.27) wheref(o) and the parameter p are considered to be independent of temperature T.

18.5 CREEP UNDER MULTIAXIAL STATES OF STRESS 18.5.1

General Discussion

Most engineering systems (machines, structures, aircraft, etc.) operate under multiaxial stress conditions. Creep tests of members in such systems are very difficult and expensive to perform. In addition, a large amount of experimental and analytical data must be accumulated to make meaningful comparisons between experimental results and analytical predictions. Digital computer representations of analytical predictions in the form of field maps (Boresi and Sidebottom, 1972) or finite element programs overcome some of this difficulty by displaying the entire analytical calculation in a single diagram or map.

,

18.5

CREEP UNDER MULTIAXIAL STATES OF STRESS

641

Metallurgical models of multiaxial stress creep are lacking. Therefore, models of multiaxial creep are mainly phenomenological in form (Kraus, 1980; Boyle and Spence, 1983; Gooch and How, 1986). These models are based mainly on concepts from the theory of plasticity of metals at normal (room) temperatures, where time effects are negligible or absent. Multiaxial plasticity theories predict reasonably accurate results for proportional loading. However, for arbitrary loading paths, differences between experimental results and analybcal predictions may be considerable. In addition, experimental data do not absolutely indicate the validity of any particular theory of plasticity. Since the extension of a single plasticity theory to creep may proceed in several ways, the number of possible creep models is quite large. Fortunately, in a number of engineering creep problems, the stress state ordinarily varies slowly with time. Consequently,different creep models may predict rather similar results. The multiaxial creep problem is far more complex than the uniaxial case because one-dimensional quantities (scalars) must now be replaced by tensor quantities. Hence, instead of a single creep strain eC and strain rate i c ,now a creep strain tensor EC . . and ‘J creep strain rate tensor (i, j = 1, 2, 3) enter. Thus, the equation of state becomes a relationship among the creep strain rate tensor stress tensor oij,and hardening parameters that may be scalars or more generally tensors of any order. When the hardening parameters are scalars, the hardening is said to be isotropic. Engineering phenomenological models of multiaxial creep have been based primarily on isotropic hardening assumptions, even though predictions so obtained may, in some cases, disagree with experiments. The simplest case of multiaxial creep is that in which the stress state is homogeneous (constant from point to point) and constant with time. As expected, most available experimental results are for this case. From this basis, a number of methods are used to extend the analysis to nonhomogeneous stress states that vary with time. As already noted, however, the number of possibilities is much larger than in plasticity theory. Indeed, it is possible to describe a large number of creep models treating special effects such as steadystate creep (creep deformation rate constant with constant stress), creep with isotropic hardening, creep with anisotropic hardening, and so on. As noted in the discussion on one-dimensional creep theory (Section 18.3), it is difficult if not impossible to determine the end of the instantaneous deformation (elastic and plastic) and the beginning of creep deformation in a creep test. However, the error introduced into the analysis by this unknown is generally small. Likewise, it is not possible to distinguish precisely between the primary and secondary stages of creep. The determination of the transition from the primary to secondary stage of creep has been attempted in several ways. For example, in the one-dimensional case, it is often assumed that as creep deformation eC increases, the function H(+) in Eq. 18.24 tends to a definite limit that is attained either for a particular value of eC or as eC + 00 (Eq. 18.25). Another method based on metallurgical concepts is to assume that primary and secondary creep are controlled by different micromechanisms that coexist simultaneously,but independently. In this case, the total deformation at any time consists of the instantaneous strain e0 (elastic and plastic), primary creep strain ePc, and secondary creep strain eSc.The primary creep (transient creep) is described by an equation of state like Eq. 18.14,namely, GPc = Fp(o,eC,T ) , which dampens out with time so that gC + 0. Other elaborate schemes have been devised. Depending on the scheme employed for the transition from the primary to secondary stage of creep, the analysis may proceed by widely differing paths. In engineering problems, issues such as simplicity and convenience often dictate methods. On this basis, the first method noted above is used most frequently. Two cases of steady-state creep are prevalent. Under one set of conditions, strain hardening may be negligible from the initiation of loading. Under other conditions, the creep rate becomes constant only after some time as the material becomes fully strain

\$

€5,

642

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

hardened and cannot undergo further hardening as creep continues. For example, if the temperature and stress levels are sufficiently high (as in short-term creep tests), strain hardening is negligible. However, at relatively low temperatures, the creep rate may become constant only after long times, with steady-state creep being preceded by a period of strain hardening. The difference in responses in the two cases is clear under variable loading. If the material does not strain harden, the instantaneous creep rate depends only on the instantaneous stress. If steady-state creep is preceded by a transient (primary) period, when a step change in load is applied in the steady-state region, the steady-state creep rate does not change instantaneously to a new value, but rather the transient period of the creep curve is repeated (more or less), until finally after some time the creep rate is again constant (Figure 18.10). For creep under multiaxial states of stress, the effects of strain hardening are more important, since strain hardening may create anisotropy in the material relative to subsequent creep after a change in loading path. Consequently, in steady-state creep, as well as nonsteady creep, under multiaxial stress states, one must distinguish between conditions of isotropic and anisotropic behavior. These conditions are influenced by the initial state of the material, strain hardening or structural changes caused by instantaneous plastic creep (which may occur because of large instantaneous loads or because of creep if the stresses are nonuniform and become redistributed), and strain hardening that occurs in the transient creep phase. As previously noted, time-dependent inelastic theories for multiaxial states of stress are based on idealized models of material behavior. The models are similar to those used in the theory of plasticity (time-independent, inelastic behavior; Chapter 4). As noted in Section 4.3, the mathematical theory of plasticity is based on three postulates (assumptions):

1. There exists an initial yield state defined by a point on a yield surface specifying the states of stress for which plastic flow begins, the yield criterion. 2. There exists a rule relating the increment of the plastic state of strain to a specified increment in the state of stress, the flow rule. 3. There exists a rule specifying the modification of the yield surface during the course of the plastic flow, the hardening rule. In addition, it is often assumed that the yield surfaces are independent of hydrostatic states of stress. In the case of time-dependent deformation, the concept of a yield surface has no meaning. However, Drucker (1959) has pointed out that one may speak of surfaces @(ojj) = constant in stress space for both time-dependent and time-independent inelastic behavior.

fl

t

FIGURE 18-10 Creep curve for discontinuous stress change.

18.6

FLOW RULE FOR CREEP OF METALS SUBJECTED TO MULTIAXIAL STATES OF STRESS

643

For von Mises and Tresca materials, these surfaces correspond to the condition 4 = 0,= constant, where 0,denotes the effective stress (Section 4.3). For time-independent inelastic deformation, the surface CT, = constant is a yield surface. For time-dependent inelastic deformation, the surface CT, = constant is interpreted by Drucker as a surface along which the rate of dissipation of energy is a constant; that is, oekeC,where EeC = dee& is the effective creep strain rate defined by E.c , , - E .~c~ y

+ ( E. c~ ~ - .c)2 E , , + ( E. c, , - ~. c ~ ,y + 6 ( exy . c ) 2 + 6 (iyz C ) 2 + 6 (izx c y (18.28)

where here the superscript C denotes creep. The mathematical theory of inelasticity for time-dependent (creep) deformations, analogous to plasticity theory, is based on the following three conditions:

1. There exist surfaces for which @ = constant that are independent of hydrostatic states of stress. 2. There exists a rule relating keC to oe,temperature, and stress histories, the creep flow rule. 3. There exists a rule specifying the modification of the surface @ = constant during the process of inelastic deformation, the creep-hardening rule. Condition 1 is generally assumed valid for metals, and isotropic hardening is often assumed in condition 3. The flow rule (condition 2) for uniaxial states of stress is obtained from the tension test. However, for time-dependent inelastic deformation, even for the uniaxial case, the flow rule is not known precisely, since the strain rate is generally not only a function of stress and temperature but also of stress and temperature histories (Section 18.3). We consider the question of selection of a flow rule in Section 18.6.

18.6 FLOW RULE FOR CREEP OF METALS SUBJECTED TO MULTIAXIAL STATES OF STRESS The flow rule for multiaxial states of stress generally is based on the existence of a flow rule for the uniaxial state of stress (the tension test or the torsion test of a thin-wall circular cross section cylinder: see Chapter 4). Often, the multiaxial flow rule is obtained from the flow rule for tension specimens by replacing the tensile stress CT by the effective stress CT, (Chapter 4) and the tensile creep strain rate Gc by the effective creep strain EeC (Eq. 18.28). Since an equation of state does not truly exist for metals that creep, the flow rule is not known for the uniaxial state of stress. However, as discussed in Section 18.4, a number of approximate flow rules have been proposed. Most of them are based on a family of constant-stress creep curves obtained from tension specimens tested at the temperature of interest. If a temperature gradient is to be included in the analysis, a family of constantstress creep curves is obtained at each of two or more temperatures in the range of interest. The family of constant-stress creep curves is incorporated into the multiaxial flow rule in a number of different ways.

