低倾角圆轨道大口径空间相机热控设计与验证  

Thermal design and verification for large aperture space camera in low-inclination circular orbit

作　　者：张煚[1] 夏晨晖 于峰[1] 宋欣阳[1] 王薇 ZHANG Jiong;XIA Chenhui;YU Feng;SONG Xinyang;WANG Wei(Beijing Institute of Space Mechanics&Electricity,Beijing 100094,China)

机构地区：[1]北京空间机电研究所,北京100094

出　　处：《航天器环境工程》2024年第6期681-689,共9页Spacecraft Environment Engineering

基　　金：国家重点研发计划项目(编号:2021YFC2202102)。

摘　　要：针对某低倾角圆轨道大口径空间遥感相机轨道外热流复杂,光学系统和主支撑结构控温精度要求高的难题,设计了一套综合热控策略。对主支撑结构,融合间接辐射控温技术及高精度离散控温算法,实现了光机结构全周期±0.3℃的高稳定性控温;针对相机内热源,通过合理分配散热面,采取差异化的散热策略,优化部组件布局,合理设置散热通路,特别是对制冷机冷指热端采用散热面耦合均温技术等,实现了高效散热。相机热平衡试验及在轨飞行数据验证了相机热控系统设计的有效性。研究可为同类遥感器的热控设计提供参考。In response to the challenges of complex external heat flow and the stringent temperature control requirements for the optical system and primary support structure of a large aperture space remote sensing camera in a low-inclination circular orbit,a comprehensive thermal control strategy has been developed.The strategy for the primary support structure integrated an indirect radiation technique with a high-precision discrete temperature control algorithm,achieving stable temperature control with a full-cycle variation within±0.3℃for the opticalmechanical structure.To manage internal heat sources,efficient heat dissipation was realized through rational allocation of heat dissipation surfaces,differentiated strategies,optimized component layout,and effective establishment of heat dissipation pathways.A heat dissipation surface coupling temperature equalization technique was particularly effective for the cold and hot ends of the refrigerator.Thermal balance tests and onorbit flight data confirm the efficacy of the camera’s thermal control system design.The research offers a valuable reference for the thermal control design of similar remote sensing instruments.

关 键 词：低倾角轨道 热设计 热平衡试验 在轨验证 间接辐射控温 离散控温 耦合均温 

分 类 号：V443.5[航空宇航科学与技术—飞行器设计]