<div class="description">
<p>Spacecraft  thermal-control  subsystems  are  necessary  to  maintain  all  clements  of  a  spacecraft  system  within  their  temperature  limits  for  all  mission  phases.  In  mosl  instances  the  heat  inputs  are  highly  variable  with  time,  requiring  thorough  transicnl- analysis  of  thermal  flow  within  the  spacecraft.  Additionally,  steady-state  thermal  profiles  are  necessary  for  precise  overall  thermal-analysis.  The  objective  of  this  thesis  is  to  develop  a  steady-state  thennal  model  of  the  Electric  Power  Subsystem  (EPS)  and  its  associated  housing  for  the  Petite  Amateur  Navy  Satellite  (PANSAT).  This  task  is  undertaken  to  identify  any  physical  locations  within  the  EPS  where  tcutperaLUres  exceed  the  limits  established  to  protect  sensitive  electronic  components.  Software  generated  steady-state  analysis  using  only  contact- conductances  for  the  EPS  through  the  housing  attachment  is  perfonned.  It  is  shown  that  given  the  geometry  of  the  physical  model,  the  conductive  relations  developed,  and  the  given  boundary  conditions,  the  steady-state  temperature  of  the  EPS  and  its  associated  housing  will  remain  within  limits.
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<br>Subjects: NA</div>
<div class="fn value">
Victor, Eric L.</div>
Internet Archive identifier