FIELD OF ART 
       [0001]    The present invention relates to a fixed-wing vertical take-off and landing (VTOL) aircraft having rotors on outriggers. The present invention more particularly relates VTOL aircraft having pivotal propulsion elements. 
       BACKGROUND OF THE INVENTION 
       [0002]    Fixed-wing VTOL aircraft present the most difficult challenges in aerospace engineering, as the transition between vertical, direct-thrust, flight and horizontal, wing-borne, flight raises serious stability problems. The Harrier aircraft uses vectored thrust from jet engine compressor bleed air for vertical, direct-thrust, flight and traditional jet engine power for wing-borne flight. The Osprey aircraft uses tilt rotors on the ends of fixed-wings for vertical takeoff and tilts the engines and rotors to transition to wing-borne flight. In vertical flight, part of the rotor-propelled air impinges on the top surface of the wing, reducing effective thrust. In wing-borne flight, the wing receives rotor-propelled air from only one side of the engine. 
         [0003]    What is needed is a VTOL aircraft using multiple smaller rotors on outriggers, such that the rotor-propelled air is least obstructed by part of the wing or fuselage. 
       SUMMARY OF THE INVENTION 
       [0004]    The VTOL aircraft of the present invention has fixed-wings which can be monoplane, biplane or tri-plane and tiltable or fixed rotors on outriggers which extend from the fuselage and/or wings. The rotors on the outriggers can be driven by engines located in the fuselage or wings via a transmission system such as a shaft, pulley, or pressurized air using pumps. If rotors are driven by jets at the tips, fuel is fed through pipes inside of the outriggers. The rotors and engines can be located at the ends of the outriggers like multi rotor drones ‘with electric engines otherwise it is preferable to separate them if the engine is heavy since separating the rotors from the engines and tilting only the rotors reduces structural requirements and weight of the aircraft. 
         [0005]    The rotors can be tilted over ninety degrees from the vertical position forwards and backwards, sideways if needed for lateral movement. The outriggers can be configured in various ways depending upon how many rotors are used and where the engines are located. Placing rotors on outriggers in the spaces least obstructed by the wings and fuselage reduces drag which increases efficiency and also offers a flexible platform for various hybrid designs. 
         [0006]    Multiple rotors has the advantage of smaller diameter and lighter rotors blades, lower structural requirements, smaller gears, reduced weight, better stability and control of aircraft, higher rotor rpm to attain higher speeds in horizontal flight, added safety if one is damaged, and longer range. In case of engine failure, wings add stability and increase the glide ratio. If the length of the rotors are short so it won&#39;t touch the ground when tilted in line with forward flight, it can be flown as a fixed-wing aircraft on take-off and landing which increases load capacity. Submitted embodiments are not inclusive of all possible designs. The placement of rotors away from the fuselage and wings allows for simple and inexpensive installation of ballistic parachutes if desired. 
