摘要
航天器的热控技术在空间应用中至关重要。以探月需求为背景,基于逐层计算法建立了航天器多层绝热材料性能仿真模型,并通过实验进行了验证。对用内热外冷模型变密度填充方式改善多层绝热性能的机制和改善幅度进行了研究。结果表明变密度多层绝热相对于均匀密度多层绝热的漏热量可以减少37.3%。分析了冷边界温度、热边界温度和真空度等因素对绝热性能的影响。
The spacecraft thermal control technology is very important in space applications. Based on the demand of lunar exploration,a layer-by-layer calculation method is used to establish a performance simulation model of the spacecraft’s multi-layer thermal insulation materials,which is verified by experiments. For the model that internal temperature is lower than external,the mechanism and the improvement magnitude of thermal insulation performance by variable density filling method were studied. The calculation results show that the heat leakage of variable density multilayer insulation can be reduced by 37.3% compared to the conventional uniform density filling method. In addition,the effects of cold boundary temperature,hot boundary temperature and vacuum on the thermal insulation performance were also analyzed.
作者
徐夏凡
陈六彪
郑建朋
王俊杰
XU Xiafan;CHEN Liubiao;ZHENG Jianpeng;WANG Junjie(State Key Laboratory of Technologies in Space Cryogenic Propellants,Technical Institute of Physics and Chemistry,CAS,Beijing 100190,China;Beijing Institute of Aerospace Control Devices,Beijing 100854,China;University of Chinese Academy of Sciences,Beijing 100049,China)
出处
《真空与低温》
2020年第4期295-300,共6页
Vacuum and Cryogenics
基金
国家自然科学基金(U1831203)
国家重点研发计划项目(2018YFB0504603)
中国科学院前沿科学重点研究计划(QYZDY-SSW-JSC028)
航天低温推进剂技术国家重点实验室基金(SKLTSCP1903)。
关键词
变密度
多层绝热
漏热
航天器热控技术
variable density
multi-layer insulation
heat leakage
spacecraft thermal control
