空间科学学报2024，Vol.44Issue(1)：114-121,8.DOI:10.11728/cjss2024.01.2023-yg13
35K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
摘要
Abstract
In order to solve the problem of cryogenic heat dissipation of space infrared detection sys-tem 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 single-level 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 start-up 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Key words
Cryogenic integration system/Loop heat pipe/Pulse tube cooler/Heat transfer performance/Flight test分类
航空航天引用本文复制引用
郭元东,刘思学,张红星,苗建印,赵建福,林贵平..35K空间深低温热传输系统性能天地差异[J].空间科学学报,2024,44(1):114-121,8.基金项目
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 （52106067, 11972040）
