Thermal environment of space radiator will vary widely during Earth-orbital mission; weight and area limitations make it undesirable to design for worst-case conditions; criteria for minimizing radiator capacity; through models, thermal environments were defined for complete range of ascending node locations and solar declinations for typical orbit inclination; radiator was sized for mission requirements and worst average heating orbit; transient performance of environmental control and life support (EC/LS) system utilizing this radiator design was evaluated in generalized computer program. (30888)
Spacecraft radiator analysis
ASME Aviation Space -- Progress Prospects
ASME Annual Aviation and Space Conference ; 1968 ; United States , Beverly Hills, CA Heat problems
1968
9 pages
Conference paper
English
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