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The purpose of satellite thermal control design is to maintain all the elements of a spacecraft system within their temperature limits for all mission phases. The thermal analysis model for Low Earth Orbit satellite payload level simulation is established by considering thermal vacuum test environment condition, thermal vacuum chamber configuration, and satellite`s payload inner thermal environment. The established thermal analysis model is used to determine thermal vacuum test conditions and test case requirements.

Preliminary Thermal Analysis for LEO Satellite Optical Payload's Thermal Vacuum Test