空间无排放消耗散热概念及试验验证  

Emission-free evaporative heat dissipation for the use in future space missions:concept and experimental study

作　　者：王玉莹[1] 宁献文[1] 赵欣[1] 曹剑峰[1] 戴承浩 孙冠杰 WANG Yuying;NING Xianwen;ZHAO Xin;CAO Jianfeng;DAI Chenghao;SUN Guanjie(Beijing Key Laboratory of Space Thermal Control Technology,Beijing Institute of Spacecraft System Engineering;China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]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 [2]中国空间技术研究院,北京100094

出　　处：《航天器环境工程》2021年第1期1-6,共6页Spacecraft Environment Engineering

基　　金：载人航天领域预先研究项目(编号:010401);国家自然科学基金项目(编号:11472040);国家留学基金项目(编号:201904980001)。

摘　　要：空间任务中缺乏有效辐射散热通道情况下,消耗型散热是排散航天器废热必不可少的技术途径,但其存在长期应用中资源消耗量大的问题。针对未来长期空间任务,提出无工质排放的消耗型散热概念。首先通过微孔膜蒸发消耗型散热试验,评估该试验系统在不同真空压力下的散热能力;之后基于此设计柔性收集装置,开展微孔膜蒸发‒水蒸气收集联合试验。试验结果表明,微孔膜蒸发可以在无工质排放条件下实现有效散热,散热量随流体进口温度升高而增加,随真空压力升高而线性减小;无排放消耗型散热系统中收集装置的水蒸气吸收速率不小于蒸发速率时,将不会削弱微孔膜蒸发的散热能力。The consumptive heat dissipation is an essential way for the spacecraft thermal management in space missions,especially for spacecraft without efficient radiation area.However,this means a large amount of working fluid consumption in the long-duration space missions,as an important issue for the future deep space explorations.Here,we propose a emission-free heat dissipation concept for the long term use in space missons.Firstly,a series of experiments are conducted based on microporous membrane evaporation,to test the heat dissipation performance of the system under different vacuum backpressures.A flexible vapor collector prototype is built to absorb the evaporated water vapor,and to carry out the emission-free evaporation experiments for the evaporator-collector combination.The test results indicate that the microporous membrane evaporator works efficiently with the flexible vapor collector,and its heat dissipation ability increases with the rise of the fluid inlet temperature,while it linearly decreases with the increase of the backpressure.It is concluded that the heat dissipation ability of the emission-free evaporative heat dissipation system will not be damaged as long as the vapor absorption velocity exceeds the evaporation velocity.

关 键 词：航天器热控 消耗散热 无排放散热 膜蒸发 试验研究 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]