644

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

18.6.1 Steady-State Creep As noted in Section 18.5, in the case of multiaxial states of creep, the presence or absence of strain-hardening effects is most important. This is because strain hardening that results from creep or plastic deformation produces anisotropic changes in the material properties that alter subsequent time-dependent deformation (creep). The effects of anisotropy are well known in rolled members of steel or aluminum alloy. For example, the elastic properties of such members may vary 10% to 20% between the direction of rolling and the direction transverse to rolling. However, the creep rate in these directions, for a given stress and temperature, may vary by a factor of 2 or more. It has also been observed that the effects of anisotropy due to strain hardening during creep may cause even greater variations in the creep rate. If one wishes to describe multiaxial creep in the secondary stage of creep (steady-state creep stage), one must distinguish between isotropic and anisotropic creep. In particular, one must be aware that anisotropy may be produced by several effects; for example, anisotropy may be caused by the manufacturing process, strain hardening due to plastic deformation at the instant of loading, strain hardening due to plastic deformationcaused by changes in load during creep, or strain hardening that occurs in the primary stage of creep. Anisotropy may also arise in steady-state creep, if the creep is of sufficient duration and magnitude to result in structural (physical) changes in the metal. The effects of creep under anisotropic conditions lie outside the scope of our study here. However, it is a topic of research in metals and composites (Ohno, 1990; Pan, 1991; Sullivan, 1991). We restrict our discussion to isotropic creep in which the principal axes of stress and strain coincide during the creep process. We have seen in Chapters 2 and 3 that the general state of stress at any point in a body may be characterized by three principal stresses olr 02,and c3,in three mutually perpendicular principal stress directions (axes). Likewise, the state of strain at the point may be defined in terms of three principal strains el, e2,E ~ in, three mutually perpendicular principal strain directions (axes). For linear elastic isotropic material properties, the principal axes of stress and strain coincide (see Chapter 3). In terms of principal axes, the stress-strain relations of a linear elastic isotropic material may be written in the form 1

+ 03)3

€1

= E 4

€2

1 =E -[02-v(cJ3+061)] 1

0 1 - V(O2

€3 = E 403-

V(bl

(18.29)

+ 02)]

where E is the modulus of elasticity and v is Poisson’s ratio. In linear elastic theory, the history of loading is neglected. However, as noted previously, in inelastic deformations, such as plasticity and creep, the history of loading affects the deformations.Also, as noted in Section 18.5, it is therefore useful to employ creep strain-rate-stress relations in the study of creep deformation (see Eq. 18.28). In general, to derive a creep strain-rate-stress relation (flow rule) for creep problems, we employ the fact that the deformation in a creep process is largely inelastic. It has been noted experimentally that inelastic deformation does not involve volumetric changes; volumetric change is principally elastic in form. Accordingly, as in the theory of plasticity, we assume that the volumetric change caused by inelastic (creep) deformation is zero. The total volumetric strain is (Boresi and Chong, 2000)

18.6

FLOW RULE FOR CREEP OF METALS SUBJECTEDTO MULTIAXIAL STATES OF STRESS

e = i,+2i2+4T3

645

(18.30)

q,

where i2, and i3are the strain invariants (see Eq.2.80). For small strains, relative to principal axes, Eq. 18.30 may be approximated as -

e = Z l = e1+e2+e3

(18.31)

since i2 and i3are higher order terms in the principal strains (el, e2, E ~ ) We . may separate the strain into elastic and inelastic (creep) parts. Thus,

By Eq. 18.29,

With the assumption that the volume change due to creep is zero, the volumetric creep strain is zero; that is, (El

+ E 2 + E 3Icreep

= E1C + E2C + E3C = O

(18.34)

where the subscript C denotes creep strain. For isotropic creep deformation in which the stress distribution does not change with time, it follows that the principal axes of stress and strain remain coincident and do not rotate during the creep deformation. Then, we can differentiate Eq. 18.34 with respect to time to obtain € l c + € 2 c + € 3=c 0

(18.35)

as the condition of constant volume under creep deformation. Although Eq. 18.35 has been obtained on the basis that the principal strain directions do not rotate, it also gives good results in certain cases in which the principal strain directions do rotate (see Pickel et al., 1971, where solid circular bars of SAE 1035 steel were tested in torsion). A second assumption, analogous to that used in plasticity theory (see Lubahn and Felgar, 1961, Chapter 8), is that the maximum shear strain rates [i.e., E j j = ( E i - kj)/2] are proportional to the maximum shear stresses (see Eq. 4.14). Thus, we write E1c-E2c 01-02

-

E2c-E3c 02-03

- E3C-ElC -

= C(X,y,z,t)

(18.36)

03-01

where C(x, y, z, t ) is a function of location (x, y, z ) in the body and time t. For steady-state creep, C(x,y, z , 2) + C(x,y, z); that is, C remains constant in time. In transient creep, C will change with time, since the creep strain rates change with time. Solving Eqs. 18.35 and 18.36 for EIC, 22c, and E3C, we obtain

(18.37)

646

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

To determine the parameter C, the creep behavior of the material must be known for given strain rates and stresses. For this purpose, we employ concepts analogous to plasticity theory (Section 4.3) and define an effective stress, an effective strain, and an effective strain rate. First, we note that the yielding of many metals has been shown to be predicted by either the Tresca (Eq. 4.12) or von Mises criterion (Eq. 4.22). Accordingly, say, for the von Mises criterion, we write for the effective stress (see Eq. 4.23) (18.38) where superscript M denotes von Mises. Similarly, for the effective strain and effective strain rate, we write (18.39) and (18.40) Returning to the case of steady-state creep, we consider a structural member subjected to constant stress and constant temperature for a long period of time. If the deformations are sufficiently small to preclude tertiary creep, the creep deformation-time diagram for the member corresponds approximately to the solid curve in Figure 18.1 1. The instantaneous deformation OA may be entirely elastic or partly elastic and partly plastic. The primary creep range AB is followed by the secondary (steady-state) creep range BC. For long times and for a relatively brief period of primary creep, it may be sufficiently accurate to approximate the steady-state creep deformation by the dashed straight line OS (taken parallel to line DBC). In derivations of a steady-state creep theory based on the straight line

FIGURE 18.11 Deformation-time diagram: OA = instantaneous deformation; AB = primary stage; BC= secondary stage; 0s= straight-line approximation ignoring OD; DBC= Odqvist approximation of ABC.

18.6

FLOW RULE FOR CREEP OF METALS SUBJECTEDTO MULTIAXIAL STATES OF STRESS

647

OS, the temperature and stress components of each volume element in the member are usu-

ally assumed to remain constant with time. Since the primary creep effect is neglected, the flow rule is given by a relation that approximatesthe creep strain rate for steady-state conditions. Then, for a given temperature, the creep rate is a function of stress only, and the flow rule takes the form (see Eq. 18.6) M E'eC

(18.41)

= F(oe) -

.

Several relations have been proposed for the function F [see Eqs. (t) through (aa), Table 18.1). A widely used formula proposed by Bailey (1935) is

(18.42) Equation 18.42 has the merit that it is simple to use. The factor l/& in Eq. 18.38 is such that .M = ilc in a simple tension test with stress o1and strain rate C,,, we have o!= o1and by Eq. 18.40, since C2, = C3, = -(1/2)ClC by Eq. 18.37. Then, by the first of Eqs. M M M M 18.37 and Eq. 18.41, we obtain ,C = 2Cae /3, or C = 3deC/(2oe ).With this value of C and Eq. 18.42, we can write Eq. 18.37 in the form (flow rule)

( 18.43)

Alternatively, if we take the Tresca yield criterion, the effective stress and effective strain rate are defined as (see Eq. 4.14 with o1> o2> 03)

(18.44) where superscript T denotes Tresca. Then, in place of Eq. 18.43, we have

( 18.45)

.T_

i3 = , l3 % [ , - -(01 1 +411 T 2 Oe

In cases where the order o1> o2> o3is retained during loading, Eq. 18.45 may be easier to use than Eq. 18.43; see Finnie and Heller (1959, Section 7.3) for a discussion of the differences between the results predicted by Eqs. 18.43 and 18.45.

648

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

18.6.2

Multiaxial creep models have been used to predict stresses or deformations of structural members subjected to prescribed stress or deformation histories and to prescribed temperature histories, including temperature gradients. Often, the flow rule for these problems is based on an equation that approximates a family of constant-stress creep curves, if only one temperature is considered, or that approximates families of constant-stress creep curves over a range of temperatures. As a generalization of Eq. 18.27, the flow rule takes the form [see also Eqs. (bb) through (gg), Table 18.11 EeC =

F ( o e )G('a) 4( t )

(18.46)

where F(o,), G(T,), and \$(t) are functions of effective stress o,,absolute temperature T,, and time t, respectively. A number of investigators have used the form [see Eqs. (x) and (cc), Table 18.11 (18.47)

where B, n,A, and k are material constants.Frequently, better accuracy is obtained by replacing o: by (sinh boan,where b is an additionalmaterial constant [see Eq.(ee). Table 18.11. Forms such as Eq. 18.47 are ordinarily used for constant stress and temperature conis ditions. The effect of varying stress or temperature on the effective strain rate iec included in the creep model by the introduction of a hardening rule. As noted in Section 18.4, two hardening rules, the time-hardening and strain-hardening (see Eqs. 18.15 and 18.16) concepts, are commonly used. The time-hardening rule assumes that the creep strain rate ic depends on stress, temperature, and time. With the time-hardening rule, the creep strain rate is obtained by taking the time derivative of Eq. 18.46. For the specific form of Eq. 18.47, we have

dec = kBoen[ e- A / T a l t ( k -

1)

(18.48)

The strain-hardening rule states that ic depends on stress, temperature, and strain. The strain-hardening form is obtained by eliminating time between Eqs. 18.47 and 18.48. Thus, we get l/k

(kdec = k{ B ~ z [ e - ~ ' ~ ~eC ]}

l)/k

(18.49)

Numerous applications of time- and strain-hardeningflow rules have been given in the literature (Rabotnov, 1969; Boresi and Sidebottom, 1972; Kraus, 1980; Boyle and Spence, 1983). Because of the complexity of 'the creep problem, approximate solutions are obtained by numerical techniques, such as iteration methods (e.g., successive elastic solutions) and finite element methods (Zienkiewicz and Taylor, 2000). Boresi and Sidebottom (1972) have given several comparisonsof multiaxial flow rules by the method of successive elastic solutions. Relatively few problems in creep analysis admit closed-form solutions. One such problem is the steady-state creep of a thick cylinder; other cases include the problem of the steady-state, small-strain creep of an infinite rectangular plate with a small circular hole (see Section 14.2) and certain steady-state creep problems in the membrane theory of shells (Kraus, 1980, Chapter 3; Boyle and Spence, 1983, Chapter 4).