     
    
     
       DESCRIPTION OF THE FIGURES OF THE DRAWINGS 
         [0007]    The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and 
           [0008]      FIG. 1  is a top plan diagrammatic view illustrating an exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers, according to a preferred embodiment of the present invention; 
           [0009]      FIG. 2  is a side elevation diagrammatic view illustrating the exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 1 , according to a preferred embodiment of the present invention; 
           [0010]      FIG. 3  is a front elevation diagrammatic view illustrating the exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 1  in a non-flight configuration, according to a preferred embodiment of the present invention; 
           [0011]      FIG. 4  is a top plan diagrammatic view illustrating a second exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers, according to a preferred embodiment of the present invention; 
           [0012]      FIG. 5  is a side elevation diagrammatic view illustrating the second exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 4 , according to a preferred embodiment of the present invention; 
           [0013]      FIG. 6  is a front elevation diagrammatic view illustrating the second exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 4 , according to a preferred embodiment of the present invention; 
           [0014]      FIG. 7  is a top plan diagrammatic view illustrating a third exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers, according to a preferred embodiment of the present invention; 
           [0015]      FIG. 8  is a side elevation diagrammatic view illustrating the third exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 7 , according to a preferred embodiment of the present invention; 
           [0016]      FIG. 9  is a front elevation diagrammatic view illustrating the third exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 7 , according to a preferred embodiment of the present invention; 
           [0017]      FIG. 10  is a top plan diagrammatic view illustrating a fourth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers, according to a preferred embodiment of the present invention; 
           [0018]      FIG. 11  is a side elevation diagrammatic view illustrating the fourth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 10 , according to a preferred embodiment of the present invention; 
           [0019]      FIG. 12  is a front elevation diagrammatic view illustrating the fourth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 10 , according to a preferred embodiment of the present invention; 
           [0020]      FIG. 13  is a top plan diagrammatic view illustrating a fifth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers, according to a preferred embodiment of the present invention; 
           [0021]      FIG. 14  is a side elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 13 , according to a preferred embodiment of the present invention; 
           [0022]      FIG. 15  is a front elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 13  in a non-flight configuration, according to a preferred embodiment of the present invention; 
           [0023]      FIG. 16  is a top plan diagrammatic view illustrating a fifth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers, according to a preferred embodiment of the present invention; 
           [0024]      FIG. 17  is a front elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 16 , according to a preferred embodiment of the present invention; and 
           [0025]      FIG. 18  is a side elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing VTOL aircraft with rotors on outriggers of  FIG. 16  with a cut-away portion, according to a preferred embodiment of the present invention. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0026]      FIG. 1  is a top plan diagrammatic view illustrating an exemplary embodiment of the fixed-wing VTOL aircraft  100  with rotors  102  on outriggers  104 , according to a preferred embodiment of the present invention. Fuselage  108 , including structural members therein, supports wings  106  with flight control surfaces  120  (such as ailerons  120 ) and a vertical stabilizer  116  further supporting horizontal stabilizer  114  having a flight control surface  118  (such as an elevator  118 ). Fuselage  108  further supports outriggers  104  which house drive shafts  122  coupled between motor output shaft  124  and rotational couplings  126 . In some embodiments, fuselage  108  may support an emergency ballistic parachute that can deploy if the aircraft  100  is disabled. Motor output shaft  124  is driven by motor  110 , which is located within the fuselage  108 . Coupling between the motor output shaft  124  and the drive shafts  122  may, in various embodiments, be of any suitable configuration, within the constraints of reliability and weight reduction. Motor  110  may, in various embodiments, be any type of motor, from a battery-operated electric motor  110  for a toy drone to a combustion motor  110  (piston or jet) for a large aircraft  100 . 
         [0027]    Rotors  102  may be rigid or, for heavy lift aircraft, flexible. While all rotors  102 ,  402  (see  FIG. 4 ),  702  (see  FIG. 7 ),  1002  (see  FIG. 10 ),  1302  (see  FIGS. 13 ) and  1602  (see  FIG. 16 ) are shown as being the same size, rotor size is not a limitation of the invention. In some embodiments, both rigid and flexible rotors may be used. In particular embodiments, so vertical lift rotors may be fixed. In some embodiments, wings  106 ,  406 , (see  FIG. 4 ),  706  (see  FIG. 7 ),  1006  (see  FIG. 10 ),  1306  (see  FIGS. 13 ) and  1606  (see  FIG. 16 ) may be swept forward or swept back. 
         [0028]    The long axis  128  of the fixed-wing VTOL aircraft  100  defines a line of symmetry for the arrangement of rotors  102 . Rotors  102  are arranged in sets of first and second rotors, spaced apart on opposite sides of the fuselage  108 , with a first set forward of the wings  106  and a second set aft of the wings  106 , as shown. 
