外露式星载光机电设备热设计的间接验证

刘绍然; 刘百麟; 罗志涛; 杨清波

doi:10.3788/OPE.20182607.1741

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外露式星载光机电设备热设计的间接验证

微纳技术与精密机械 | 更新时间：2020-08-13

- 外露式星载光机电设备热设计的间接验证
- Indirect validation method of thermal design for exposed opto-electro-mechanical instrument on satellite
- 光学精密工程 2018年26卷第7期页码：1741-1748
- 作者机构：
  
  1.中国空间技术研究院通信卫星事业部, 北京 100094
  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.哈尔滨工业大学可调谐激光技术国家级重点实验室, 黑龙江哈尔滨 150001
- 作者简介：
  
  [ "刘绍然(1988-), 男, 安徽亳州人, 工程师, 2008年于中国农业大学获得学士学位, 2011年于中国空间技术研究院获得硕士学位, 主要从事卫星总体和热控制系统方面的研究。E-mail:lsrvv@163.com" ]
- 基金信息：
  
  国家自然科学基金资助项目(11504068);国家自然科学基金资助项目(11404082);国家青年自然科学基金资助项目(61503096)
- DOI：10.3788/OPE.20182607.1741
  中图分类号： V416
- 收稿日期：2017-12-08，
  
  录用日期：2018-1-24，
  
  纸质出版日期：2018-07-25
- 稿件说明：
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刘绍然, 刘百麟, 罗志涛, 等. 外露式星载光机电设备热设计的间接验证[J]. 光学精密工程, 2018,26(7):1741-1748.

Shao-ran LIU, Bai-lin LIU, Zhi-tao LUO, et al. Indirect validation method of thermal design for exposed opto-electro-mechanical instrument on satellite[J]. Optics and precision engineering, 2018, 26(7): 1741-1748.
刘绍然, 刘百麟, 罗志涛, 等. 外露式星载光机电设备热设计的间接验证[J]. 光学精密工程, 2018,26(7):1741-1748. DOI： 10.3788/OPE.20182607.1741.

Shao-ran LIU, Bai-lin LIU, Zhi-tao LUO, et al. Indirect validation method of thermal design for exposed opto-electro-mechanical instrument on satellite[J]. Optics and precision engineering, 2018, 26(7): 1741-1748. DOI： 10.3788/OPE.20182607.1741.

摘要

星载光机电设备兼有光学系统和运动机构的特点，前者温度指标要求高，后者构型复杂并且相对星体其他部分运动，这给热设计的验证带来困难。文章以光机电设备激光通信终端为例，提出了热设计的间接验证方法，即通过地面试验数据修正热分析模型、再由热分析模型预示在轨温度，进而验证热设计。设计了热平衡试验，并根据试验结果修正了模型，修正后的试验模型计算结果与试验结果基本一致，81%的测温点偏差小于5℃，模型较好地反映了真实的热物理状态，其预示的在轨温度可用于验证热设计。对比了轨道计算温度与飞行温度，81%的测温点偏差小于4℃，证明了间接验证方法的正确和有效，满足星载激光通信终端的应用要求。所述的验证方法显著降低了热试验的难度，对多姿态与高温度指标的光机电设备具有借鉴意义。

Abstract

Satellite-borne opto-electromechanical instruments preserve both optical systems and mechanism properties; the former has a strict requirement for temperature

and the latter has a complex structure and is constantly moving. This is a challenge to the test validation of the thermal characteristics. A case study of the indirect validation method of the thermal design for the optical communication terminal is presented. The indirect validation method may be utilized to predict the in-orbit temperature through the thermal analytical model

which is corrected using temperature data in the thermal balance test. The thermal balance test and model correction have been made. Very good correlation was demonstrated between the computed results of the proposed model and the measured test data; a deviation of 81% is less than 5℃. Thus

the model is appropriate for use in validation of thermal design. Comparing the thermal analytical results to the flight results

the deviation of 81% is less than 4℃. This demonstrates the accuracy and the effectiveness of the indirect validation method

and the method meets the application requirements of optical communication terminals on satellites. The proposed indirect validation method greatly reduces the difficulty of thermal testing and is of certain reference value to altitude-varied and high temperature precision opto-electromechanical instruments.

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references

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