一体化星敏感器温度控制措施及试验验证  

Temperature Control Method and Test Verification for Integrated Star Sensor

作　　者：孙鹏[1] 赵欣[1] 刘伟[1] 江海[1] SUN Peng ;ZHAO Xin;LIU Wei;JIANG Hai(Beijing Institute of Spacecraft System Engineering,Beijing Key Laboratory of Space Thermal Control Technology,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,空间热控技术北京市重点实验室,北京100094

出　　处：《航天器工程》2018年第2期119-123,共5页Spacecraft Engineering

摘　　要：针对一体化有源像元(APS)星敏感器的高精度高稳定温度要求,文章提出了从热扰动源波动控制、热量传递路径设计和高精度温度控制参数选择3个方面对星敏感器进行热设计的方法。以太阳同步轨道卫星为例,针对(20±1)℃的温度及稳定度要求,对3台星敏感器集中布局的情况进行分析,最终达到了星敏感器接口温度波动在1℃以内的效果。同时,采用地面等效热平衡试验验证了该方法的有效性,可为后续卫星星敏感器热设计提供参考。In response to the high precision and high stability temperature requirement of the integrated active pixel sensor(APS)star sensor,a thermal design method is taken with the heat disturbance source control,heat transfer path design and high precision temperature control parameter chosen.Based on the sun-synchronous satellite and the(20±1)℃temperature and stability control requirement,analysis is carried out for the three centralized layout star sensors.The thermal analytic result shows that the temperature fluctuation of star sensor interface is less than 1℃.Furthermore,an individual test is carried out for the star sensor.The thermal balance test result confirms that the thermal design is correct and is worth for the other star sensor thermal design.

关 键 词：卫星 一体化星敏感器 高精度高稳定度 热设计 热平衡试验 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]