环月轨道一体式星敏感器热设计及仿真验证

Thermal design of an integrated star sensor on lunar orbit with simulation validation

文章提出了一种适用于环月轨道条件下的一体式星敏感器的复合热设计方案。一体式星敏感器自身热耗集中,在环月轨道条件下受太阳辐射和月球红外辐射共同影响,散热条件恶劣。利用热管、热控涂层、多层和电加热器等热控措施相结合的方法,解决了环月轨道条件下的一体式星敏感器的散热问题。通过仿真分析,星敏感器最高温度36.7℃,满足单机温度要求。

A composite design for the thermal management of an integrated star sensor on lunar orbit is proposed.On the lunar orbit, the thermal condition of the integrated star sensor is determined by the solar radiation, the infraredradiation of the lunar surface and the concentrated heat load of the star sensor. As the result, the thermal management ofthe star sensor is extremely difficult. The heat dissipation of the star sensor is realized through the combined actions ofthe heat pipe, the thermal control coating, the MLI and the electric heater. The thermal simulation is performed to verifythe design. The result shows that the maximum temperature of the star sensor is 36.7℃, which satisfies the temperaturerequirement of the star sensor.