针对空间遥感器反射镜组件的结构复杂性和高性能需求, 对空间遥感器反射镜组件的设计方法进行了研究。提出了一种经验设计、拓扑优化与尺寸参数优化相结合的设计方法, 该方法可使设计结果快速收敛, 获得最优化的设计结构。采用该方法完成了某空间遥感器反射镜组件的结构设计, 通过有限元分析的手段得到了表征反射镜成像质量的RMS值, 同时对整个反射镜组件进行了动力学分析计算, 最后利用环境试验对有限元分析结果的正确性和设计的合理性进行了验证。结果表明: 在重力载荷、温度载荷、镜面加工残差和装配误差的综合影响下, 反射镜组件面形误差RMS值满足使用要求; 整个结构有一个好的动态刚度和合理的模态分布, 反射镜组件动态性能优良, 满足使用要求。针对反射镜组件的设计, 该设计方法是一种有效的、可靠的设计方法。

Based on the structural complexity and high performance requirements of space remote sensor reflector component, the design method of space remote sensor reflector component was studied. A method which was a combining method with the experience design, the topology optimization design and the size parameter optimization design was put forward, which can make the design result fast convergence, getting the optimal design structure. A reflector component structure design of a space remote sensor was achieved with this method, by means of the finite element analysis techniques, the shape error variation RMS and PV of optical reflector component which characterized the image quality of the component were got, and dynamic simulation calculation was carried out. Finally, the correctness of the finite element analysis results and the rationality of the design were validated by environmental testing. The test results show that the RMS meet the design index under the comprehensive influence of gravity load, thermal load which is in the control range, reflector surface machining residual error and assembly error, and that the overall structure has a high enough dynamic stiffness and reasonable distribution of modal, the dynamic performance of the reflector component is good and meets the application requirement. In view of the reflector components design, this method is an effective and reliable design method.