35 K空间深低温热传输系统性能天地差异  

Investigation on Performance Difference of 35 K Cryogenic Heat Transfer System in Ground and Space Environment

作　　者：郭元东 刘思学 张红星[2] 苗建印[2] 赵建福[4,5] 林贵平 GUO Yuandong;LIU Sixue;ZHANG Hongxing;MIAO Jianyin;ZHAO Jianfu;LIN Guiping(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191;Beijing Key Laboratory of Space Thermal Control Technology,Beijing Institute of Spacecraft System Engineering,Beijing 100094;School of Mechanical Engineering,Tianjin University,Tianjin 300072;Key Laboratory of Microgravity,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049;International Innovation Institute,Beihang University,Hangzhou 311115)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]北京空间飞行器总体设计部空间热控技术北京市重点实验室,北京100094 [3]天津大学机械工程学院,天津300072 [4]中国科学院力学研究所微重力重点实验室,北京100190 [5]中国科学院大学工程科学学院,北京100049 [6]杭州市北京航空航天大学国际创新研究院,杭州311115

出　　处：《空间科学学报》2024年第1期114-121,共8页Chinese Journal of Space Science

基　　金：国家自然科学基金项目(52106067,11972040);中国科协青年人才托举工程项目(2023 QNRC001);卓越青年科学基金项目(2020-JCJQ-ZQ-042)共同资助。

摘　　要：为了解决空间红外探测系统的深低温散热问题,保证红外探测器的低温工作环境,基于脉冲管制冷机和深冷环路热管,设计研制了一套35 K温区的深低温获取与热传输集成系统.该系统由一套35 K温区氖工质深冷环路热管、两台35 K温区脉冲管制冷机、一台150 K温区脉冲管制冷机、隔热冷屏、测温/加热组件、控制系统等组成.完成了地面单机级、整星级热真空测试,并于2020年完成空间飞行测试.在地面单机试验中开展了水平姿态和逆重力恶劣姿态下的传热测试,保证了空间微重力下必定能稳定工作;整星级测试验证了系统在卫星平台散热工况下的工作特性,空间飞行测试获得了系统的空间微重力下的工作性能.本文分析了系统在上述不同阶段的热性能,包括超临界启动特性,稳态运行性能等,验证了相关设计的正确性,重点对比了不同阶段的性能差异,分析其可能的原因.In order to solve the problem of cryogenic heat dissipation of space infrared detection system and ensure its cryogenic operating environment,an integrated system of cryogenic acquisition and heat transfer in 35 K temperature range was designed and developed based on pulse tube cooler and cryogenic loop heat pipe.The system consists of a neon cryogenic loop heat pipe,two sets of pulse tube cooler in 35 K temperature range,one pulse tube cooler in 150 K temperature range,thermal insulation screen,temperature measurement/heating components,control system.It has completed ground singlelevel and satellite-level thermal vacuum tests,and completed space flight tests in 2020.Heat transfer tests under horizontal attitude and anti-gravity conditions were carried out in the ground stand-alone test to ensure that the system could work stably in space microgravity.The whole-satellite test verified the working characteristics of the system under the heat dissipation condition of the satellite platform,and the space flight test obtained the working performance of the system under space microgravity.This paper introduces the thermal performance of the system in different stages,including supercritical startup characteristics,steady-state operation performance,etc.The results have verified the correctness of relevant design,and this paper focuses on comparing the performance differences in different stages,and analyzes the possible reasons.

关 键 词：深低温集成系统 环路热管 脉冲管制冷机 传热性能 飞行试验 

分 类 号：V524[航空宇航科学与技术—人机与环境工程]