         [0029]    Each outrigger  104  supports a rotational coupling  126  linking each respective driveshaft  122  to each respective rotor  102 , enabling rotation of the powered rotors  102  relative to their respective outriggers  104 . The rotors  102  are diagrammed in this view in a vertical flight configuration, with the forward rotors  102  above their respective outriggers  104  and the rear rotors  102  below their respective outriggers  104 . By illustrating the rotors  102  as circles, the absence of thrust obstruction by the wings  106  and by the fuselage  108  can be clearly seen. 
         [0030]    In some embodiments, force to propel the rotors  102  may be provided by pneumatics, hydraulics, or rotor-tip jets, rather than the motor  110 , motor output shaft  124 , and drive shafts  122 . Such variation is available in all embodiments. The shape of the illustrated fuselage  108  and airfoils  106 ,  114 , 116 ,  118 , and  120  are not limitations of the invention. Rather, the outriggers  104  housing drive shafts  122  to four rotors  102  supporting articulatible couplings  126 , with two rotors  102  forward of the wing  106  and two rotors  102  aft of the wing  106  represents a novel feature of the invention. 
         [0031]      FIG. 2  is a side elevation diagrammatic view illustrating the exemplary embodiment of the fixed-wing VTOL aircraft  100  with rotors  102  on outriggers  104  of  FIG. 1 , according to a preferred embodiment of the present invention. The couples of dashed-line arrows illustrate the directional of rotation for forward rotors  102  and rear rotors  102  from a vertical thrust position (as shown) to a wing-borne flight forward thrust position. Flight control surface  212 , such as a rudder  212 , is shown on vertical stabilizer  116 . Notice that the outriggers  104  are below the wings  106 . Horizontal stabilizer  114  in not impinged by rotation of the rear rotors  102 . 
         [0032]      FIG. 3  is a front elevation diagrammatic view illustrating the exemplary embodiment of the fixed-wing VTOL aircraft  100  with rotors  102  on outriggers  104  of  FIG. 1  in a non-flight configuration, according to a preferred embodiment of the present invention. A non-flight configuration is shown to illustrate that rotor  102  (on the viewer&#39;s left), in a wing-borne flight forward thrust position ,does not extend below the fuselage  108  and so this aircraft  100  could, in an embodiment equipped with landing gear, take off and land horizontally as well as vertically, as illustrated by rotor  102  (on the viewer&#39;s right). 
         [0033]      FIG. 4  is a top plan diagrammatic view illustrating a second exemplary embodiment of the fixed-wing VTOL aircraft  400  with rotors  402  on outriggers  404 , according to a preferred embodiment of the present invention. Fuselage  408 , including structural members therein, support wings  406  with flight control surfaces  420  (such as ailerons  420 ) and a vertical stabilizer  416  further supporting horizontal stabilizer  414  having a flight control surface  418  (such as an elevator  418 ). Wings  406  further support outriggers  404  which house drive shafts coupled between motors  410 , which motors  410  are located under their respective wings  406 . Motor  410  may, in various embodiments, be any type of motor, from a battery-operated electric motor for a toy drone to a combustion motor (piston or jet) for a large aircraft. Transfer of power from the motor  410  to the rotors  402  may be similar to the embodiment of  FIG. 1 . Rotors  402  are arranged in sets of first and second rotors  402 , spaced apart on opposite sides of the fuselage  408 , with a first set forward of the wings  406  and a second set aft of the wings  406 , as shown. 
         [0034]    Each outrigger  404  supports a rotational coupling  426  linking each respective driveshaft to each respective rotor  402 , enabling rotation of the powered rotors  402  relative to their respective outriggers  404 . The rotors  402  are diagrammed in a vertical flight configuration, with the forward rotors  402  above their respective outriggers  404  and the rear rotors  402  below their respective outriggers  404 . By illustrating the rotors  402  as circles, the absence of thrust obstruction by the wings  406  and by the fuselage  408  can be clearly seen. The shape of the illustrated fuselage  408  and airfoils  406 ,  512  (see  FIGS. 5 ),  414 ,  416 ,  418 , and  420  are not limitations of the invention. Rather, the outriggers  404  housing drive shafts  122  to four rotors  102  supporting articulatible couplings  126 , with two rotors  102  forward of the wing  106  and two rotors  102  aft of the wing  106  represents a novel feature of the invention. The use of two wing mounted motors  410  to drive the drive shafts (not shown, but as with  FIG. 1 ) within the outriggers  404  is also a novel feature of the invention. 
