航天器热辐射器MMOD击穿泄漏特性分析及验证  

Analysis and Verification of Puncture Leakage Characteristics of Spacecraft Heat Radiator by MMOD

作　　者：黄磊[1] 杨敏 车邦祥 王岩[1] 李振宇 HUANG Lei;YANG Min;CHE Bangxiang;WANG Yan;LI Zhenyu(National Key Laboratory of Spacecraft Thermal Control,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部航天器热控全国重点实验室,北京100094

出　　处：《航天器工程》2024年第2期139-143,共5页Spacecraft Engineering

摘　　要：针对空间站等长寿命载人航天器热辐射器在舱外受微流星体和空间碎片(MMOD)击穿后工质泄漏导致的热控系统失效风险问题,文章对热辐射器被击穿后漏孔的泄漏特性进行了分析,建立了数学计算模型,计算得到了漏孔孔径与泄漏容积速率关系。通过试验,验证了数学模型的准确性,结果表明:当泄漏孔径≤3 mm时,泄漏数学模型能够很好的预测泄漏的速率、压力等特性。可以为应用流体回路热辐射器进行热量排散的低轨航天器设计提供参考。In response to the risk of thermal control system failure caused by refrigerant leakage in the heat radiators of long-life manned spacecraft such as space stations after being penetrated by micro-meteoroid and orbital debris(MMOD),this paper analyzes the leakage characteristics,and a mathematical model is established to calculate the relationship between the aperture and the leakage volume rate.The accuracy of the mathematical model has been verified through experiments,and the results shows that when the leakage aperture is less than 3mm,the model can well predict the leakage rate,pressure and other characteristics well.This can provide reference for the design of low orbit spacecraft,which use fluid loop heat radiators for heat dissipation.

关 键 词：流体回路 热辐射器 穿孔 泄漏 

分 类 号：V423.5[航空宇航科学与技术—飞行器设计]