发动机内剩余推进剂排放对卫星表面污染的研究

STUDY OF SATALLITE SURFACE COMTAMINATION OF REMAINDER PROPELLANT EXHAUSTED FROM AN ENGINE

应用真空物理的相关理论，分析了在高空超高真空环境中，发动机二次启动前推进剂排放及其在空中迁移的物理过程，给出模型假设和模拟方程，并针对此真空环境及物理过程应用合适的计算方法对方程进行求解．最后计算了推进剂的排放对卫星造成的污染，给出计算域内浓度变化的非定常过程及卫星表面不同时刻的最大污染量，为推进剂排放方案的实施与否提供理论依据．

The physical processes of exhausting propellant and its migrating in space before the secondary startup of an engine in the high altitude and super-vacuum environment have been analyzed by using the vacuum physical theory. The assumptions used in the model and equations are given. An appropriate numerical method is developed to solve the equations and to conduct the computer simulation related to the physical process at the condition of vacuum. The contamination on satellite caused by the exhausting propellant is calculated. The unsteady process of concentration variation as well as the maximum contamination on satellite surface at different time is obtained. The theoretical criterion is provided for performing the propellant exhausting scheme desired.