<div class="description">
<dl><dd>Thesis advisor(s): I. M. Ross</dd>
<dd>"September 1994."</dd>
<dd>Thesis (M.S. in Astronautical Engineering) Naval Postgraduate School, September 1994</dd>
<dd>Bibliography: p. 191</dd>
<dd>The thermal design of a spacecraft ensures proper heat transfer so all components and subsystems remain within prescribed temperature limits during all aspects of the spacecraft's mission. This thesis develops a point to-point heat flow model of the Electrical Power Subsystem (EPS) and its associated housing for the Petite Amateur Navy Satellite (PANSAT). This analysis was performed to identify physical locations in the EPS where temperatures may exceed the limits established to protect sensitive electronic components, and to define the expected environment of the batteries. The Integrated Thermal Analysis System (ITAS) and a Steady State Thermal Analyzer and Model Builder were used to perform steady state and transient analyses on the EPS: analysis of the batteries was performed using ITAS only. The simulated transient temperatures within the EPS housing remained within limits, but the batteries exceeded specifications. It is suggested that a passive thermal control technique be adapted for the batteries and its design be experimentally validated before flight</dd>
<dd>Mode of access: World Wide Web</dd>
<dd>System requirements: Adobe Acrobat Reader</dd>
<dd>THERMAL ANALYSIS, NICKEL CADMIUM BATTERIES, MILITARY SATELLITES, ELECTRIC POWER PLANTS, ELECTRIC BATTERIES, HEAT TRANSFER, STEADY STATE, OPTICAL PROPERTIES, SPACECRAFT, ELECTRONIC EQUIPMENT, THESES, GATES(CIRCUITS), RADIATIVE TRANSFER, SOLAR CELLS, PRINTED CIRCUIT BOARDS</dd></dl><br>Subjects: Astronautical Engineering</div>
<div class="fn value">
Patterson, Sheila A.</div>
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