空间遥感器大口径反射镜的复合支撑结构

王克军; 董吉洪; 宣明; 张缓缓; 迟春燕; 赵伟国

doi:10.3788/OPE.20162407.1719

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空间遥感器大口径反射镜的复合支撑结构

微纳技术与精密机械 | 更新时间：2020-08-13

- 空间遥感器大口径反射镜的复合支撑结构
- Compound support structure for large aperture mirror of space remote sensor
- 光学精密工程 2016年24卷第7期页码：1719-1730
- 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 130033
  2.中国科学院大学, 北京 100049
  3.吉林建筑大学, 吉林长春 130118
- 作者简介：
  
  王克军(1982-), 男, 山东乐陵人, 硕士, 助理研究员, 2006年、2008年于吉林大学分别获得学士、硕士学位, 现主要从事空间遥感器光机结构设计。E-mail:wangkejun1@163.com E-mail:wangkejun1@163.com
- 基金信息：
  
  国家自然科学基金资助项目(41175208)
- DOI：10.3788/OPE.20162407.1719
  中图分类号： TH751
- 收稿日期：2015-08-03，
  
  录用日期：2015-9-9，
  
  纸质出版日期：2016-07
- 稿件说明：
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王克军, 董吉洪, 宣明, 等. 空间遥感器大口径反射镜的复合支撑结构[J]. 光学精密工程, 2016,24(7):1719-1730.

Ke-jun WANG, Ji-hong DONG, Ming XUAN, et al. Compound support structure for large aperture mirror of space remote sensor[J]. Optics and precision engineering, 2016, 24(7): 1719-1730.
王克军, 董吉洪, 宣明, 等. 空间遥感器大口径反射镜的复合支撑结构[J]. 光学精密工程, 2016,24(7):1719-1730. DOI： 10.3788/OPE.20162407.1719.

Ke-jun WANG, Ji-hong DONG, Ming XUAN, et al. Compound support structure for large aperture mirror of space remote sensor[J]. Optics and precision engineering, 2016, 24(7): 1719-1730. DOI： 10.3788/OPE.20162407.1719.

摘要

针对空间遥感器反射镜对支撑功能的需求

设计了一种应用于空间领域的大口径反射镜复合支撑结构。该复合支撑结构包括A框加切向拉杆的周边支撑和3组whiffletree结构组成的背部支撑。研究了复合支撑的支撑原理和工程实现。基于功能分配和指标分配的理念设计了复合支撑结构。采用有限元分析的手段对设计结果进行了静力学和动力学仿真验证，然后对实际的支撑系统进行了相关的试验测试。试验结果表明，采用复合支撑的反射镜组件在工作状态下的面形精度优于

/50(

=632.8 nm)，镜体刚体位移小于0.01 mm，镜体转角小于2"，质量小于50 kg。整个组件模态分布合理，基频为161 Hz，远高于设计要求的120 Hz。各项仿真和测试结果均表明该复合支撑效果良好，满足空间遥感器对可靠性和稳定性的需求。

Abstract

For requirements of the mirror in a space remote sensor for support function

a compound support structure used in the mirror with a large aperture in the space field was designed. The compound support structure includes a peripheral support composed of an A frame and a tangential pull rod and a back support composed of three groups of whiffletree structures. The support principle and engineering realization of the compound support structure were researched. Then

the design idea of function allocation and index allocation was used to design the compound support structure. The statics and dynamics simulations were carried out on the design result by the finite element analysis

and the relative test was performed on the actual mirror support component. Experimental results show that the surface shape error of the mirror with the compound support structure is better than

/50(

=632.8 nm)

the rigid body displacement of mirror and the dip angle are smaller than 0.01 mm and 2" respectively

and the mass of mirror component is less than 50 kg. Furthermore

the component has a reasonable modal distribution

and the fundamental frequency is 161 Hz

higher than the requirement of 120 Hz. The simulation and test results demonstrate that the compound support structure has good support effects

which meets the demand of space remote sensors for high reliability and high stability.

关键词

Keywords

references

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