Thermal analysis of PANSAT electric power subsystem
Victor, Eric L.
Ross, I. Michael
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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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