Structural design of 1 m diameter space mirror component of space camera

XU Hong; GUAN Ying-jun

doi:10.3788/OPE.20132106.1488

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Structural design of 1 m diameter space mirror component of space camera

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- Structural design of 1 m diameter space mirror component of space camera
- Optics and Precision Engineering Vol. 21, Issue 6, Pages: 1488-1495(2013)
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所 &nbsp
  2. 长春工业大学机电工程学院
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20132106.1488
  CLC： V447.3
- Received：26 April 2012，
  
  Revised：03 July 2012，
  
  Published Online：20 June 2013，
  
  Published：15 June 2013
- 稿件说明：
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徐宏关英俊. 空间相机1m口径反射镜组件结构设计[J]. 光学精密工程, 2013,21(6): 1488-1495

XU Hong GUAN Ying-jun. Structural design of 1 m diameter space mirror component of space camera[J]. Editorial Office of Optics and Precision Engineering, 2013,21(6): 1488-1495
徐宏关英俊. 空间相机1m口径反射镜组件结构设计[J]. 光学精密工程, 2013,21(6): 1488-1495 DOI： 10.3788/OPE.20132106.1488.

XU Hong GUAN Ying-jun. Structural design of 1 m diameter space mirror component of space camera[J]. Editorial Office of Optics and Precision Engineering, 2013,21(6): 1488-1495 DOI： 10.3788/OPE.20132106.1488.

摘要

针对1 m口径空间相机反射镜的设计要求，提出了一种新的反射镜柔性支撑结构。以材料选择、径厚比、支撑点数量和位置、轻量化结构形式等为设计变量，以自重作用下反射镜面形精度rms值为目标函数，优化设计了一种背部开口、三角形轻量化孔、背部三点支撑的SiC空间反射镜结构，同时提出了一种反射镜柔性支撑结构。对反射镜在光轴水平状态下进行装调检测时影响反射镜面形精度的柔性支撑结构参数进行了灵敏度分析，找到了影响反射镜面形精度的结构参数。对反射镜组件动、静态特性和热特性进行了有限元分析，分析结果表明，光轴水平方向重力载荷作用下反射镜面形精度rms达到 5.6 nm，4 ℃均匀温升工况下反射镜面形rms为2.7 nm，反射镜组件一阶固有频率为192 Hz。最后，进行了反射镜组件的动力学测试试验，测得反射镜组件一阶固有频率为197 Hz，最大响应应力为181 MPa，验证了有限元分析的准确性。得到的结果显示该反射镜组件完全满足设计指标要求。

Abstract

A novel flexible support structure for the 1-m primary mirror of a space camera was introduced. By taking the material selection

diameter-thickness ratio

number and positions of support points

and lightweight forms as design variables and the surface figure accuracy rms of the mirror under the self-weight as objective function

a kind of back opening SiC space mirror with triangle lightweight holes and three-point support on the back was designed optimally. Then

the flexible support structure was designed for the primary mirror. Through sensitivity analysis

the parameters of flexible support structure that effect on rms of mirror were found when its optical axis was on the horizontal state. By using finite element method

the dynamic and static stiffnesses as well as thermal character of the primary mirror subassembly were analyzed. The results indicate that surface accuracy of the mirror has reached rms 5.6 nm and 2.7 nm under gravity perpendicular to optical axis and a uniform temperature rise of 4 ℃

respectively

and the fundamental frequency of the primary mirror subassembly is 192 Hz. Finally

dynamics test was performed in the laboratory

experimental results indicate that the first-order natural frequency is 197 Hz and the maximum stress is 181 MPa

which verifies the accuracy of FEA. Obtained results satisfy the requirements of space application.

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references

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Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun 130033, China

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