低轨道遥感相机光机热一体化分析及优化设计  

Integrated Opto-mechanical-thermal Analysis and Optimization Design of a Low-Orbit Remote Sensing Camera

作　　者：刘朋朋 靳利锋[1] 赵慧 李妥妥[1] LIU Pengpeng;JIN Lifeng;ZHAO Hui;LI Tuotuo(Beijing Institute of Space Mechanics and Electrictiy,Advanced Optical Remote Sensing Technology Key Laboratory,Beijing 100094,China)

机构地区：[1]北京空间机电研究所先进光学遥感技术北京市重点实验室,北京100094

出　　处：《红外技术》2022年第6期614-621,共8页Infrared Technology

基　　金：国家自然科学基金资助项目(11874087)。

摘　　要：低轨道卫星热环境复杂恶劣,对遥感相机光机结构的热性能提出了严格要求。本文提出了一种基于在轨温度场的光、机、热一体化仿真分析方法,以某低轨道卫星相机为例,分别采用Thermal Desktop、MSC Patran/Nastran、Code V构建热分析模型、结构有限元分析模型、光学分析模型,分析得出了相机单次成像时间内最极端工况下各反射镜的平移、倾斜及镜间距变化量等结构变形特性,计算了光学系统MTF的变化,并剖析了系统传函的主要影响因素。然后从主承力结构的结构参数出发进行了优化设计,优化结果表明主承力结构线胀系数在(5~5.5)×10^(-6)时系统热特性最优,系统传函满足指标要求。The complex and harsh thermal environment of low-orbit satellites necessitates strict requirements for theperformance of the optical-mechanical structure of remote sensing cameras.In this study,an integratedopto-mechanical-thermal simulation analysis method based on an on-orbit temperature field is proposed by using alow-orbit satellite camera as an example.Thermal desktop,MSC Patran/Nastran,and Code V are used toconstruct the thermal,structural finite element,and optical analysis models,respectively.The structuraldeformation characteristics,including the shift,tilt,and distance of each mirror in the most extremeconditions of single camera imaging time,are obtained.Changes in the MTF of the optical system are analyzed and the primary influencingfactors of the system transfer function are determined.Subsequently,optimization design is performed based on the structuralparameters of the primary force-taking structure.The optimization results show that the thermal characteristics ofthe system are optimal when the linear expansion coefficient of the primary force-taking structure ranges from 5.0e-6 to 5.5e-6,and the system transfer functionmeets the target requirements.

关 键 词：低轨道 光机结构 无热化设计 光机热一体化分析 MTF 

分 类 号：TN216[电子电信—物理电子学]