空间遥感器反射镜组件的设计与有限元分析

摘要

Referring to the design targets of mirror used in a space remote sensor,the support scheme and structure pa-rameter of the mirror were analyzed and optimized, and a mirror structure with a mass of 23.7kg and lightweight ratio of 76.2% was obtained. The support of the primary mirror was designed after determining the basic configuration of the primary mirror, then, a flexible support structure was reasonably designed to satisfy the dynamic and static stiffness as well as the thermal character. The mirror subassembly was exactly analyzed by ABAQUS finite element software, the results indicate that the surface figure accuracy of the mirror has reached RMS 3.66nm under the action of gravity of 1g, and the surface figure accuracy of the mirror has reached RMS 4.16nm under a uniform temperature rise of 4℃, then,and the surface figure accuracy of the mirror has reached RMS 5.51nm under the coupling of gravity of 1g and a uniform temperature rise of 4℃, respectively, and the fundamental frequency of the primary mirror subassembly is 137.51Hz. Obtained results satisfy the requirements of space application.%针对某空间遥感器反射镜的设计指标要求，分析并优化了反射镜的支撑形式和结构参数，得到了质量为23.7kg，轻量化率达到76.2%的反射镜结构。在反射镜基本构型确定的基础上，设计了镜体的支撑结构，通过合理设计柔性卸载结构满足了反射镜结构系统的动静态刚度和热尺寸稳定性要求。采用有限元软件ABAQUS对反射镜组件进行了精确有限元分析，分析结果表明，在1g重力作用下反射镜的面形精度RMS达到3.66nm，在4℃均匀温升载荷作用下反射镜的面形精度RMS达到4.16nm，在1g重力和4℃均匀温升载荷耦合作用下反射镜的面形精度RMS达到5.51nm，反射镜组件的一阶固有频率为137.51Hz。得到的结果显示该反射镜组件完全满足设计指标要求。