18.7

AN APPLICATION OF CREEP OF METALS

649

18.7 AN APPLICATION OF CREEP OF METALS One of the simplest problems for which a closed-form solution of creep is possible is that of a thin-wall metal tube with closed ends, subjected to constant internal pressure and temperature (see Chapter 11). By equilibrium, the stresses in the radial, circumferential,and axial directions are

(18.50) where r is the inner radius of the tube, h is the tube wall thickness, and (r, 8, z ) refer to the radial, circumferential, and axial directions, respectively. For small strains, the stresses remain constant for constant pressure, since the changes in geometry are negligible. Consider a Tresca material. Then, if we use the time-hardening formulation given by Eq. 18.48, we get

iTC = kB(o:y[e

- A / T , I t(k-I)

(18.51)

Also, by Eqs. 18.50 and the first of Eqs. 18.44, we have

By Eqs. 18.45, 18.51, and 18.52, we obtain m

€2,

=

€zr,

=0

(18.53)

m

.1

i3, = krrC =

-!-(-) pr 2 T h ‘eC

= - ?1k B E y [ e

- A / T , It(k-I)

Oe

As a result, we see that the tube grows radially in diameter but maintains its length. Considering the radial displacement caused by creep, uc = reeec, we have t

(18.54)

uC = rEeeC = r/€geCdT 0

If we assume that initial strain is entirely elastic, the total radial displacement is u = uelastic + uc, where uelasticis given by Hooke’s law (Eq. 18.29) ‘elastic

-

2

r

- reeeelastic = E[Cee-

v(0zz

+

err)] = ~ ( 1 - z ) V

(18.55)

Hence, the total radial displacement is, after carrying out the integration of Eq. 18.54,

(18.56)

650

CHAF'TER 18 CREEP TIME-DEPENDENT DEFORMATION

18.7.1 Summary T Since 0 < k < 1, the creep rate iec + 0 as time t becomes large (see E!q. 18.51). The radial displacement u continues to increase with time, and the circumference of the tube increases. Since the volumetric change is zero, the thickness of the tube decreases.

18.8 CREEP OF NONMETALS Under appropriate conditions, most materials will creep. For example, nonmetallic materials such as glass, polymers, Portland cement paste, and so on, creep when subjected to sufficiently high temperatures and stresses. As pointed out by Finnie and Heller (1959), the mechanical behavior of many nonmetallic materials during creep is somewhat simpler than that of metals. This has been attributed to the fact that nonmetallic materials like glass, polymers, and cements are more nearly isotropic than metals and large creep strains are required to induce anisotropy in them. The creep of glass and polymers is often treated by the theory of linear viscoelasticity.The creep behavior of other nonmetals, such as concrete, asphalt, and wood, is very complex. Nevertheless, one of the first applications of the theory of linear viscoelasticity was in the study of creep in concrete (Rabotnov, 1969). Concrete is a material that undergoes an aging process, such that under sustained load the modulus of elasticity changes with time. Generally, the properties of concrete depend on its age; that is, property changes occur that are independent of deformation. Aging is a phenomenon that alters creep of concrete. It is caused mainly by cement hydration, a process that continues for a long time after the initial hardening period. Because aging changes the rate of creep, it must be accounted for, thereby increasing the difficulty of predicting the creep behavior of concrete. Aging effects have been discussed by Bazant (1977) and Bazant and Prasannan (1989a,b). Asphalt, a widely used pavement material, acts much like a viscoelastic material. However, the creep behavior of asphalt resembles that of concrete. In the following, we give a brief description of the creep behavior of asphalt, concrete, and wood.

18.8.1 Asphalt The early work of Van der Poel(1954) discusses asphaltic mixtures and their applications to road design and lists a large number of references. More recently, Bollc (1981) p u b lished a manual on the creep test, which summarizes much of the work on the creep of asphalt conducted by The Netherlands Government Highway Engineering Laboratory. In this study, the representation of creep behavior was examined from the viewpoint that asphalt possesses elastic, viscous, and plastic properties dependent on the temperature and duration of loads. At low temperatures and/or for short duration of load, asphalt behaves in an almost linear elastic manner. At high temperatures and/or long duration of loads, asphalt responds in a viscous manner. Asphalt responds plastically at high levels of loads or under localized high stress (even at low loads). Consequently,rheological modeling is employed (Hills, 1973) and, for theoretical analyses, the various rheological components are assumed to be independent of one another. In a test, it is difficult, if not impossible, to separate the measured deformation into its rheological components. Also, in creep tests, deformation behavior over long periods of time is of primary interest. Nevertheless, the permanent deformation (the deformation that remains after reversible deformation is recovered see Monismith and Tayeboli, 1988) of asphalt is composed of viscous, plastic, and viscoplastic components.These effects change in importance with the duration of load

18.8

CREEP OF NONMETALS

65 1

and temperature. For example, during a creep test of asphalt, the binder film that exists between mineral particles becomes thinner. As a result, mineral particle-to-particle contact gradually occurs. Because these particles are relatively dry, the shear force required to maintain a shear strain rate gradually increases; that is, the asphalt appears to strain harden (Prendergast, 1992). Ordinarily, creep tests are performed in a temperature range for which asphalt does not behave as a purely viscous material, and in these tests, the viscous component of deformation is nonlinear in time. Thus, even in a well-controlled creep test, the separation of the permanent deformation of asphalt into various linear rheological components is not feasible. Consequently, in practice, a phenomenological approach is taken, much as in the case of metals (Bolk, 1981). However, the material constants in the creep rate equations exhibit a stronger dependency on temperature and time than they do for metals (see Table 18.1). The relation of creep to the engineering properties of asphalt (e.g., rutting of pavements, total deformation, strength) has been examined extensively (see, e.g., Bolk, 1981; Monismith and Tayeboli, 1988; Eckmann, 1989). Bolk (1981) has concluded that the correlation between the deformation measured in a creep test and that measured in a rutting test of asphalt hardly changes when the permanent strain in the flow rule is replaced by the total strain measured in the creep test. Hence, for practical purposes, it is sufficient to measure only total strain. The measurement of the reversible strain is therefore optional. Bolk (1981) concluded that the creep test is a valuable tool for prediction of engineering properties, such as rutting of asphalt pavements. He also gives recommendations for conducting uniaxial static creep tests with asphalt test specimens and recommends the logarithmic flow rule, E = A + B log t, where A and B are material constants determined by the tests. A relatively low value of B indicates low viscous behavior; a high value of B suggests mainly viscous behavior.

18.8.2

Concrete

The creep of concrete is affected by many factors. For example, water-reducing admixtures tend to increase creep rates, as do retarding admixtures and accelerating admixtures (Mindess and Young, 1981). Many other experimental variables affect the creep of concrete, for example, paste parameters (porosity, age, etc.), concrete parameters (aggregate stiffness, aggregatekement content, volume to surface ratio), and environmental parameters (applied stress, duration of load, humidity, etc.). Usually, the creep of concrete is influenced more by paste properties, since the aggregate tends to retard creep rate. Since creep data on paste are limited, creep data on concrete are relied on to assess the influence of various parameters. Concrete is often treated as an isotropic material, and creep flow formulas similar to those of metals are used to represent concrete creep. For example, creep dependence on stress and temperature is often represented by the formula

RT

(18.57)

where C is a constant, V is the activation volume, R is the universal gas constant, and T is the absolute temperature [see Eq. (z), Table 18.11. Equation 18.57 has been used with success to represent experimental data. Since the parameter VoIRT is generally small, the creep strain-stress-temperature relation is approximately linear in the stress range ordinarily used in concrete. From a practical viewpoint, the creep strain-stress relation in concrete is commonly taken to be

652

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATION

EC

= Cpo

(18.58)

where (J is called the specifrc creep. The concept of specific creep is useful for comparing the creep of different concrete specimens at different stress levels. A typical value of Cp is approximately 150 p/MPa (where p = lo4). Although Eqs. 18.57 and 18.58 are both frequently used to estimate creep in concrete, many empirical equations (some simple, some complex) have been used to predict creep in concrete. These equations are used in the same manner as for metal creep. There is considerable disagreement regarding a specific equation to represent different aspects of concrete creep, because of the difficulty in separating effects such as shrinkage from the more conventional effects. Nevertheless, under the assumption that the initial instantaneous strain, creep strain, and shrinkage strain are independent and additive, the American Concrete Institute (ACI, 1991) has developed a simplified creep equation of the form

(18.59) where t denotes time, B is a constant that depends on the age of the concrete before loading (B is taken to be 10 when the concrete is more than 7 days old before loading), and Cult is the ultimate creep coefficient. The value of Cultis difficult to determine, as it may vary considerably (for 40% relative humidity C,,, may range between 1.30 and 4.5). ACI recommends a value of Cdt = 2.35, if experimental data are not available. ACI also recommends certain correction factors to adjust Cultfor different conditions of humidity and age at loading. The interested reader is referred to the ACI Manual of Concrete Practice (ACI, 2000) for details.

