一体化太阳敏感器热分析与验证方法  

Thermal Analysis and Verification for an Integrative Sun Sensor

作　　者：莫亚男[1] 张宁[2] 刘庭伟[2] 崔坚[1] 陈然[1] 赵媛[1] 

机构地区：[1]北京控制工程研究所,北京100190 [2]中国航天标准化所,北京100071

出　　处：《空间控制技术与应用》2015年第1期36-40,58,共6页Aerospace Control and Application

基　　金：国家重大专项资助项目

摘　　要：为保证太阳敏感器在进行光电一体化设计后的光学系统热稳定性,满足电子元器件的工作温度降额要求,采取光学模型与热模型相结合的热分析方法,得出了包括光学组件在内的整机温度分布数据.采用温度边界设定结合太阳光外热流的热平衡试验方法对产品实际温度分布情况进行验证,结果表明一体化太阳敏感器在壳体温度达到55℃,且受到1太阳常数太阳光照射时,仍满足设计要求,且测试数据和分析结果吻合.The sun sensor is usually placed on the surface of a spacecraft and receives the radiation of sunlight directly. By adopting the optics-electronics integrative design method,the heat stabilization of optical system and the working temperature of electronic device can be ensured simultaneously. To analyze the temperature distribution of integrative sun sensor,the optical and thermal models are combined.Based on the given temperature boundary condition,the heat of sunlight is also considered when the thermal analysis and thermal verification are carried out. The results show that the working temperature of sun sensor satisfies the thermal design criterion even if the temperature of the shell is 55℃ and the radiation of sunlight is 1 constant. The data of verification are coincident with the analysis results well.

关 键 词：太阳敏感器 热分析 试验验证 

分 类 号：V448[航空宇航科学与技术—飞行器设计]