         [0035]      FIG. 5  is a side elevation diagrammatic view illustrating the second exemplary embodiment of the fixed-wing VTOL aircraft  400  with rotors  402  on outriggers  404  of  FIG. 4 , according to a preferred embodiment of the present invention. The couples of dashed-line arrows illustrate the directional of rotation for forward rotors  402  and rear rotors  402  from a vertical thrust position to a wing-borne flight forward thrust position. Flight control surface  512 , such as a rudder  512 , is shown on vertical stabilizer  416 . Notice that the outriggers  1404  are below the wings  406 . Horizontal stabilizer  414  in not impinged by rotation of the rear rotors  402 . The view of wing  406  is of the underside of the wing  406 . 
         [0036]      FIG. 6  is a front elevation diagrammatic view illustrating the second exemplary embodiment of the fixed-wing  406  VTOL aircraft  400  with rotors  402  on outriggers  404  of  FIG. 4 , according to a preferred embodiment of the present invention. Rotors  402  extend below the fuselage  408  during forward flight, requiring this embodiment to take off and land vertically. In a particular embodiment, landing gear extending from the bottom of the fuselage may be added to enable horizontal takeoff and landing. 
         [0037]      FIG. 7  is a top plan diagrammatic view illustrating a third exemplary embodiment of the fixed-wing  706  VTOL aircraft  700  with rotors  702  on outriggers  704 , according to a preferred embodiment of the present invention. Fixed-wing VTOL aircraft  700  is shown in a vertical flight configuration. Fixed-wings  706 , extending from fuselage  708 , have ailerons  720 . Vertical stabilizer  716  (see  FIG. 8 ) extends from fuselage  708  and supports rudder  712  (see  FIG. 8 ) and horizontal stabilizer  714 . Horizontal stabilizer  714  supports flight control surfaces  718  (one of two labeled), such as elevators  718 . Engines  710  transfer power to gear boxes  728  which transfer power via drive shafts  722  within outriggers  704 . Outriggers  704  support rotational couplings  726  to drive and articulate rotors  702 . Gear boxes  728  are preferably supported on supports for outriggers  704  on or within the fuselage  708 . Rotors  702  are arranged in sets of first and second rotors  702 , spaced apart on opposite sides of the fuselage  708 , with a first set forward of the wings  706  and a second set aft of the wings  706 , as shown. 
         [0038]    The shape of the illustrated fuselage  708  and airfoils  706 ,  712  (see  FIGS. 8 ),  714 ,  716 ,  718 , and  720  are not limitations of the invention. Rather, the outriggers  704  housing drive shafts  722  to four rotors  702  supporting articulatible couplings  726 , with two rotors  702  forward of the wing  706  and two rotors  702  aft of the wing  706  represents a novel feature of the invention. The use of four external fuselage-mounted motors  710  to drive the drive shafts  722  within the outriggers  704  is also a novel feature of the invention. 
         [0039]      FIG. 8  is a side elevation diagrammatic view illustrating the third exemplary embodiment of the fixed-wing  706  VTOL aircraft with rotors  702  on outriggers  704  of  FIG. 7 , according to a preferred embodiment of the present invention. The couples of dashed-line arrows illustrate the directional of rotation for forward rotors  702  and rear rotors  702  from a vertical thrust position to a wing-borne flight forward thrust position. The view of wing  706  is of the underside of the wing  706 . 
         [0040]      FIG. 9  is a front elevation diagrammatic view illustrating the third exemplary embodiment of the fixed-wing  706  VTOL aircraft  700  with rotors  702  on outriggers  704  of  FIG. 7 , according to a preferred embodiment of the present invention. Rotors  702  do not extend below the fuselage  708  during forward flight, enabling this embodiment to take off and land horizontally or vertically. In a particular embodiment, landing gear may be added to this embodiment to facilitate horizontal landing. 