18.8.3

Wood

Hearmon (1954)gave one of the early reviews of creep data of wood up to 1953. Bodig and Jayne (1982) wrote a comprehensive treatise on the mechanics of wood and wood composites. They approached the creep of wood from a rheological (flow) point of view, as a study of the time-dependent stress-strain behavior of materials. Since wood is highly anisotropic, the magnitude of creep strain depends on a large number of factors. The most critical conditions include the alignment of the orthotropic axes of wood relative to the load, the magnitude and type of stress, the rate of load, the duration of load, moisture content, and temperature. There are many practical situations in which the creep of wood is particularly important: for example, the deflection of wood beams and other types of loadcarrying wood members under long durations of load; the reduction of pressure between layers of glulam members due to creep relaxation, resulting in loss of bonding; and creep rupture of wood members at sustained loads less than the ultimate static load. In spite of the complexity of wood, many of the same concepts employed in the study of creep in metals are used, and the study of creep in wood rests heavily on curve-fitting of experimental data to obtain approximate flow rules. Because of the nature of the manufacturing process of wood composites, creep relaxation may strongly affect the serviceability of wood composites (Bodig and Jayne, 1982). In contrast to creep models of metals that are described in terms of three stages of creep, Bodig and Jayne consider the total creep deformation to consist of elastic and viscoelastic parts. For example, consider a tension specimen subjected to an instantaneously applied load P at time to (Figure 18.12). The deformation at some later time tl is taken to be

18.8

CREEP OF NONMETALS

653

FIGURE 18.12 Creep curve for wood. ( a )Load-time function. ( b )Componentsof creep.

where 6, is the instantaneous elastic deformation caused by the instantaneous application of load, ade is a delayed elastic deformation, and 6, is a viscous component. To determine the delayed elastic part, one imagines that the load is instantaneously reduced to zero at time t2. Then, the elastic deformation 6, is instantaneously recovered. As time continues, additional deformation is recovered (Figure 18.12). Since the process of recovery is irreversible, a residual deformation remains. The nonrecoverable (viscous) deformation developed to time t2 is 6,. At time t2, the total deformation is S2.It consists of the viscous deformation 6, and the delayed elastic deformation 6de. For a particular time t > t2, 6, can be obtained from the data (Figure 18.12). Therefore, (18.61)

Tests show that, for many wood composites, 6, increases linearly with time. By subtracting the viscous contribution from the total deformation-time curve, the delayed elastic component can be determined. Guided by this simplistic one-dimensional model and employing linear rheological models (e.g., linear viscoelastic models, namely, the Maxwell body, Kelvin body, and Burger body), Bodig and Jayne (1982, Section 5.4) derived creep formulas that are the synthesis of linear viscoelastic models and experimental data. For example, for a beam made of a flakeboard-veneercomposite, they derived the straintime relation -t/ 1.2557

5.48

+I) 72.37

(18.62)

where CT is in lb/in.' and t is in hours. Note that the first term is the instantaneous elastic strain, the second term is the delayed elastic strain, and the third term is the viscous strain (see Eq. 18.59). A similar approach for a multiaxial stress state may be carried out following the concepts presented in Section 18.6.

654

CHAPTER 18 CREEP TIME-DEPENDENT DEFORMATlON

REFERENCES AMERICANCONCRETE INSTITUTE (ACI) (2000). Manual of Concrete Practice, Part I: Materials and General Properties of Concrete. Detroit, MI. AMERICAN SOCIETY FOR METALS (ASM) (1976). Metals Handbook; Failure Analysis and Prevention, Vol. 10, p. 249. Metals Park, OH. AMERICAN SOcIETV FOR TESTING AND MATERIALS (ASTM) (1959). Effects of Nonsteady Load and Temperature Conditions on the Creep of Metals, STP 260. Philadelphia. ASTM (1965). Literature Survey on Creep Damage in Metals, STP 391. Philadelphia. ASTM (1983). Recommended Practice for Conducting Creep, CreepRupture and Stress-Rupture Tests of Metallic Materials, Std. E139. Philadelphia. ANDRADE, E. N. DA C. (1910). The Viscous Flow in Metals and Allied Phenomena. Proc. Roy. SOC.Ser. A, 84: 1. BAILEY, R. W. (1935). The Utilization of Creep Test Data in Engineering Design. Proc. Inst. Mech. Eng., 131: 131. Z. P. (1977). Viscoelasticityof SolidifyingPorous MaterialBAZANT, Concrete. J. Eng. Mech., ASCE, 103(6): 1W9-1067. Z. P., and PRASANNAN, S. (1989a). Solidification Theory for BAZANT, Concrete Creep I: Foundation. J. Eng. Mech.,ASCE, 115(8): 16911703. S. (1989b), Solidification Theory for BAZANT,Z. P., and PRASANNAN, Concrete Creep II: Verification and Application. J. Eng. Mech. ASCE, 115(8): 1704-1725. BERNASCONI, G., and P I A m , G. (Eds.) (1979). Creep of Engineering Materials and Structures. Essex, England Elsevier. BODIG,J., and JAYNE,B. A. (1982). Mechanics of Wood and Wood Composites. New York Van Nostrand Reinhold. BOLK,IR. H. J. N. (1981). The Creep Test. The Netherlznds: Study Center for Road Construction. Amsterdam. BORES, A. P., and CHONG,K. P. (2000). Elasticity in Engineering Mechanics, 2nd ed. New York Wiley-Interscience. BORES],A. P., and SIDEBOTTOM,0. M. (1972). Creep of Metals under Multiaxial States of Stress. In?.J. Nucl. Eng. Design, 18:415-456. BOYLE,J. T., and SPENCE,J. (1983). Stress Analysis for Creep. London: Buttenvorth. BRITISHSTANDARD INSTITUTE (BSI) (1987). Methods for Creep and Rupture Testing of Metals, Tensile Creep Testing, BS3500, Part 6.

London. CADEK,J. (1988). Creep in Metallic Materials. New York Elsevier. CONWAY, J. B. (1968). Numerical Methods for Creep and Rupture Analysis. New York Gordon and Breach. CONWAY, J. B. (1969). Stress-RuptureParameters: Origin, Calculation and Use. New York: Gordon and Breach. I. (ed.) (1988). Mechanical Testing. London: Inst. of CURBISHLEY, Metals. DAVENPORT, C. C. (1938). Correlation of Creep and Relaxation Properties of Copper. J.Appl. Mech., 60:A55460. DE LACOMBE, J. (1939). A Method of Representing Creep Curves. Rev. Metallurgy, 36: 178. DORN,J. E. (1962). Progress in Understanding High-Temperature Creep, H. W. Gillet Mem. Lecture. Philadelphia: ASTM. DRUCKER, D. C. (1959). A Definition of Stable Inelastic Material. J. Appl. Mech. Trans. ASME, 81: 101-106. ECKMANN, B. (1989). Exxon Research in Pavement Design-Moebius Software: A Case Study Reduction of Creep through Polymer Modification. Proc. Assoc. Asphalt Paving Technologist, 58: 337-361.

EVANS, R., and WILSHIRE, B. (1985). Creep of Metals and Alloys. London: Inst. of Metals. FELTHAM, P. (1953). The Plastic Flow of Iron and Plain Carbon Steels above the A3-Point. Proc. Phys. SOC.,London, 66: 865. FINNIE,I., and HELLER, W. R. (1959). Creep of Engineering Materials. New York McGraw-Hill. FREUNDENTHAL, A. M. (1936). Theory of Wide-Span Arches in Concrete and Reinforced Concrete. Int. Assoc. Bridge struct. Eng., 4 249. GAROFALO, F. (1965). Fundamental of Creep and Creep Rupture in Metals. New York: Macmillan. GOOCH, D. J., and HOW, I. M. (eds.) (1986). Techniquesfor Multiaxial Creep Testing. New York: Elsevier. GRAHAM, A. (1953). The Phenomenological Method in Rheology. Researcht, 6 92. GRAHAM, A., and WALLES,K. F. A. (1955). Relations between Long and Short Time Properties of a Commercial Alloy. J. Iron Steel Inst., 1 7 9 105-120. GRAY,T. G. F. (1988). Tensile Testing. In Mechanical Testing (I. Curbishley, Ed.), Chapter 1. London: Inst. of Metals. HEARMON, R. F. S. (1954). Wood. In Building Materials, Their Elasticity and Inelasticity (M. Reiner, Ed.), Chapter 5. Amsterdam: North Holland. HILLS, J. F. (1973). The Creep of Asphalt Mixes. J. Inst. Petrol., 59(570): 247-262. HULT,I. (1966). Creep in Engineering Structures. Waltham, MA: Blaisdell Publ. INTERNATIONAL STANDARDS ORGANIZATTON (ISO) (1987). Metallic Material+Ver\$cations of Extensometers Used in Uniaxial Testing. Geneva, Switzerland DIS 95 13. KACHANOV,L. M. (1960). Theory of Creep. London: UK Natl. Lending Library for Sci. and Technol. (Translation 1967). KANTER, J. (1938). Problem of Temperature Coefficient of Tensile Creep Rate. Trans.AIME, 131:385-418. KENNEDY,A. J. (1962). Creep and Stress Relaxation in Metals. London: Oliver and Boyd. KRAUS,H. (1980). Creep Analysis. New York Wiley. LARSON, F. R., and MILLER,J. (1952). A Time-Temperature Relationship for Rupture and Creep Stresses. Trans.ASME, 7 4 765. LOVEDAY, M. S. (1988). Creep Testing. In Mechanical Testing (I. Curbishley, Ed.), Chapter 2. London: Inst. of Metals. LUBAHN, J. D., and FELGAR, R. P. (1961). Plasricity and Creep of Metals. New York Wiley. LUDWIK,P. (1908). Elemente a'er TechnologischenMechanik. Berlin: Springer-Verlag. MANSON, S . S., and HAFERD,A. M. (1953). A Linear Time-Dependent Relation for Engineering Creep and Stress Rupture Data. NACA Tech. Note 2890. Washington, Dc:NACA. M c V m , P. G. (1934). Working Stresses for High Temperature Service. Mech. Eng., 56: 149. MCVEITY,P. G. (1943). Creep of Metals at Elevated TemperaturesThe Hyperbolic Sine Relation between Stress and Creep Rate. Trans.ASME, 65: 761. MINDESS,S., and YOUNG,J. F. (1981). Concrete. Englewood Cliffs, N J Prentice Hall. MONISMITH, C. L., and TAYEBOLI, A. A. (1988). Permanent Deformation (Rutting) Considerations in Asphalt Concrete Pavement Sections. Proc. Assoc. Asphalt Paving Technologists, 5 7 414-463.

