摘要
受空间复杂热环境影响,星敏感器姿态测量结果存在轨道周期的光轴热漂移低频误差,因此需对星敏感器进行热设计并进行热稳定性试验验证。文章提出星敏感器热稳定性试验总体方案,并建立热稳定性试验系统;依据航天器真空热环境试验规范,提出星敏感器热稳定性试验判据与条件;针对试验系统误差提出控制方法并针对某型星敏感器开展热稳定性试验,结果表明星敏感器光轴热漂移量为0.114(″)/℃,满足设计指标要求。试验验证了该星敏感器热设计的有效性。
Due to the complex thermal environment in space,the attitude measurement results by the star sensor exhibit low-frequency error of boresight axis thermal drift during the orbital period.Therefore,thermal design and thermal stability test verification for star sensor are required.In this article,an overall scheme for the thermal stability test of the star sensor was proposed,and a thermal stability test system was established.According to the vacuum thermal environmental testing specifications for spacecraft,the criteria and conditions for thermal stability test of star sensor were presented.A control method for the test system error was put forward and a thermal stability test was carried out for a star sensor.The test results indicate that the boresight axis thermal drift of the star sensor is 0.114(")/℃,which meets the reguirements of the design index.The effectiveness of the star sensor thermal design is experimentally verified.
作者
孟小迪
王晓燕
齐静雅
武延鹏
王艳宝
王苗苗
MENG Xiaodi;WANG Xiaoyan;QI Jingya;WU Yanpeng;WANG Yanbao;WANG Miaomiao(Beijing Institute of Control Engineering,Beijing 100190,China)
出处
《航天器环境工程》
CSCD
2024年第1期89-94,共6页
Spacecraft Environment Engineering
基金
民用航天“十三五”预先研究项目“XX星敏感器技术研究”。
关键词
星敏感器
光轴热稳定
真空试验
低频误差
热设计
star sensor
boresight axis thermal stability
vacuum test
low-frequency error
thermal design
