空间光学遥感器反射镜柔性支撑的设计

王忠素; 翟 岩; 梅 贵; 江 帆; 程志峰

doi:10.3788/OPE.20101808.1833

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空间光学遥感器反射镜柔性支撑的设计

微纳技术与精密机械 | 更新时间：2020-08-12

- 空间光学遥感器反射镜柔性支撑的设计
- Design of flexible support structure of reflector in space remote sensor
- 光学精密工程 2010年18卷第8期页码：1833-1841
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
  2. 中国科学院研究生院北京,100039
- 作者简介：
- 基金信息：
  
  国家自然科学基金资助项目(No.60507003)()
- DOI：10.3788/OPE.20101808.1833
  中图分类号： V443.5;TH703
- 收稿日期：2009-11-16，
  
  修回日期：2010-01-14，
  
  网络出版日期：2010-08-20，
  
  纸质出版日期：2010-08-20
- 稿件说明：
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王忠素, 翟岩, 梅贵, 江帆, 程志峰. 空间光学遥感器反射镜柔性支撑的设计[J]. 光学精密工程, 2010,18(8): 1833-1841

WANG Zhong-su, ZHAI Yan, MEI Gui, JIANG Fan, CHENG Zhi-feng. Design of flexible support structure of reflector in space remote sensor[J]. 光学精密工程, 2010,18(8): 1833-1841
王忠素, 翟岩, 梅贵, 江帆, 程志峰. 空间光学遥感器反射镜柔性支撑的设计[J]. 光学精密工程, 2010,18(8): 1833-1841 DOI： 10.3788/OPE.20101808.1833.

WANG Zhong-su, ZHAI Yan, MEI Gui, JIANG Fan, CHENG Zhi-feng. Design of flexible support structure of reflector in space remote sensor[J]. 光学精密工程, 2010,18(8): 1833-1841 DOI： 10.3788/OPE.20101808.1833.

摘要

为降低光学遥感器反射镜在复杂且恶劣的空间环境下的面形误差

设计了一种柔性支撑结构

使反射镜在具有良好的热尺寸稳定性的同时结构刚度满足力学要求。针对某长圆形光学反射镜组件

通过设置柔性铰链的厚度、最薄处厚度和柔性铰链圆弧半径3个特征参数

对柔性铰链进行合理的结构设计。采用有限元法对反射镜组件在力热耦合状态下的面形精度和结构强度及结构的动态刚度进行仿真分析

结果表明

反射镜面形PV值由350.08 nm降至59.03 nm

RMS值由102.67 nm降至9.11 nm

柔性结构保证了反射镜的热尺寸稳定性

同时满足力学要求。最后

对反射镜组件的力热模拟件进行力学试验

得到的结果显示其3个方向的基频分别达到264 Hz

290 Hz和320 Hz。这些结果表明

该柔性支撑结构设计方案是合理可行的。

Abstract

To reduce the surface deformation of a remote sensor reflector in complex and execrable space environments

a flexible support structure was designed. By defining the thickness

width and radius as design variables

the flexible hinge in an oblong reflector subassembly was optimized. Then

the surface figure precision

structural strength and dynamic stiffness of the reflector subassembly in the thermal-structural coupling state were analyzed with finite element method. Simulation results show that the maximum PV value is decreased to 59.03 nm from 350.08 nm

the maximum RMS value is decreased to 9.11 nm from 102.67 nm and the thermal dimensional stability is ensured by proposed flexible structure. Finally

the thermal-structural simulation subassembly was subject to a mechanical test

and results indicate that the fundamental frequencies of the component in three directions are 264 Hz

290 Hz and 320 Hz

respectively. Analysis and test results demonstrate that the flexible support structure is reasonable.

关键词

Keywords

references

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