空间遥感器长条形平面镜的背部支撑技术

Backside Support Technique of Rectangular Plane Mirror for Space Remote Sensor

某空间遥感器的大长宽比长条形平面镜的要求是在尽量减小重量的前提下,在工作温度为20±5℃条件下,反射镜的面形误差变化量(Root Mean Square,RMS)值小于λ/50(λ=632.8 nm)。介绍了反射镜材料和支撑结构材料的选择;对反射镜的轻量化及支撑方式进行了分析。根据反射镜的外形特点,增加了镜背的局部宽度,并将其设计成了背部三点支撑形式。通过有限元分析,优化并确定了反射镜及其柔性支撑结构。反射镜位移及面形的分析结果满足设计指标要求。最后,通过力学环境试验测试了反射镜组件模拟件的力学特性,证明该结构能满足设计要求。

The requirement of the large aspect-ratio rectangular plane mirror for a certain space remote sensor is that its weight should be reduced as much as possible and its surface deformation error（RMS）should be less than λ/50（λ=632.8 nm） at the operation temperature of 20±5℃.The material selection of the mirror and its supporting structure is presented.The weight reduction and supporting modes of the mirror are analyzed.According to the shape features of the mirror,the local width of the back of the mirror is increased and the backside of the mirror is designed to have three supporting points.Through finite element analysis,the mirror and its flexible supporting structure are optimized and determined.The analysis results show that the displacement and surface deformation of the mirror meet the design requirements.Finally,the dynamic characteristics of a simulated mirror assembly is tested in a mechanical environment experiment.It is shown that the structure of the mirror meets the design requirements.