         [0041]      FIG. 10  is a top plan diagrammatic view illustrating a fourth exemplary embodiment of the fixed-wing  1006  VTOL aircraft  1000  with rotors  1002  on outriggers  1004 , according to a preferred embodiment of the present invention. Wings  1006  extend from fuselage  1008  and support ailerons  1020 , or similar flight control surfaces  1020 . Vertical stabilizer  1016  (see  FIG. 11 ) extends from fuselage  1008  and supports rudder  1102  (see  FIG. 11 ) and horizontal stabilizer  1014 . Four motors  1010 , located partially within the fuselage  108 , transfer power to drive shafts (not shown, but as with  FIG. 1 ) within outriggers  1004  to rotational couplings  1026 . Rotational couplings  1026  transfer power to rotors  1002  and articulate the rotors  1002  between the vertical flight and wing-borne flight forward flight modes. Rotors  1002  are arranged in sets of first and second rotors  1002 , spaced apart on opposite sides of the fuselage  1008 , with first and second sets forward of the wings  1006  and third and fourth sets aft of the wings  1006 , as shown. The lift between the forward and aft sets of rotors  1002  is preferably balanced about the center of mass of the aircraft  100 , which is preferably near the center of lift provided by wings  1006 . As for all of the embodiments, the transition from vertical to wing-borne flight forward mode is controlled by a control system which may be entirely onboard the aircraft or may be partially onboard and partially off board, as with remotely controlled aircraft. 
         [0042]    A particular advantage of the present embodiment is that one pair of rotors  1002  forward of the wings  1006  and one pair of rotors  1002  aft of the wings  1006  may be transitioned to wing-borne flight forward mode before the remaining pairs of rotors  1002 , to smooth the transition to wing-borne flight forward mode. The shape of the illustrated fuselage  1008  and airfoils  1006 ,  1012  (see  FIGS. 8 ),  1014 ,  1016 ,  1018 , and  1020  are not limitations of the invention. Rather, the outriggers  1004  housing drive shafts  1022  to four rotors  1002  supporting articulatible couplings  1026 , with two rotors  1002  forward of the wing  1006  and two rotors  1002  aft of the wing  1006  represents a novel feature of the invention. The use of four semi-external fuselage-mounted motors  1010  to drive the drive shafts (not shown) within the outriggers  1004  is also a novel feature of the invention. 
         [0043]      FIG. 11  is a side elevation diagrammatic view illustrating the fourth exemplary embodiment of the fixed-wing  1006  VTOL aircraft  1000  with rotors  1002  on outriggers  1004  of  FIG. 10 , according to a preferred embodiment of the present invention. This view shows motors  110  partially within the fuselage  1008 . As shown in  FIG. 10 , the rotors  1002  do not contact one another in any flight mode. 
         [0044]      FIG. 12  is a front elevation diagrammatic view illustrating the fourth exemplary embodiment of the fixed-wing  1006  VTOL aircraft  1000  with rotors  1002  on outriggers  1004  of  FIG. 10 , according to a preferred embodiment of the present invention. Preferably, the control system onboard synchronizes the rotors  1002  to provide steady air flow over the wings  1006 , vertical stabilizer  1016 , and horizontal stabilizer  1014 . Avoidance of flow resonances is preferred. Rotors  1002  do not extend below the fuselage  1008  during forward flight, enabling this embodiment to take off and land horizontally or vertically. In a particular embodiment, landing gear may be added to this embodiment to facilitate horizontal landing. 
