A generalized approach used in the thermal analysis of complex orbiting spacecraft is presented. The approach, consisting of the development of a mathematical model and its refinement, using verification testing, has allowed close predictions of actual spacecraft temperatures during flight. The application of this approach in the analysis of the Injun V (Explorer 40) spacecraft is presented as an example.
Generalized Approach to the Thermal Analysis of Orbiting Spacecraft
Sae Technical Papers
1969 International Automotive Engineering Congress and Exposition ; 1969
1969-02-01
Conference paper
English
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