Abstract
A large deployable antenna for a communication satellite requires sophisticated thermal control to satisfy the temperature requirements for electrical characteristics, and its performance must be confirmed by a thermal balance test. The results of a tradeoff study of the thermal control method for an antenna conducted in an effort to meet temperature requirement demands indicate that the thermal design of an antenna system can be accomplished by using passive thermal control techniques and heaters in spite of the large and complicated structure. Antenna system thermal balance tests are limited by the volume of the space simulation chamber. To overcome this problem, we introduce a two-step thermal design verification method consisting of component level tests and a whole antenna system level test. This paper describes the thermal control method, the thermal design verification method, and the predicted antenna temperatures in a geostationary orbit obtained from the verified thermal analytical model.
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