星载低温光学系统热控设计与飞行验证  

Thermal control design and flight test of a satellite-borne cryogenic optical system

作　　者：刘庆志[1] 易桦[1] 江海[1] 刘银年[2] LIU Qing-zhi;YI Hua;JIANG Hai;LIU Yin-nian(Beijing Institute of Spacecraft System Engineering,Beijing Key Laboratory of Space Thermal Control Technology,Beijing 100094,China;Shanghai Institute of Technical Physics,Chinese Academy of Sciences,Shanghai 200083,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 [2]中国科学院上海技术物理研究所,上海200083

出　　处：《中国光学（中英文）》2023年第3期542-549,共8页Chinese Optics

基　　金：实践九号卫星国家重大科技专项工程。

摘　　要：星载长波红外相机工作时需要将整个光学系统的温度降低至-20℃以下,以减少背景红外辐射的影响。在弱导热连接结构设计的基础上,研制了Ω型柔性遮阳装置,通过直接辐冷方式实现了光学系统的低温设计;研制了鸟笼式三维导热带,实现了主镜筒的均温设计。作为国内首个在空间领域应用的低温光学系统随实践九号B星进行了在轨飞行试验,结果表明,整个光学系统温度可长期保持在-35℃~-20℃,主镜筒圆周温度差小于4℃。该热控设计方法简单有效,可以为类似星载红外光学系统的热设计提供参考。In order to reduce influence of background infrared radiation,the temperature of the whole optical system should be below−20°C for satellite-borne long-wave infrared imagers working in orbit.On the base of the weak heat conduction structure,aΩtype flexible sunshield made of MLI was developed and a cryogenic optical system was achieved through direct radiation cooling.Cage-like three-dimensional heat conduction straps made of copper were developed and an isothermal design for the body tube was realized.The cryogenic optical system applied to space remote sensing was used for the first time in China when it was tested in orbit with SJ-9B satellite.The results showed the temperature of the whole optical system could be maintained at−35°C~−20°C all the time,and the temperature difference in the body tube was no more than 4°C.All flight test data met the temperature requirement of the long-wave infrared imager.This thermal control method is simple and effective,which can provide a reference for the thermal design of similar satellite-borne infrared optical systems.

关 键 词：低温光学系统 弱导热 柔性遮阳装置 鸟笼式导热带 飞行验证 

分 类 号：TK124[动力工程及工程热物理—工程热物理]