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