为了使月基极紫外相机反射镜组件在月球环境下具有良好的力学和热学稳定性，从而保证相机的成像质量，本文针对月基极紫外相机所处的严酷的力学和温度条件，设计了一种满足月球环境的反射镜组件结构.通过对反射镜组件有限元模型的重力分析、热载荷分析、动态刚度分析以及结构强度分析，结果表明反射镜组件的一阶谐振频率达到354 Hz，在1 g重力作用和ΔT=50℃均匀温变作用下镜面综合面形误差RMS值分别达到3.62 nm和2.46 nm，满足反射镜面形要求.最后，通过静力学面形检测、力学试验、温度适应性试验及成像分辨率测试，结果显示反射镜镜面面形精度RMS值优于14 nm，反射镜组件的设计满足总体指标，验证了该方案的合理性.

In order to get fine stability of the optical reflector of space remote sensor under the lunar-based environment of force and thermal constraints, base on the inclement environment of force and thermal constraints where lunar-based extreme ultraviolet camera is under, a reflector subassembly meeting lunar-based environment is designed. The finite element analysis of the reflector subassembly show that the first resonant frequency of the reflector subassembly is 354 Hz, the RMS value is 3.62 nm and 2.46 nm under 1 g gravity and ΔT=50℃ temperature change, the result shows the surface accuracy of reflector meets the needs of imaging quality. At last, through the statics surface accuracy detection, mechanical testing temperature tolerance test and imaging resolution test, the result shows RMS value is less than 14nm and meets the design require. It demonstrates that the reflector subassembly structure is reasonable.