         [0045]      FIG. 13  is a top plan diagrammatic view illustrating a fifth exemplary embodiment of the fixed-wing  1306  VTOL aircraft  1300  with rotors  1302  on outriggers  1304 , according to a preferred embodiment of the present invention. VTOL aircraft  1300  is shown in a vertical flight configuration. Swept wings  1306  extend from the top of fuselage  1308  and support flight control surfaces  1320  (one of four labeled). Vertical stabilizer  1316  also extends from fuselage  1308 . Outriggers  1304  support rotational couplings  1326  which transfer power to rotor  1302  and articulate rotors  1302  between vertical flight and wing-borne flight forward modes. The shape of the illustrated fuselage  1308  and airfoils  1306 ,  1316 , and  1320  are not limitations of the invention. Rather, the outriggers  1304  housing drive shafts (not shown, but as in  FIG. 1 ) to three rotors  1302  supporting articulatible couplings  1326 , with two rotors  1302  forward of the wing  1306  and one rotor  1302  aft of the wing  1306  represents a novel feature of the invention. The use of a counter-rotating rotor  1402  with each rotor  1302  where the rotor pairs  1302 ,  1402  are pair-wise articulatible, is also a novel feature of the invention. Use of a single, internally fuselage-mounted motor  1410  to drive the drive shafts (not shown) within the outriggers  1304  is also a novel feature of the invention. Rotors  1302  are arranged in a set of first and second rotors  1302 , spaced apart on opposite sides of the fuselage  1308 , with first and second rotors  1302  forward of the wings  406  and a third rotor  1302  aft of the wings  1306  ,as shown. 
         [0046]    The shape of the illustrated fuselage  1308  and airfoils  1306 ,  1316 , and  1320  are not limitations of the invention. Rather, the outriggers  1304  housing drive shafts (not shown, but as in  FIG. 1 ) to three rotors  1302  supporting articulatible couplings  1326 , with two rotors  1302  forward of the wing  1306  and one rotor  1302  aft of the wing  1306  represents a novel feature of the invention. The use of a counter-rotating rotor  1402  with each rotor  1302  where the rotor pairs  1302 ,  1402  are pair-wise articulatible, is also a novel feature of the invention. Use of a single, internally fuselage-mounted motor  1410  to drive the drive shafts (not shown) within the outriggers  1304  is also a novel feature of the invention. 
         [0047]      FIG. 14  is a side elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing  1306  VTOL aircraft  1300  with rotors  1302  on outriggers  1304  of  FIG. 13 , according to a preferred embodiment of the present invention. A single motor  1410  provides power to all rotor pairs  1302  and  1402  via drive shafts in outriggers  1304 . All rotors  1302  have counter-rotating rotors  1402  in order to reduce net torque. Forward rotor pairs  1302  and  1402  are mounted above the outriggers  1304  to enable rotation without impact with the outriggers  1304 . Rear rotor pair  1302  and  1402  is mounted below the outrigger  1304  for the same reason. The control system will control the rotor velocity between the two front rotors and the rear rotor to compensate for any changes in the center of mass due to fuel consumption. The couples of dashed-line arrows illustrate the directional of rotation for forward rotor pairs  1302  and  1402  and rear rotor pair  1302  and  1402  from a vertical thrust position to a wing-borne flight forward thrust position. 
         [0048]      FIG. 15  is a front elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing  1306  VTOL aircraft  1300  with rotors  1302  and  1402  on outriggers  1304  of  FIG. 13  in a non-flight configuration, according to a preferred embodiment of the present invention. Because rear rotor  1302  extends below the fuselage, as shown, horizontal takeoff and landing is unsafe. In some embodiments, landing gear extending from the underside of fuselage  1308  may enable safe horizontal takeoffs and landings. 
