Abstract: The low orbital altitude of the near Earth satellite makes the satellite have higher detection accuracy. However, the service life of the satellite is restricted by the drag caused by the satellite not completely leaving the atmosphere. The air breathing electric propulsion system is used to extend the life of the satellite. The direct simulatiou Monte Carlo (DSMC) calculation method is used to simulate a two dimensional air breathing electric propulsion model. The wall impact model is set as completely diffuse reflection. On the premise that the inlet diameter of the inlet is maintained at a constant value, the inlet long to longitudinal ratio, outlet cone angle, grid length and grid layer number are changed to explore the inlet performance variation rule under the single action of these influencing factors. Under the premise of single influence rule, genetic algorithm is used to carry out multi objective optimization, and the design parameters of high performance inlet meeting the design requirements are obtained, and the optimal design method of inlet at typical height is studied.

Key words: super low orbit satellite, direct simulation of Monte Carlo, air breathing electric propulsion, multi objective optimization