中国空间科学技术

中国空间科学技术 ›› 2024, Vol. 44 ›› Issue (5): 57-65.doi: 10.16708/j.cnki.1000-758X.2024.0073

• 论文 • 上一篇    下一篇

基于钎焊工艺的环路热管耦合系统设计及验证

孟恒辉，徐亚威，韩东阳，刘鑫，耿利寅，张庆君，刘立平，张红星，王玉莹   

  1. 1 北京空间飞行器总体设计部，北京100094
    2 航天器热控全国重点实验室，北京100094
    3 北京卫星制造厂有限公司，北京100094
    4 中国空间技术研究院 遥感卫星总体部，北京100094
  • 出版日期:2024-10-25 发布日期:2024-10-21

Design and verification of loop heat pipe coupling heat system based on brazing technology

MENG Henghui，XU Yawei，HAN Dongyang，LIU Xin，GENG Liyin，ZHANG Qingjun，LIU Liping，ZHANG Hongxing，WANG Yuying   

  1. 1 Beijing Key Laboratory of Space Thermal Control Technology，Beijing 100094，China
    2 National Key Laboratory of Spacecraft Thermal Control，Beijing 100094，China
    3 Beijing Spacecraft Co.，Ltd.，Beijing 100094，China
    4 Institute of Remote Sensing Satellite，China Academy of Space Technology，Beijing 100094，China
  • Published:2024-10-25 Online:2024-10-21

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摘要： 随着航天技术的发展，航天器的功能集成度提升，对系统散热要求越来越高。环路热管作为一种两相态高效传热部件，具备远距离、逆重力、布局灵活等特点，常应用于单一热源下的定向热量传输；对于多点热源的复杂环境，环路热管系统稳定性差，一般很难适应。针对复杂空间热流下多点分散热源的散热需求，设计了一种基于钎焊工艺的环路热管强耦合热管理系统，对关键耦合参数进行了敏感性分析，并开展了相关试验，验证了界面低热阻、强耦合等关键技术的可行性，提升平台散热能力达52%。环路热管实现了在陆地探测四号01星载荷舱上的应用，为国际首次在平台系统的大规模应用，载荷舱散热能力由4kW提升到6kW，为大功率固态放大器提供0~20℃在轨温度环境。环路热管突破了在平台应用的约束限制，为后续环路热管的热耦合系统设计提供借鉴。

关键词: 环路热管, 航天器, 热耦合, 换热, 热管理, 钎焊

Abstract: With the development of aerospace technology，the functional integration of spacecraft has been improved，and the complexity of research and development has increasingly high requirements for system heat dissipation.As a two-phase high-efficiency heat transfer component，loop heat pipes（LHPs）have the characteristics of long distance，anti-gravity，and flexible layout，which are often used for directional heat transfer under a single heat source.For complex environments with multiple heat sources，LHP systems have poor stability，which are generally difficult to adapt to.A strong coupling heat management system for LHPs based on brazing technology is designed to meet the heat dissipation requirements of dispersed heat sources under complex spatial heat flux.Sensitivity analysis of key coupling parameters is conducted，and relevant experiments are conducted to verify the feasibility of key technologies such as low thermal resistance and strong coupling at the interface.The platform's heat dissipation capacity is improved by 52%.LHPs，having been applied to payload module of the Land Exploration Satellite-4（LEX-4），which is the first large-scale application in the platform system in the world，improve heat dissipation capacity of the payload module from 4kW to 6kW，providing an on-orbit temperature environment of 0 - 20℃ for the high-power solid-state amplifier.LHP breaks through the restriction of platform application，which provides reference for the design of thermal coupling systems for LHP in the future.

Key words: loop heat pipe, spacecraft, thermal coupling, heat exchange, thermal management, brazing