REFERENCES

MOW, N. F. (1953). A Theory of Work-Hardeningof Metals II. Philos. Mag., 44: 742. MOW, N. F., and NABARRO, F. R. N. (1948). Dislocation Theory and Transient Creep: Report on a Conference on the Strength of Solids. Proc. Phys. SOC.,London, Series B, 64: 1-19. NADAI,A. (1931). Plasticity. New York McGraw-Hill. NORTON,F. H. (1929). The Creep of Steel at High Temperature. New York McGraw-Hill. ODQVIST,F. K. G. (1953). Influence of Primary Creep on Stresses in Structural Parts. Teckniska Hogskdam--Handlingar, Stockholm. 66: 18. ODQVIST,F. K. G. (1966). Mathematical Theory of Creep and Creep Rupture, 2nd ed. (1974). London: Clarendon Press. ODQVIST,F. K. G., and HULT,J. (1962). Creep Strength of Metallic Structures. Berlin: Springer-Verlag(in German). OHNO,N. (1990). Recent Topics in Constitutive Modeling of Cyclic Plasticity and Viscoplasticity.Appl. Mech. Rev., 43( 11): 283-295. PAN,T.-Y. (1991). Thermal Cycling Induced Plastic Deformation in Solder Joints-Part 1: Accumulated Deformation in Surface Mount Joints. J. Elec. Packaging, Trans. ASME, 113(1): 8-15. PENNY, R. K.,and MARRIOW,D. L. (1971). Design for Creep. New York: McGraw-Hill. PHILLIPS,F.(1905). The Slow Stretch in India Rubber, Glass and Metal Wire When Subjected to a Constant Pull. Philos. Mag., 9: 513. PICKEL,T. W., JR., SIDEBOWOM, 0. M., and BORESI,A. P. (1971). Evaluation of Creep Laws and Flow Criteria for lbo Metals Subjected to Stepped Load and Temperature Changes. Exper. Mech., ll(5): 202-209. PRENDERGAST, J. (1992). A European Road Comes to the U.S.Civil Eng., 62(5): 52-54.

655

RABOTNOV, Yu. N. (1963). On the Equations of State of Creep. Proc. Joint. Int. Con\$ Creep, 2: 117-122. RABOTNOV, Yu. N. (1969). Creep Problems in Structural Members. Amsterdam: North-Holland. ROBINSON, E. L. (1943). 100,000 Hour Creep Test. Mech. Eng. 65(3): 166-168. SMITH, C. L. (1948). A Theory of Transient Creep in Metals. Proc. Phys. Soc., Series B, London, 61: 201-205. SODERBERG, C. R. (1936). The Interpretation of Creep Tests for Machine Design. Trans. ASME, 58(8): 733-743. STOWELL, E. 2. (1957). Phenomenological Relation between Stress, Strain, and Temperature for Metals at Elevated Temperatures. Washington, DC:NACA, Tech. Note 4000. J. L. (1991). Measurements of Composite Creep. Exper. SULLIVAN, Mech., lS(5): 32-37. TAIRA,S. (1962). Lifetime of StructuresSubjected to Varying Load and Temperature. In Creep in Structures (N. J. Hoff, Ed.), pp. 96-124. Berlin: Springer-Verlag. VANDER POEL,C. (1954). Road Asphalt. In Building Materials, Their Elasticity and Inelasticity (M. Reiner, Ed.), Chapter 9. Amsterdam: North-Holland. VICAT,L. J. (1834). Note sur I’allongemontprogressif du fil de fer soumis A diverses tensions. Ann. ponts et chausies, Mem. et Doc. 7(l): 40. WARREN,J. W. L. (1967). A Survey of the Mechanics of Uniaxial Creep Deformation of Metals. London: Aero. Res. Council. WYAW, 0. H. (1953). Transient Creep in Pure Metals. Proc. Phys. SOC.,London, Series B, 66: 459. 0. C. and TAYLOR,R. L. (2000). The Finite Element ZIENKIEWICZ, Method, 5th ed. Oxford Buttenvorth-Heinemann.

APPENDIX

A

AVERAGE MECHANICAL PROPERTIES OF SELECTED MATERIALS

657

658

APPENDIX A AVERAGE MECHANICALPROPERTIESOF SELECTED MATERIALS

TABLE A.1

Properties in S.I. Units

Material

Density [103kg/m31

Yield

Ultimate

Poisson,s

stress [MPal

stress [MPal

ratio

Young's modulus [GPal

Percent elongation at rupture

Thermal coefficient [104PCl

STEEL Structural, ASTM A36 AISI-C 1018, cold drawn AISI-C 1030, normalized AISI-C 1040, normalized AISI-C 1080, normalized AISI-3140, normalized AISI-4340, normalized AlSl301 Stainless, annealed AlSl301 Stainless, half hard

7.85 7.85 7.85 7.85 7.85 7.85 7.8 7.92 7.92

250 370 340 390 520 620 860 280 760

400 440 530 590 1010 900 1310 760 1030

0.29 0.29 0.29 0.29 0.29 0.29 0.29 0.27 0.27

200 200 200 200 200 200 200 193 193

30 15 30 28 11 19 12 60 15

11.7 11.7 11.7 11.7 11.7 11.7 11.7 17.3 17.3

CAST IRON Gray, Class 30 (tension) Gray, Class 30 (compression) Gray, Class 40 (tension) Gray, Class 40 (compression)

7.21 7.21 7.21 7.21

-

210 510 410 990

0.20 0.20 0.20 0.20

103 103 138 138

nil nil nil nil

12.1 12.1 12.1 12.1

ALUMINUM ALLOYS 1100-H12 2024 T4 6061 T6 6063 T5 7075 T6

2.71 2.77 2.7 2.7 2.77

103 320 275 145 500

110 470 310 185 570

0.33 0.33 0.33 0.33 0.33

25 19 12 12 11

23.5 22.5 23.6 23.4 22.5

COPPER ALLOYS Free-Cutting Copper, soft Free-Cutting Copper, hard Yellow Brass, annealed Yellow Brass, half hard Commercial Bronze, annealed Commercial Bronze, half hard

8.91 8.91 8.43 8.43 8.84 8.84

62 290 117 340 90 280

220 320 340 420 270 330

0.35 0.35 0.35 0.35 0.35 0.35

117 117 105 105 110 110

42 12 60 23 45 25

17.6 17.6 20.0 20.0 18.0 18.0

TITANIUM Alloy Ti-AI-V

4.54

890

930

0.33

114

12

9.5

TIMBER (12% MC) Coastal Douglas Fir (bending) Loblolly Pine (bending) White Oak (bending)

0.48 0.51 0.68

-

85 88 105

2.32

-

28

CONCRETE Medium Strength (compression) aParallel to the grain.

-

70.0 74.5 69.0 69.0 72.0

-

13.4 12.3 12.3

0.15

25.0

-

-

3.1-4.5' 3.1-4.5' 3.1-4.5=

-

9.9

659 TABLE A.2

Properties in US. Customary Units ~~~

~~

Yield

Material

Ultimate Density s t r ~ stress [ l b / ~1103 l psi1 n o 3 psi]

Poisson,s ratio

Young's modulus [lo6 psi]

Percent elongation at rupture

Thermal coefficient [lOb/'FI

STEEL Structural, ASTM A36 AISI-C 1018, cold drawn AISI-C 1030, normalized AISI-C 1040, normalized AISI-C 1080, normalized AISI-3140, normalized AISI-4340, normalized AlSl301 Stainless, annealed AlSl301 Stainless, half hard

490 490 490 490 490 490 490 495 495

36 54 49 56 75 90 125 40 110

58 64 77 85 145 130 190 110 150

0.29 0.29 0.29 0.29 0.29 0.29 0.29 0.27 0.27

29 29.7 29 29 29 29 29 28 28

30 15 30 28 11 19 12 60 15

6.5 6.5 6.5 6.5 6.5 6.5 6.5 9.61 9.61

CAST IRON Gray, Class 30 (tension) Gray, Class 30 (compression) Gray, Class 40 (tension) Gray, Class 40 (compression)

450 450 450 450

-

30 74 60 144

0.20 0.20 0.20 0.20

15 15 20 20

nil nil nil nil

6.72 6.72 6.72 6.72

ALUMINUM ALLOYS 1100-H12 2024 1 4 6061 T6 6063 15 7075 T6

170 173 168 168 173

15 46 40 21 73

16 68 45 27 83

0.33 0.33 0.33 0.33 0.33

10.2 10.8 10.0 10.0 10.4

25 19 12 12 11

13.06 12.5 13.1 13.0 12.5

COPPER ALLOYS Free-Cutting Copper, soft Free-Cutting Copper, hard Yellow Brass, annealed Yellow Brass, half hard Commercial Bronze, annealed Commercial Bronze, half hard

556 556 526 526 552 552

9 42 17 49 13 41

32 46 49 61 39

17 17 15.2 15.2

48

0.35 0.35 0.35 0.35 0.35 0.35

16 16

42 12 60 23 45 25

9.78 9.78 11.11 11.11 10.0 10.0

TITANIUM Alloy Ti-AI-V

283

130

135

0.33

16.5

12

5.28

1.95 1.79 1.78

-

1.7-2.5a 1.7-2.5a 1.7-2.5a

3.6

-

5.5

TIMBER (12% MC) Coastal Douglas Fir (bending) Loblolly Pine (bending) White Oak (bending) CONCRETE Medium Strength (compression) aParallelto the grain.

30 31.8 42.4

145

-

-

12.40 12.80 15.20

4

-

0.15

AUTHOR INDEX

Index Terms

A Abramyan, B. L.

239

262

Allen, R. K.

609

623

Almroth, B. O.

424

455

American Concrete Institute (ACI)

652

654

18

19

American Institute of Steel Contruction (AISC)

24

221

262

442

563

565

625

626

632

654

455 American Institute of Timber Construction (AITC)

337

356

American Iron and Steel Institute (AISI)

442

455

18

24

American Society for Metals (ASM)

567

588

American Society for Testing and Materials (ASTM)

105

559

Anderson, C. G.

341

356

Anderson, C. M.

239

262

Andrade, E. N. da C.

625

630

Arutyunyan, N. Kh.

