大口径空间反射镜大容差支撑结构设计与优化

郭疆; 朱磊; 赵继; 龚大鹏

doi:10.3788/OPE.20192705.1138

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大口径空间反射镜大容差支撑结构设计与优化

微纳技术与精密机械 | 更新时间：2020-08-13

- 大口径空间反射镜大容差支撑结构设计与优化
- Design and optimize of high tolerance support structure for large aperture space mirror
- 光学精密工程 2019年27卷第5期页码：1138-1147
- 作者机构：
  
  1.吉林大学机械与航空航天工程学院，吉林长春 130022
  2.中国科学院长春光学精密机械与物理研究所，吉林长春 130033
  3.东北大学，辽宁沈阳 110819
- 作者简介：
  
  [ "郭疆 (1976-)，男，新疆石河子人，博士研究生，研究员，2000年、2011年于吉林大学获得学士、硕士学位，主要从事空间遥感成像技术的研究。E-mail:guojiang006@163.com" ]
  [ "赵继 (1959-)，男，吉林蛟河人，教授，博士生导师，1997年于吉林工业大学获得博士学位，主要从事智能精密制造方向研究。E-mail:jzhao@jlu.edu.cn" ]
- 基金信息：
  
  中科院长春光机所大口径光学技术基金资助项目(Y6A912U160)
- DOI：10.3788/OPE.20192705.1138
  中图分类号： V447.1
- 收稿日期：2018-11-20，
  
  录用日期：2018-12-11，
  
  纸质出版日期：2019-05-15
- 稿件说明：
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郭疆, 朱磊, 赵继, 等. 大口径空间反射镜大容差支撑结构设计与优化[J]. 光学精密工程, 2019,27(5):1138-1147.

Jiang GUO, Lei ZHU, Ji ZHAO, et al. Design and optimize of high tolerance support structure for large aperture space mirror[J]. Optics and precision engineering, 2019, 27(5): 1138-1147.
郭疆, 朱磊, 赵继, 等. 大口径空间反射镜大容差支撑结构设计与优化[J]. 光学精密工程, 2019,27(5):1138-1147. DOI： 10.3788/OPE.20192705.1138.

Jiang GUO, Lei ZHU, Ji ZHAO, et al. Design and optimize of high tolerance support structure for large aperture space mirror[J]. Optics and precision engineering, 2019, 27(5): 1138-1147. DOI： 10.3788/OPE.20192705.1138.

摘要

针对传统反射镜无法消除加工及装配应力，长期使用后面形精度下降不能满足使用要求的问题，提出了一种高稳定性空间反射镜支撑结构的解决方案，进行了具有大容差特性的1.5 m口径高精度空间反射镜工程化研究和创制。依据经验和理论，完成了初始反射镜组件构型，反射镜的材料选用RB-SiC，采用三角形背部半开口反射镜轻量化形式和背部三点膜片型柔性支撑结构。以装配误差0.01 mm的9种工况下反射镜的面形RMS变化量最小为目标，利用isight软件对反射镜支撑结构的主要尺寸进行了优化设计。最终完成了轻量化率为82.1%，组件质量为170.23 kg的反射镜的研制。试验结果表明：反射镜在1

重力作用下，面形精度RMS优于0.016

(

=632.8 nm)；加入0.02 mm强迫位移模拟装配误差，面形RMS仍然为0.016

；在20 ℃±5 ℃温变环境下，面形RMS变化量在0.002

范围内；组件一阶固有频率为101.3 Hz。反射镜组件静态刚度、动态刚度、面形精度以及环境适应性满足空间工程应用要求。

Abstract

In a traditional space mirror

the stress of processing and assembling cannot be eliminated and this causes the surface accuracy of the mirror to degrade. In this study

an optimization method for a high-stability support structure for a space mirror was proposed to solve this problem. A 1.5-m aperture high-tolerance and high-accuracy space mirror for engineering applications was fabricated. First

the initial configuration of the mirror subassembly was designed based on theory and experience. The mirror was composed of reaction-bonded silicon carbide. A back-half open triangle was selected for the lightweight structure of the mirror

and a diaphragm-type flexure structure was used to support the mirror. The main dimensions of the supporting structure were then optimized using iSIGHT

and the minimum change of the root mean square (RMS) in nine situations with a 0.01-mm assembly error was chosen as the target. A mirror with a mass of 170.23 kg and lightweight ratio of 82.1% was obtained in 30 months. A series of tests revealed the following: The surface accuracy of the mirror was 0.016

RMS(

=632.8 nm) under 1 g of gravity

and a 0.02-mm forced displacement on the interface of the structure caused no changes. The change scope was 0.002

(RMS) in a (20 ± 5 ℃)temperature environment

and the first-order natural frequency of the subassembly was 101.3 Hz. The static stiffness

dynamic stiffness

accuracy of the surface

and environment adaptability of the subassembly were found to meet the requirements of commercial remote sensing.

关键词

Keywords

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