宇航学报

宇航学报 ›› 2021, Vol. 42 ›› Issue (6): 798-806.doi: 10.3873/j.issn.1000-1328.2021.06.014

• 环境试验与器件 • 上一篇    

航天分散热源控温用环路热管设计及飞行应用

杨涛，赵石磊，高腾，赵振明，赵宇，李春林   

  1. 北京空间机电研究所，北京100094
  • 收稿日期:2021-01-25 修回日期:2021-03-04 出版日期:2021-06-15 发布日期:2021-07-23
  • 基金资助:
    国家重大科技专项工程

Design and In orbit Application of Temperature Controlled Loop Heat  Pipe for Aerospace Distributed Heat Sources

YANG Tao, ZHAO Shi lei, GAO Teng, ZHAO Zhen ming, ZHAO Yu, LI Chun lin   

  1. Beijing Institute of Space Mechanics & Electricity, Beijing 100094, China
  • Received:2021-01-25 Revised:2021-03-04 Online:2021-06-15 Published:2021-07-23

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摘要： 为满足国家高分专项遥感卫星焦面电路的力热稳定性要求，提出并设计了一种用于分散式热源精密控温的改进型环路热管(LHP)，既实现了狭小空间内对多片焦面CCD器件的统一恒温控制，又兼顾了焦面结构与卫星舱板间的力学解耦功能。地面测试结果表明：该LHP的热负载携带能力及对分散式热源的精确控温效果良好。2015年9月份，将该控温用LHP成功应用于GF 9卫星遥感器CCD器件的飞行控温，截止目前已在轨运行超60个月，受控的4片CCD器件温度稳定性达±0.7 ℃/年，证明了该控温用LHP设计方法的正确性及工程可实现性，同时实现了我国自研控温用LHP在航天微重力环境下的首次长寿命应用。本文LHP的设计方法和在轨飞行数据，对后续LHP在航天热控领域的应用具有一定的参考价值。


关键词: 环路热管, 分散热源, GF 9卫星CCD器件, 恒温控制, 飞行应用

Abstract: Loop heat pipe (LHP), as an advanced thermal control technology, has been widely used in spacecraft thermal control system and has a broad development prospect. However, due to the inherent defects of the traditional LHP, it is difficult to accurately control the temperature of the distributed heat sources in an aerospace electronic system. Aiming at the distributed CCD device of the GF 9 satellite remote sensor, a temperature control LHP structure which is different from the traditional LHP structure has been presented, and a unified and effective heat management system which can accurately control the temperature of four CCD devices has been realized. The results show that the LHP has good heat transfer capability and tight temperature control effect of the distributed heat sources. In September 2015, the LHP was successfully applied to the CCD devices’ temperature control system of GF 9 satellite remote sensor in orbit. Up to now, the LHP has been running for more than 60 months in space, and the temperature stability of the four CCD devices is achieved up to ± 0.7 ℃/year. This is the first successful application of China’s homemade LHP in the space microgravity environment. The design method and flight data of the LHP will have a great reference value for the subsequent application of LHP in the spacecraft temperature control field.


Key words: Loop heat pipe, Distributed heat source, GF 9 satellite CCD device, Constant temperature control, Application in orbit.

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