航天器环境工程2018，Vol.35Issue(3)：258-262,5.DOI:10.3969/j.issn.1673-1379.2018.03.010
650mm口径主反射镜组件结构设计
The structural design of a φ650 mm primary mirror subassembly
摘要
Abstract
To improve the in-orbit surface and structural stabilities of the primary mirror for the remote sensing camera, a special design of a 650 mm primary mirror assembly is presented in this paper. The traditional frame support structure is used for the mirror subassembly, and the glue spot is subjected to shear loads in this structure to make a uniform distribution of the thermal expansion of the materials of the mirror with the support structure. The structural analysis of the mirror assembly shows that the optical surface error is 2.30 nm(PV) and 0.42 nm(RMS); the displacement of the mirror vertex is 0.8 μm, and the light axis deviation of the mirror is 0.01″under 1g gravity in the y direction, on which the mirror subassembly is tested. And the optical surface error is 3.02 nm(PV) and 0.56 nm(RMS), respectively under a (20±2) ℃ thermal environment, as complied with the camera thermal requirement on obrit. The simulated natural frequency of the mirror assembly is 164.3 Hz, basically in accordance with the experimental result of 158.0 Hz. After a routine vibration and vaccum outgassing test, the structural displacement is measured to be less than 3 μm and the degree deviation is less than 3″. It is shown that all concerned properties of this large-aperture space mirror meet the design requirements.关键词
主反射镜组件/结构设计/仿真计算/地面环境试验Key words
primary mirror assembly/structural design/simulation calculation/ground environmental test分类
航空航天引用本文复制引用
史姣红,罗世魁,唐璐,罗廷云..650mm口径主反射镜组件结构设计[J].航天器环境工程,2018,35(3):258-262,5.