239

262

20

24

Bach, C.

481

501

Bailey, R. W.

625

630

633

647

Barsom, J. M.

543

562

563

565

Bazant, Z. P.

423

424

428

444

American Society of Civil Engineers (ASCE)

Asltonen, P.

B

654 Bemasconi, G.

625

654

Bleich, F.

444

455

Bleich, H.

340

356

Bodig, J.

652

653

654

Bolk, Ir. H. J. N.

650

651

654

This page has been reformatted by Knovel to provide easier navigation.

654

455

650

Index Terms Boresi, A. P.

24

28

32

50

52

56

58

63

78

81

84

85

86

103

152

199

200

202

203

211

214

218

239

241

242

256

262

265

266

294

295

318

380

388

392

422

444

455

458

464

468

474

477

486

501

507

508

541

582

588

625

633

640

644

648

654

655

Bowles, J. E.

359

388

Boyle, J. T.

625

637

641

648

654

Bridget, F. J.

440

455

British Standards Institute (BSI)

626

654

Broek, D.

543

561

562

563

565

Broughton, D. C.

342

356

Brown, W. F., Jr.

547

566

Brush, D. O.

424

455

Buch, A.

567

568

Buxbaum, O.

567

588

625

629

631

635

640

424

455

Cedolin, L.

423

424

428

444

455

Chajes, A.

424

455

Chandler, H. O.

584

588

Chang, C.

106

146

Chen, W. F.

115

122

127

128

146

Chien, W. Z.

234

235

262

Chong, K. P.

8

24

28

32

50

52

56

58

63

78

81

84

85

86

103

152

199

200

202

203

211

214

218

239

241

242

256

262

265

266

588

C

This page has been reformatted by Knovel to provide easier navigation.

654

Index Terms

Chong, K. P. (Cont.) 294

295

318

380

388

392

422

458

464

468

474

477

486

501

507

508

541

582

588

644

654

Chu, S. C.

407

422

Clark, M. E.

342

356

Clarke, W.L.

20

24

568

588

Clausmeyer, H.

562

565

Coffin, L. F.

581

588

Coker, E. G.

522

523

541

Conway, J. B.

629

640

654

Corten, H. T.

342

356

Cruse, T. A.

17

24

Curbishley, I.

543

562

565

587

588

626

654

Das, Y. C.

357

388

Davenport, C. C.

637

654

de Lacombe, J.

630

654

Dolan, T. J.

576

Dorn, J. E.

629

630

Dowling, N. E.

543

565

Doyle, J. F.

503

541

Drucker, D. C.

642

654

651

654

21

24

Ellyin, F.

584

588

Euler, L.

428

455

Evans, R.

633

640

654

Ewalds, H. L.

543

567

563

D

654

E Eckmann, B. Eisenstadt, M. M.

577

588

634

635

639

562

563

565

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

F Faufman, J. G.

547

566

Felgar, R. P.

106

146

625

631

632

645

654 Feltham, P.

630

654

Fessler, H.

601

603

623

Filon, L. N. G.

522

523

541

Finnie, I.

625

647

650

Forest Products Society (FPS)

100

103

Freed, C. N.

547

565

Freundenthal, A. M.

630

654

Frocht, M. M.

522

524

541

Fuchs, H. O.

567

568

570

588

Garofalo, F.

640

654

Gauthier, J. P.

567

588

1

24

424

434

440

456

Gooch, D. J.

641

654

Goodier, J. N.

319

345

356

509

542

596

20

24

567

568

588

Graham, A.

630

631

654

Graham, J. A.

584

588

Gray, T. G. F.

626

654

Greenberg, H. D.

547

565

Griffith, A. A.

525

527

630

654

Hakala, J.

20

24

Han, D. J.

115

122

128

146

Hanninen, H.

20

24

Harr, M. E.

17

24

654

G

Gere, J. M.

623 Gordon, G. M.

541

H Haferd, A. M.

127

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Harvey, J. M.

440

442

456

Hearmon, R. F. S.

652

654

Heimerl, G.J.

440

456

Hejwowski, T.

568

588

Heller, W.R.

625

647

650

Henmann, H. J.

562

563

565

Hertz, H.

589

590

592

607

378

388

654

623 Hetényi, M.

357

358

Hill, R.

128

146

Hills, J. F.

650

654

Hoersch, V. A.

596

597

How, I. M.

641

654

Hult, J.

625

654

Hwang, K. C.

562

565

Inglis, C. E.

509

541

International Standards Organization (ISO)

626

654

Irwin, G. R.

556

565

Iyengar, K. T. S. R.

357

378

Jacobsen, L. S.

525

541

James, R. W.

384

388

Jayne, B. A.

652

653

Jeffreys, H.

86

103

Jerome, C. C.

440

455

Johnson, J. E.

428

442

Johnson, K. L.

590

623

Jones, R.

357

388

503

623

655

I 552

565

388

J

654

446

448

This page has been reformatted by Knovel to provide easier navigation.

456

541

Index Terms

K Kachanov, L. M.

562

565

Kanninen, M. F.

543

565

Kanter, J.

630

654

Kennedy, A. J.

629

631

Kerr, A. D.

357

388

Klätschke, H.

567

588

Klesnil, M.

568

582

Kliman, V.

568

588

Knott, J. F.

543

625

654

654

584

588

547

556

559

565

70

78

503

522

541

Koh, S. K.

584

588

Koundis, A. N.

434

456

Kraus, H.

625

627

629

631

641

648

568

588 Kobayashi, A. S.

654 Kussmaul, K.

562

565

Kwofie, S.

584

588

Lagoda, T.

584

588

Lamba, H. S.

407

422

Landgraf, R. W.

584

588

Langhaar, H. L

80

103

147

148

152

153

199

423

424

434

437

456

461

413

501

Larson, F. R.

630

654

Levy, M

477

501

Levy, S

498

501

Li, C.

584

588

Libove, C.

440

456

Liebowitz, H

543

545

562

565

Liu, C. K

614

616

620

621

Lobo, G

492

501

L

This page has been reformatted by Knovel to provide easier navigation.

623

Index Terms

Logsdon, W.A.

547

565

Loveday, M. S.

626

631

654

Lubahn, J. D.

106

146

625

631

146

632

645

654 Lubliner, J.

114

123

126

Ludwik, P.

630

637

654

Lukáš P.

568

582

584

588

Lundquist, E. E.

440

456

Macha, E.

584

588

Mallis, J

434

456

Manson, S. S.

568

569

573

581

587

588

630

654

461

466

476

479

487

489

655

588

601

604

M

Marguerre, K.

501 Marriott, D. L.

625

629

McPherson, A. E.

498

501

McVetty, P. G.

630

654

McWhorter, J. C.

351

356

Mendelson,A

114

116

Mihashi, H.

563

566

Miller, J.

630

654

Mindess, S.

651

654

Mindlin, R. D.

614

623

Mitsuda, T.

619

623

40

41

43

Monismith, C. L

650

651

654

Morkovin, D.

105

146

Morley, A.

491

501

Morozov, E. M.

562

565

Morrow, J. D.

580

581

Mohr, O.

146

582

623 Mott, N. F.

630

655

Moyar, G. J

601

604

Muralidharon, U.

587

588

623

This page has been reformatted by Knovel to provide easier navigation.

Index Terms Murnahan, F. D.

78

Nabarro, F. R. N.

630

655

251

262

Naruoka, M.

476

501

Naumov, V. E.

239

262

Nelson, F. G.

547

566

Neuber, H.

513

514

538

542

Newell, H. E., Jr.

465

501

Nicholson, A. M

545

566

Noor, A. K.

239

262

Norton, F. H.

630

633

655

Odqvist, F. K. G.

625

631

635

Oh, S. J.

584

588

Ohno, N.

644

655

Ollerton, E.

601

603

Opperman, H.

567

588

Pan, T.-Y.

644

655

Paris, P. G.

546

549

Parton, V. Z.

562

566

Paul, B

545

556

Pawliczek, R.

584

588

Penny, R. K.

625

629

655

Peterson, R. E

503

524

542

Petrequin, P.

567

588

Phillips, F.

625

630

Phillips, J. W.

503

541

Piatti, G.

625

654

Pickel, T. W., Jr.

631

637

N

630

631

637

655

516

517

520

537

569

588

O 646

655

645

655

623

P

566

566

655

639

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Pilkey, W. D.

503

542

Popelar, C. H.

543

565

Prandtl, L.

216

262

Prasannan, S.

650

654

Prendergast, J.,

651

655

Prescott, J.

495

501

Pryle, W. H.

547

565

Raba, G. W.

384

388

Rabotnov,Yu. N.

625

627

629

633

639

648

650

655

Ramberg, W. A.

498

501

Ramu, S. A.

357

378

Rao, B. N.

446

456

Rhodes, J.

440

442

Robinson, E. L.

633

655

Rolfe, S. T

543

562

Roos, E.

562

565

Rossmanith, H. P.

543

566

Roux, S.

562

563

565

253

262

512

542

Salmon, C. G.

428

442

446

448

Sandor, B. I.,

568

588

Savin, G.N.

506

509

Schilling, P. E.

547

566

Scott, P. M.

20

24

Scott, R. F.

357

388

Seeger, T.

568

588

Seely, F B.

444

455

Selvadurai, A. P. S.

357

388

Shanley, F. R

444

445

R

634

388

456

563

565

S

542

456

This page has been reformatted by Knovel to provide easier navigation.

456

638

Index Terms Sidebottom, O. M

106

146

351

356

407

422

444

455

625

633

640

648

654

655

Sih, G. C

546

549

566

Skelton, R. P

568

588

Slater, W. A

477

480

482

501

Smith, A. I.

545

566

569

588

Smith, C. L.

630

655

Smith, F. A.

235

262

Smith, J. O

235

262

444

455

579

588

614

616

620

621

623

Socie, D. F.

568

588

Society of Automotive Engineers (SAE)

581

588

Soderberg, C. R.

