航天器工程2024，Vol.33Issue(2)：139-143,5.DOI:10.3969/j.issn.1673-8748.2024.02.020
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
黄磊 1杨敏 1车邦祥 1王岩 1李振宇1
作者信息
- 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
- 折叠
摘要
Abstract
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 experi-ments,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Key words
fluid loop/heat radiator/perforation/leakage分类
航空航天引用本文复制引用
黄磊,杨敏,车邦祥,王岩,李振宇..航天器热辐射器MMOD击穿泄漏特性分析及验证[J].航天器工程,2024,33(2):139-143,5.