         [0049]      FIG. 16  is a top plan diagrammatic view illustrating a fifth exemplary embodiment of the fixed-wing  1606  VTOL aircraft  1600  with rotors  1602  on outriggers  1604 , according to a preferred embodiment of the present invention. Double parallel spaced apart fuselage members  1608  support fixed-wing  1606 , vertical stabilizers  1616 , and horizontal stabilizer  1614  on top of the fuselage members  1608 . Horizontal stabilizer  1614  supports elevator  1618 . Between double parallel spaced apart fuselage members  1608  are supported front thrust assembly  1609 ; inner wing  1607 , and rear thrust assembly  1609 . Each thrust assembly  1609  includes a cowling  1613 , a motor  1610  supported  1611  (one of four labeled) in the cowling  1613 , and a rotor  1602  driven by the motor  1610 . Each thrust assembly  1609  can be rotated between a vertical flight configuration, as shown, to a wing-borne flight forward thrust configuration about an axis between the fuselage members  1608 . Inner wing  1607  may serve, at least in part, as a fuel tank. Outriggers  1604  extend from wings  1606  and support motors  1610  which drive rotors  1602 . Outrigger-mounted motors  1610  are articulated by rotation of the outrigger  1604 . Rotors  1602  are arranged in sets of first and second rotors  1602 , spaced apart on opposite sides of the fuselage  1608 , with first and second rotors  1602  aligned to the chord of the wings  1606 , as shown. First and second thrust assemblies  1609  are arranged with one forward of the wings  1606  and one aft of the wings  1606 , as shown. 
         [0050]    The shape of the illustrated fuselage members  1608  and airfoils  1606 ,  1607 ,  1612  (see  FIGS. 18 ),  1614 ,  1616 , and  1618  are not limitations of the invention. Rather, the outriggers  1604  to two motors  1610  driving rotors  1602 , with two rotors  1602  outboard of the wings  1606  and two thrust assemblies  1609  between fuselage members  1608  represents a novel feature of the invention. The articulation of the two outboard motors  1610  to using the outriggers  1604  is also a novel feature of the invention. The use of inner wing  1607  as a fuel tank is also a novel feature of the invention. 
         [0051]      FIG. 17  is a front elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing  1606  VTOL aircraft  1600  with rotors  1602  on outriggers  1604  of  FIG. 16 , according to a preferred embodiment of the present invention. Landing gear supports  1628  supports skis  1630  for ice and snow landings. In another embodiment, landing gear supports  1628  may support wheels. 
         [0052]      FIG. 18  is a side elevation diagrammatic view illustrating the fifth exemplary embodiment of the fixed-wing  1606  VTOL aircraft  1600  with rotors  1602  on outriggers of  FIG. 16  with a cut-away portion and in a non-flight configuration, according to a preferred embodiment of the present invention. The forward thrust assembly  1609  is shown in a wing-borne flight forward thrust position with a dashed arrow showing the direction of rotation to a vertical flight position. Thrust assemblies  1609  have at least a ninety angular degree freedom of movement. Cowling  1613  can best be seen in this view. The cutaway portion best shows inner wing  1607 . Fuselage  1608  supports vertical stabilizer  1616  which supports rudder  1612 . The rear thrust assembly  1609  and outrigger-mounted motor  1610  are shown in vertical flight positions. 
         [0053]    The embodiments illustrated herein are merely exemplary, and do not define the limits of the invention. In some embodiments, for example, the rotors  102 ,  402 ,  702 ,  1002 ,  1302 , or  1602  may be capable of rotation beyond ninety degrees and may rotate sideways. The limits of the invention are described in the claims below.
The VTOL aircraft of the present invention has fixed-wings which can be monoplane, biplane or tri-plane and tiltable rotors on outriggers which extend from the fuselage and/or wings. The rotors on the outriggers can be driven by engines located in the fuselage or wings via a transmission system such as a shaft, pulley, or pressurized air using pumps. If rotors are driven by jets at the tips, fuel is fed through pipes inside of the outriggers. The rotors and engines can be located at the ends of the outriggers or the rotors may be separate from the engines and tilting only the rotors reduces structural requirements and weight of the aircraft. The rotors can be tilted over ninety degrees from the vertical position forwards and backwards, sideways if needed for lateral movement. The outriggers can be configured in various ways depending upon how many rotors are used and where the engines are located. Placing rotors on outriggers in the spaces least obstructed by the wings and fuselage reduces drag which increases efficiency and also offers a flexible platform for various hybrid designs.