630

635

Southwell, R. V.

426

456

Spence, J.

625

637

641

648

654

Srawley, J. E

547

566

Steigerwald, E. A

547

566

Stephens R. I

567

568

570

588

Sternberg, E

512

542

Stowell, E. Z

440

441

456

630

Sullivan, J. L

644

655

Szilard, R

424

456

473

501

Taira S

639

655

Takahashi, H

563

566

Talbott, A. N.

525

Tayeboli, A. A

650

651

654

Taylor, G. I

525

527

541

Taylor, R. C

239

262

Taylor, R. L.

648

655

Thomas, F. M.

235

262

Thomas, H. R

596

597

20

24

655

T

Tice, D. R

623

This page has been reformatted by Knovel to provide easier navigation.

655

Index Terms Timoshenko, S

342

345

356

424

434

440

456

473

476

492

500

501

509

542

596

623

378

388

473

501

Vallabhan, C. V. G

357

388

Van der Poel C

650

655

Vicat, L. J.

625

655

von Kármán, T.

234

235

Vormwald, M.

568

588

Vosseller, A. B.

440

455

Wahl, A. M.

492

501

Walles, K. F. A

631

654

Wang C. C

329

356

Wanhill, R. J. H

543

562

Warren, J. W. L

630

655

Weronski, A,

568

588

Wessel, E. T

547

565

566

Westergaard, H. M.

357

388

477

480

482

501

Wetenkamp, H. R

351

356

Wilshire, B

633

634

635

639

640

654

Wittmann, F

563

566

Woernle, H.-T

461

466

476

479

487

489

492

501

Ting, B.-Y.

U Ugural, A. C

V

262

W 524

542

563

565

501 Wöhler

569

588

Woinowsky-Krieger S

473

476

Wyatt, O. H

630

655

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

X Xenophontos, J.

357

388

Yang, W

562

565

Young, J. F

651

654

Yu, S. W

562

565

239

262

Y

Z Zienkiewicz, O. C

648

655

This page has been reformatted by Knovel to provide easier navigation.

SUBJECT INDEX

Index Terms

A Adiabatic conditions Angle of internal friction Anisotropic elasticity

80 126 84

Approach

607

Autofrettage

405

1

Axial strain

2

Axial stress

2

Axis: of bending

264

neutral

266

principal

267

274

275

32

moments of intertia

266

665

strain

55

60

stress

30

32

3

200

106

246

3

263

of twist in torsion

B Bauschinger effect Beams, bending displacement

4

shear stress

4

stress

4

curved

272

319

Bleich’s correction factors

338

340

circumferential stress

320

322

correction of

338

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Beams, (Cont.) deflections

343

350

351

neutral axis of cross section

326

333

anisotropic materials

334

stain energy density

344

statically indeterminate

348

on elastic foundations

357

boundary conditions for

360

on equally spaced elastic supports

364

finite length beam

361

general solution

357

table of coefficients for infinitely long

362 358

subject to concentrated load

360

subject to distributed load

369

subject to triangular load

371

semiinfinite

374

374

376

short

345

376

377

figure of solutions for

379

thin-wall circular cylinder

378

380

flexure formula

158

265

bending axis

264

266

deflection

280

281

flexure stress

158

266

geometry of deformation

280

281

284

273

nonsymmetrical bending

268

unsuitable cantilever

284

straight,

263

267

267

275

272

268

This page has been reformatted by Knovel to provide easier navigation.

Index Terms Bending, pure

axis of beams

264

266

deflections

280

281

273

nonsymmetrical

268

272

285

286

263

268

stresses

272

symmetrical

265

an unsuitable cantilever

284

fully plastic load (moment)

Binomial expansion

267

267

435

Boundary conditions, beams on elastic foundations

360

essential

438

forced

80

geometric

438

kinematic

438

natural

437

torsion

211

Brittle materials

15

Bulk modulus

87

437

475

438

475

120

Buckling of columns, see Columns

C Castigliano’s first theorem

149

Castigliano’s second theorem (on deflections)

152

164

343

155

Coaxing

571

Cohesion

126

Columns, boundary conditions buckling load

437

438

19

424

424

deflection response

425

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Columns, (Cont.) effective length

438

factor

438

439

empirical column formulas

446

447

Euler’s formula

426

428

eigenproblem formulation

430

energy method

443

equilibrium method

428

for general end conditions

436

437

higher buckling modes

430

431

imperfection method

432

ideal, definition of

425

elastic buckling of

425

imperfect

427

inelastic buckling

442

426

direct tangent-modulus method

443

444

double-modulus method

443

444

Engesser’s formula

444

445

tangent-modulus method

444

445

446

jamming

425

large deflections

426

425

local buckling

440

441

slenderness ratio

426

427

5

62

63

391

392

71

79

Compatibility relations Complementary energy, principle of

152

Conservative system

148

Constitutive relations

5

7

8

91

93

108

589

590

Contact stresses approach

607

assumptions

591

computation of

598

This page has been reformatted by Knovel to provide easier navigation.

84

Index Terms

Contact stresses (Cont.) friction, effect of

616

geometry of contact surface

591

592

line contact between bodies

611

613

with friction

613

619

without friction

611

619

notation for

596

597

octahedral shear stress, maximum

599

600

603

orthogonal shear stress, maximum

599

600

603

point of contact

592

606

606

607

principal stresses

590

597

roller on plane

614

shear stress, maximum

599

600

deflections at

range of

619

table of values of

620

Continuum mechanics, method of

618

619

613

617

598

600

613

613

617

7

Coordinates, cylindrical

52

elliptic

509

generalized

147

orthogonal curvilinear

52

polar

53

spherical

53

Corrosion fatigue

568

457

575

576

Cracks, see also Fracture and Fracture mechanics atomic model of

506

blunt

553

elastic stress at tip

553

critical length

558

extension force

556

critical value of

558

This page has been reformatted by Knovel to provide easier navigation.

616

Index Terms

Cracks, see also Fracture and Fracture (Cont.) growth analysis

562

propagation of

555

sharp

554

elastic stress at tip of

555

stationary

551

surface displacement of Modes I, II, III

545

Creep, aging (time) models

636

application to metals

649

definition

624

equation of state approach

639

failure

624

formulas for uniaxial stress

626

627

constant stress and temperature

626

table of

630

631

variable stress and temperature

631

635

640

641

643

647

multiaxial stress flow rule for nonsteady creep

648

644

theory of inelasticity for creep

643

nonmetals

650

asphalt

650

concrete

651

wood

652

rate

627

recovery

627

relaxation

627

rheological models

652

specific creep

652

632

models

635

strain-hardening models

633

635

633

636

643

637

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Creep, (Cont.) tension test

631

631

constant stress

631

time-hardening models

636

Creep curves (strain–time plots)

624

isochronous

633

similarity of

633

three ranges of

625

Cubical strain

625

628

634

394

395

626

86

Curved beams, see Beams, curved Cylinders, thick-wall

389

autofrettage

405

basic relations

389

of brittle materials

399

compatibility condition

391

composite

401

criteria of failure

399

395

for closed ends

395

for open ends

396

of ductile materials

400

equations of equilibrium

391

fully plastic pressure

405

material response data

392

shrink fit

398

strain–displacement relations

391

stress components for

391

closed ends

392

open ends

394

396

400

392

solutions for steady-state temperature distribution

410

stress–strain–temperature relations

392

Tresca material

406

von Mises material

406

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

D Deflections, beams, curved

165

361

straight, nonsymmetrical bending

280

281

by energy methods

7

statically determinate structures

163

statically indeterminate structures

163

180

Deformation, beam bending of deformable body geometry of

273 50

54

273

Design, inequality

17

limits on

16

modes of

16

Direction cosines, table of

31

Dislocations

21

Divergence theorem

81

Ductile materials

104

170

171

Dummy unit load method

170

171

E Eigenvalue problem

33

Elastic coefficients, see Material properties Elastic limit, see Material properties Elastic membrane method Elastic response

216

512

Elliptical hole

508

Elliptic integrals

597

percent

228

511

516

8

Ellipsoidal cavity

Elongation

217

517

2 11 This page has been reformatted by Knovel to provide easier navigation.

552

Index Terms Endurance limit

Energy, strain, see Strain energy Equations of equilibrium

5

272

Equations of motion

5

50

of a deformable body Euler’s buckling formula

50 426

428

F Factors of safety

17

Failure

16

of columns buckling creep

22 19 624

excessive deflection

19

20

fatigue

19

22

fracture

19

21

general yielding

20

modes

19

plastic deformation

19

Failure criteria

16

Fatigue

567

coaxing

571

corrosion

568

cross-over number of cycles

582

ε–N relation

580

effects of mean stress

572

effects of stress range

577

endurance limit

569

fatigue life design

580

hysteresis loop

580

low-cycle

568

σ–N (S–N) diagrams

569

strain-controlled testing

580

strain-life curves

583

strength

575

576

581

581

580

22

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Finite difference method for the torsion problem

241

242

Flexure formula

158

266

267

Flow rule

113

549

558

Flat plates, see Plates, flat 275

Forces, body

27

external

80

normal

25

shear

26

vectoral summation of

29

Fourier heat equation

409

Fourier series

434

Fracture mechanics

543

brittle fracture

545

crack-growth analysis

562

design of test specimens

547

elastic-plastic

562

fracture toughness, KIC

547

table of values

548

linear elastic

561

562

notch toughness

544

stationary crack

551

stress history

562

stress intensity factor, KI

546

569

critical

546

548

definition of

546

547

table of

550

testing

547

specimen design

547

549

558

G Gages, strain

70

Gerber relation

572

573

Goodman relation

572

573

This page has been reformatted by Knovel to provide easier navigation.

