长条形空间反射镜及其支撑结构设计

李志来; 徐宏

doi:10.3788/OPE.20111905.1039

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长条形空间反射镜及其支撑结构设计

微纳技术与精密机械 | 更新时间：2020-08-12

- 长条形空间反射镜及其支撑结构设计
- Design of rectangular space mirror and its support structure
- 光学精密工程 2011年19卷第5期页码：1039-1047
- 作者机构：
  
  中国科学院长春光学精密机械与物理研究所,吉林长春 130033
- 作者简介：
- 基金信息：
  
  国家863高技术研究发展计划资助项目(No.2009AA7020107)()
- DOI：10.3788/OPE.20111905.1039
  中图分类号： V475.3;TH703
- 收稿日期：2010-09-02，
  
  修回日期：2010-09-28，
  
  网络出版日期：2011-05-26，
  
  纸质出版日期：2011-05-26
- 稿件说明：
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李志来, 徐宏. 长条形空间反射镜及其支撑结构设计[J]. 光学精密工程, 2011,19(5): 1039-1047

LI Zhi-lai, XU Hong. Design of rectangular space mirror and its support structure[J]. Editorial Office of Optics and Precision Engineering, 2011,19(5): 1039-1047
李志来, 徐宏. 长条形空间反射镜及其支撑结构设计[J]. 光学精密工程, 2011,19(5): 1039-1047 DOI： 10.3788/OPE.20111905.1039.

LI Zhi-lai, XU Hong. Design of rectangular space mirror and its support structure[J]. Editorial Office of Optics and Precision Engineering, 2011,19(5): 1039-1047 DOI： 10.3788/OPE.20111905.1039.

摘要

提出了一种空间反射镜柔性支撑结构

以满足反射镜在重力和温变载荷下对较高面形精度的要求。根据光学设计指标要求确定了反射镜的结构形式

根据该结构形式设计了柔性支撑结构

并利用有限元分析软件对反射镜组件进行了分析和结构优化。分析结果表明

反射镜组件的一阶固有频率达到179 Hz

在

3轴方向1

重力作用下镜面面形误差RMS值分别达到5.06

4.43

7.59 nm;在3个方向1

重力和4 ℃温升耦合作用下

镜面综合面形误差RMS值分别达到6.08

6.32

8.08 nm。实验室静态检测结果表明

反射镜在4℃温变条件下能够保证像质

力学试验结果与理论分析基本吻合;经过力学与热真空环境试验后

反射镜面形变化不明显。分析及试验结果表明

反射镜及其支撑结构设计合理

能够满足空间应用要求。

Abstract

A flexible support structure was proposed to keep the higher surface figure accuracy of space mirrors under gravity and uniform temperature change load cases. According to the optical design requirements

the structural form of a mirror was determined

and then a flexible support structure of the primary mirror was designed. By adopting finite element analysis software

the mirror component was analyzed and its structure was optimized. Analysis results show that the first order natural frequency of the mirror component is 179 Hz

and the surface figure accuracy RMS of the mirror reaches 5.06

4.43 and 7.59 nm when gravity load is applied in the directions of

and

axes

respectively. Furthermore

the integrated surface figure accuracy RMS of the mirror reaches 6.08

6.32 and 8.08 nm respectively under the load cases of gravity in three directions coupled with uniform temperature rise of 4 ℃. Laboratory test results indicate that the mirror can offer a good image quality under the condition of 4 ℃ uniform temperature change

and the mechanical test results are consistent with that of the theoretical analysis. The change of the surface figure accuracy is not obvious after dynamic and thermal vacuum tests. Analysis and experimental results demonstrate that designs of the mirror and its support structure are effective

which can meet the requirements of space applications.

关键词

Keywords

references

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