航天器工程2019，Vol.28Issue(2)：63-71,9.DOI:10.3969/j.issn.1673G8748.2019.02.010
基于相变传热技术的空间瞬时大热耗载荷级联散热设计
Cascade Heat Dissipation Design of Space Large Heat Consumption Load Based on Phase Change Heat Transfer Technology
摘要
Abstract
Aiming at the heat dissipation problem of space kilowattGlevel instantaneous large heat load,a general cascade heat dissipation method is proposed,which is the integration of "flat vapor chamber (VC)+ phase changed material (PCM)+ loop heat pipe (LHP)". The system is mainly passive thermal control,VC with equivalent thermal conductivity ≥2000W/(m·K)is used to enhance heat transfer,and then PCM with 3D printed thermal honeycomb structure is used to enhance heat storage and release.In this paper,the heat dissipation design of a space load with instantaneous heat consumption up to 3000W is carried out.Through thermal analysis and thermal test verification,the results show that the maximum temperature rise of the heat source is 12.5℃ in 45s and 19.6℃ in 60s,the temperature of which can be controlled in the range of 10~40℃.Comparing the modified thermal analysis model with the thermal test results,the abG solute error is about 1℃,and the relative error is 4.85%.The correctness of the design method is verified,which can be used as a reference for thermal design of instantaneous large thermal load of the same kind of space kilowattGlevel.关键词
空间瞬时大热耗/相变/一体化/散热设计Key words
space instantaneous high heat consumption/ phase change/ integration/ heat dissipation design分类
航空航天引用本文复制引用
李新,韩新民,何书通,刘万发,黄金印,彭方汉,王录,孟繁孔,何江..基于相变传热技术的空间瞬时大热耗载荷级联散热设计[J].航天器工程,2019,28(2):63-71,9.基金项目
国家自然科学基金(61705230) （61705230）
