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In this study, a thermal control research is carried out for light off-axis Space optical remote sensor in the sun-synchronous orbit, and a thermal control system is designed to meet the requirements of lightweight and low power consumption. Firstly, the study analyzes the characteristics of the remote sensor, including the analysis on Space environment, the analysis on structural features of complete machine and the calculation of thermal control indexes. Secondly, based on general thought of thermal control and analysis on power consumption this study targetedly designs a thermal control system. Thirdly, this study carries out the finite element simulation and analysis for the design of thermal control in extreme low temperature and high temperature. Finally, thermal balance test is operated on remote sensor in the same working conditions. Test result indicates that: in extreme working conditions, the temperature of optical structure of remote sensor can be stable at 20±0.6℃; temperature difference in different directions is less than 1℃; the average long-term power consumption in the cycle of orbit is not more than 47.70W, which meet the thermal control indexes of complete machine and average power consumption requirement in cycle of orbit, showing that the thermal control design of the Space optical remote sensor is reasonable and feasible.
sun-synchronous orbit, space optical remote sensor, thermal control design, thermal balance test
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