Index Terms Green strain

components

56

total

56

H Haigh-Westergaard stress space

114

Hardening rule

113

Hooke’s Law

84

anisotropic elasticity

84

isotropic elasticity

84

orthotropic elasticity

93

Hydrostatic stress

85

34

I Inelastic response Instability, structural

8

104

22

Internal energy density

79

81

complementary

79

82

elastic

81

variation of

81

83

Invariants, strain

61

86

stress

33

86

120

J J2 materials

122

K Kirchhoff shear

476

Kirchhoff approximation, plates

462

463

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

L Lamé’s elastic coefficients

86

Limit states

18

design

16

87

18

5 18

5

M Magnification factor

56

Material properties

10

elastic coefficients

11

elastic limit

10

homogeneous

85

isotropic

85

yield strength

11

tables of

658

Mechanics of materials method review

13

84

87

659

6 1

Membrane analogy (Randtl)

216

Methods of analysis

5

Metric coefficients

52

217

228

Modulus, of elasticity

11

of resilience

12

of rupture

13

of toughness

13

Mohr’s circle

40

134

41

three-dimensional

43

two-dimensional (plane)

40

41

Moment–curvature relations, plates

470

471

Moments of plane area, second

266

660

common areas

661

662

parallel axis theorem for

661

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Moments of plane area, second (Cont.) polar moment of inertia

660

661

principal axes for

266

665

transformation equations for

664

Motion, equations of

5

Multi-axial stress state

106

Multiply-connected cross section

218

50

230

N Necking

13

Nonlinear material response

107

Notch sensitivity index

531

Notch toughness

544

O Octahedral, plane

37

stress

36

normal

36

shear

36

Orthotropic materials

93

axes for

93

coefficients for

93

Poisson’s ratios

94

stress–strain relations

94

P Parallel axis theorem

661

109

Plane, stress, see Stress, plane Plane of loads

263

effect of small inclination of Plane, principal

284 32

130

Plastic moment

130

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Plasticity

104

Plastic moments for beam cross sections

132

Plates, flat

457

boundary conditions

457

forced

475

natural

475

107

113

473

circular, clamped (fixed) edges

488

with circular hole

489

large deflections

492

simply-supported edges

488

solution for table of solutions for

496

497

486

488

493

491

493

classification of

457

differential equation for

476

displacement components

462

equilibrium equations

466

flexural rigidity of

470

general theory

466

kinematic relations

461

Kirchhoff approximation

462

Kirchoff shear in

476

Levy method

477

membrane stiffening

492

493

moment-curvature relation

470

471

Navier method

477

500

pure bending

472

463

497

rectangular, clamped (fixed) edges

481

deflections

482

large deflections

498

other type edges

482

simply supported edges

480

solution for

477

table of solutions for

483

479

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Plates, flat (Cont.) rotation of surface element

464

small displacement rotation of a volume element

464

465

strain–displacement relations

461

strain energy of

472

bending

472

membrane

472

stress components

472

stress resultants

460

stress–strain–temperature relations

469

tractions

459

transverse shears

460

twisting moments

460

461

13

87

Prandtl membrane analogy

216

217

228

Prandtl stress function

216

217

228

Poisson’s ratio

Principle planes

32

Principal axes

32

of moments of inertia

461

266

665

of strain

55

60

of stress

30

32

Principal stresses

32

Product of inertia of plane area

664

Progressive fracture, see Fatigue Proportional limit Pure bending

10 6

π-plane

122

123

R Rayleigh’s method

434

Redundant member

177

Redundant reaction

177

Reentrant comers, torsion

219

Reliability concepts

17

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Resilience, modulus of

12

Resistance

17

factors

18

Review of elementary mechanics of materials Rigid-perfectly plastic material Rotating disks

1 15 411

plastic deformation

415

residual stresses

417

Rupture, modulus of

13

418

S S-N (σ-N) diagrams, see Fatigue Safety, factor of

17

Saint-Venant principle

203

Sand heap analogy

251

Section modulus

130

elastic

130

plastic

130

Semi-inverse method

209

Shear center

263

axis of antisymmetry

265

axis of symmetry

265

beam with thin-wall

295

channel section

298

box beams

306

composite beams

303

definition of

264

table for

300

268

265

Shear correction coefficient

159

160

Shear flow

229

296

cut

307

in torsion

229

Shear stress at yield

118

119

345

121

σ-N (S–N) diagrams, see Fatigue

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Simply connected cross section

218

Soap-film analogy

216

228

Soderberg relation

572

573

Stationary potential energy

147

148

Steel cross sections, properties of

668

Strain, compatibility relations of

62

cubical

86

elastic

11

engineering

55

62

extensional

60

62

gages

70

Green strain

55

components

56

total

56

hardening

21

invariants

61

of line element

55

magnification factor

56

measurement of

70

offset

11

permanent

10

plane

62

Mohr’s circle of

63

62

86

71

63

67

principal

55

60

rosettes

70

71

delta

71

rectangular

71

shear

58

tensor

59

theory of

25

transformation of

55

true volumetric

59

55

9 86

92

This page has been reformatted by Knovel to provide easier navigation.

Index Terms

Strain-displacement relations, in cylindrical coordinates

64

finite displacement

57

in orthogonal coordinates

63

in polar coordinates

64

small displacements

61

integration of

69

in spherical coordinates

64

Strain energy, axially loaded members

156

157

bending of beams

158

complementary

152

density

13

81

complementary

82

83

elastic

81

for isotropic elastic material

85

shear in beams

158

for torsion

160

Strain hardening

11

Strength, fatigue

22

ultimate

11

yield

11

12

546

554

Strength reduction factor Stress, array of plane stress

38

components of

27

on arbitrary plane

29

normal

30

on oblique plane

30

shear

30

symmetry of

28

contact, see Contact stresses definition of

25

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Index Terms

Stress, (Cont.) deviator effective uniaxial

37

38

106

114

hydrostatic

34

invariants of

33

86

mean

37

38

multi-axial

120

106

notation

26

octahedral

36

normal

36

shear

36

plane stress

38

array

39

Mohr’s circles in

40

tensor

39

principal

30

principal stress space

41

32

114

shear, pure

38

tensor

28

deviator

38

mean

38

theories of

25

transformation

31

true

28

9

ultimate

11

vector

26

normal

26

shear

26

yield Stress concentration factors

11

12

504

551

573

505

530

atomic model of a crack

506

in beams

527

calculated

504

515

effective

504

575

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Index Terms

Stress concentration factors (Cont.) repeated loads

532

533

elastic membrane method

525

for ellipsoidal cavity

512

experimental techniques

522

for fillet in torsion

525

527

for grooves and holes in bars

513

520

inelastic strains

536

Neuber’s theorem, application of for infinite plate, with circular hole

537

538

507

515

with crack

512

with elliptical hole

508

511

methods of reducing

577

nature of

504

Neuber’s nomograph

514

notch sensitivity index

531

theory of elasticity

507

Stress intensity factors

546

554

critical

546

559

definition

556

Model I

545

546

Modes II and III

545

546

104

105

Stress–strain data

575

516

limitations on use of

104

standard tests for

105

Stress–strain relations

8

79

108

diagram

9

14

15

linear

2

79

orthotropic materials Stress–strain–temperature relations isotropic linear elastic

517

94 71

91

91

Superposition, method of

363

Supports, settling of

180

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552

Index Terms

T Tensor, deviator stress

38

mean stress

38

of plane stress

39

second order symmetric

32

strain

59

stress

28

Thermal expansion coefficient

91

Thermodynamics, first law

79

411

Thennoelasticity, for isotropic linear elastic material Torsion

91 200

angle of twist per unit length

200

201

209

237

201

203

214

237

216

220

221

246

250

angular velocity

204

axis of twist

200

Bauschinger effect

246

boundary conditions

211

circular cross section

200

constant

215

elastic-plastic

244

boundary

246

elliptical cross sections

214

equations of equilibrium

210

frequency of rotation

204

fully plastic

244

sand heap analogy

251

tables for

251

general cross section

250

geometry of deformation

209

of hollow thin-wall member

228

inelastic torsion

243

230

This page has been reformatted by Knovel to provide easier navigation.

224

230

Index Terms

Torsion (Cont.) linear elastic solution

213

maximum shear stress in

225

membrane analogy

216

modulus of rupture in

244

of multiply-connected cross section

218

of narrow rectangular cross section

219

214

217

228

228

230

cross section made up of long narrow rectangles

221

numerical solution

239

power

204

rectangular cross sections

222

reentrant corners

219

residual shear stress

246

restrained ends

234

I-section tables for

225

235 240

rigidity factor for

203

Saint-Venant’s principle

203

semi-inverse method

209

shear flow

229

simply-connected cross section

218

soap-film analogy

216

228

stress function

211

transmission shaft design

204

unit angle of twist warping function Torsionally loaded members

215

216

220

214

240

253

201

203

214

237

210

234

210 3

angle of twist

3

shear strain

3

shear stress

3

Toughness, modulus of notch

13 544

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224

Index Terms

U Unit vector

29

V Virtual displacement

147

Virtual work

148

Viscoelasticity

107

Viscoplasticity

107

Volumetric strain

86

92

W Warping, restraint of

234

Winkler foundation

357

Work

80

hardening

21

virtual

148

external

148

internal

148

deviatoric plane

122

of ductile metals

117

effective stress

116

121

function

114

121

hydrostatic axis

122

hydrostatic stress, effect of

122

129

Y Yield,

128

locus, Haigh-Westergaard stress space

114

principal stress space

114

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Index Terms

Yield, (Cont.) moment

129

π-plane

122

123

11

12

114

115

117

106

113

114

stress surface Yield criteria Beltrami’s

116

comparison of

139

140

distortional energy density

119

120

Drucker-Prager

127

128

general concepts

113

Hill’s

128

maximum octahedral shear stress

119

maximum principal strain

116

maximum principal stress

114

maximum shear stress

118

Mohr-Coulomb

126

for orthotropic materials

128

Rankine’s

114

Saint–Venant’s

116

strain-energy density

116

Tresca

118

von Mises

119

Young’s modulus

11

127

121

115

119

87

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