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

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.