空间摄像机热控系统设计

陈立恒; 吴清文; 刘伟奇; 郭亮; 江帆

doi:10.3788/OPE.20122003.0556

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空间摄像机热控系统设计

微纳技术与精密机械 | 更新时间：2020-08-12

- 空间摄像机热控系统设计
- Thermal design for space cameras
- 光学精密工程 2012年20卷第3期页码：556-562
- 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：
  
  国家重大国防科研项目(No.06E030)()
- DOI：10.3788/OPE.20122003.0556
  中图分类号： V447-3;V245.3
- 收稿日期：2011-05-03，
  
  修回日期：2011-07-18，
  
  网络出版日期：2012-03-22，
  
  纸质出版日期：2012-03-22
- 稿件说明：
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陈立恒, 吴清文, 刘伟奇, 郭亮, 江帆. 空间摄像机热控系统设计[J]. 光学精密工程, 2012,(3): 556-562

CHEN Li-heng, WU Qing-wen, LIU Wei-qi, GUO Liang, JIANG Fan. Thermal design for space cameras[J]. Editorial Office of Optics and Precision Engineering, 2012,(3): 556-562
陈立恒, 吴清文, 刘伟奇, 郭亮, 江帆. 空间摄像机热控系统设计[J]. 光学精密工程, 2012,(3): 556-562 DOI： 10.3788/OPE.20122003.0556.

CHEN Li-heng, WU Qing-wen, LIU Wei-qi, GUO Liang, JIANG Fan. Thermal design for space cameras[J]. Editorial Office of Optics and Precision Engineering, 2012,(3): 556-562 DOI： 10.3788/OPE.20122003.0556.

摘要

根据摄像机所处空间环境和结构特点

设计它的热控系统

同时进行了热平衡试验来验证热设计的合理性。首先

总结了摄像机热设计的准则

分析了摄像机所处的空间热环境。然后

对摄像机的各个部分进行了热设计;采用被动热控措施进行热隔离和热疏导

充分利用了摄像机所搭载的卫星平台的热容;采用主动热控措施将温度控制在热控指标范围之内。最后

根据摄像机的热环境和各种工作模式设计了4种极端试验工况

并进行了热平衡试验。试验结果表明

摄像机在存储工况时

其温度与安装面温度相差3℃左右

满足存储温度指标要求;低温工况和高温工况时

其整机温度为-3.1℃和45.7℃

镜头温度为-4.5℃和46.8℃

均满足热控指标要求。试验结果证实设计的空间摄像机热控系统合理可行。

Abstract

A thermal control system for space cameras was designed according to its space environments and structure characteristics. Firstly

the thermal design guidelines of space cameras were summarized

and the thermal environment of a space camera was analyzed. Then

the thermal design of the space camera was carried out. By utilizing the thermal capacitance of a satellite

the passive thermal control was used for thermal isolation and thermal transmission and the active thermal control was conducted to implement the temperature compensation. Finally

four extreme test conditions were designed and thermal balance tests were undertaken according to various work patterns and different thermal environments. The test results show that the temperature difference is 3 ℃ between the space camera and the fitting surface

which meets the system requirements for storage work conditions. Furthermore

the whole space camera temperatures are -3.1 ℃ and 45.7 ℃

the lens temperatures are -4.5 ℃ and 46.8 ℃ in the low temperature and high temperature work conditions

respectively

and they meet the thermal control system requirements. In conclusions

the thermal design of the space camera is feasible and reasonable.

关键词

Keywords

references

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