Abstract:
CE-1 is the first deep space satellite launched by China. Despite the experience of other DFH-3 satellites in many aspects, the thermal control design is very difficult due to its special thermal environment. The peculiar layout of thermal radiators, the complicity of external heat flux and the variety of detectors and sensors pose severe requirements on the thermal control system and the vacuum thermal test system. A series of system level and sub-system level thermal vacuum tests were carried out for CE-1 in 2005 and 2006, to verify the space environmental test techniques in BISEE. This paper discusses the application of the external heat flux simulation design technique, the bracket design technique and the measurement and control technique in the CE-1 thermal test.
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