大口径反射镜组件温度适应性

刘巨; 董得义; 辛宏伟; 李志来; 张学军; 崔抗

doi:10.3788/OPE.20132112.3169

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大口径反射镜组件温度适应性

微纳技术与精密机械 | 更新时间：2020-08-12

- 大口径反射镜组件温度适应性
- Temperature adaptation of large aperture mirror assembly
- 光学精密工程 2013年21卷第12期页码：3169-3175
- 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,中国,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-激光共性技术研究()
- DOI：10.3788/OPE.20132112.3169
  中图分类号： V447.3;TH703
- 收稿日期：2012-07-17，
  
  修回日期：2012-09-25，
  
  网络出版日期：2013-12-25，
  
  纸质出版日期：2013-12-25
- 稿件说明：
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刘巨董得义辛宏伟李志来张学军崔抗. 大口径反射镜组件温度适应性[J]. 光学精密工程, 2013,21(12): 3169-3175

LIU Ju, DONG De-Xi, XIN Hong-Wei, LI Zhi-Lai, ZHANG Hue-Jun, CUI Kang. Temperature adaptation of large aperture mirror assembly[J]. Editorial Office of Optics and Precision Engineering, 2013,21(12): 3169-3175
刘巨董得义辛宏伟李志来张学军崔抗. 大口径反射镜组件温度适应性[J]. 光学精密工程, 2013,21(12): 3169-3175 DOI： 10.3788/OPE.20132112.3169.

LIU Ju, DONG De-Xi, XIN Hong-Wei, LI Zhi-Lai, ZHANG Hue-Jun, CUI Kang. Temperature adaptation of large aperture mirror assembly[J]. Editorial Office of Optics and Precision Engineering, 2013,21(12): 3169-3175 DOI： 10.3788/OPE.20132112.3169.

摘要

考虑温度适应性是大口径反射镜组件设计过程中的重要因素，本文研究了温度影响空间相机大口径反射镜组件的机理，讨论了进行温度适应性分析与试验的必要性。结合其设计流程，总结了大口径反射镜组件温度适应性分析的方法。采用有限元方法，建立了研究对象的物理模型，进行了结构-热耦合的优化设计，确定了最终设计状态。对优化设计结果进行了在轨状态及地面检测状态的温度适应性分析。结果显示：在轨工作状态下的温度适应范围为4 ℃，温差适应范围为X向5 ℃、Y向4 ℃、Z向7 ℃;地面检测试验状态温度适应范围为3 ℃，温差适应范围为X向4 ℃、Y向3 ℃、Z向4 ℃。在实验室进行了组件均匀温变的温度适应性试验，并与相应分析结果进行对比，结果表明：5 ℃内PV值误差优于4%，RMS值误差优于7%。

Abstract

As the temperature adaptation effects the design process of a large aperture mirror assembly seriously

this paper researches the influence mechanism of temperature on the large aperture mirror assembly and discusses the necessity of temperature adaptation analysis and test. With the design flow of the large aperture mirror assembly given

the temperature adaptation analysis method is summarized. The physical calculation model of the large aperture mirror assembly is constructed by Finite Element Method(FEM). The final design status is confirmed after structural-thermal optimization. The temperature adaptation of the optimal design is analyzed in the orbit environment and on the ground environment. The results indicate that the temperature adaptation in the orbit environment is at the range of 4 ℃ and the temperature distribution demands are 5 ℃

4 ℃ and 7 ℃ in X

Z directions

respectively. Moreover

the temperature adaptation on the ground environment is at the range of 3 ℃

and the temperature distribution demands are 4 ℃

3 ℃ and 4 ℃ in X

Z directions

respectively. The temperature adaptation test of temperature uniform change for the assemblies is performed

and compared with the test results of the corresponding analysis results. It shows that the PV value error is in 4% and the RMS value error is in 7% within a 5 ℃ temperature range.

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Keywords

references

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