吸气式电推进系统可行条件分析

吸气式电推进系统作为有可能实现长寿命超低轨飞行的技术而被关注。根据不同轨道环境条件，采用管状结构进气道、以及机械增压的吸气方式，讨论了吸气式电推进系统所需的可行条件。分析表明，在轨高度180~240km，航天器所需总功耗与迎风面之比需要大于2kW/m2，电推力器比冲需大于4×104m/s，方可满足推阻平衡需求。分析得出，实现吸气式系统在地球轨道的运用，关键技术在于增加气体收集效率并且降低收集功耗，同时电推力器的效率还需进一步提升。

Feasibility analysis of air breathing plasma propulsion system

The air breathing plasma propulsion system has been studied as a potential technology for long life super low altitude flight. According to different orbital environmental conditions, the feasibility of the air breathing plasma propulsion system was discussed by using the tubular inlet and the mechanical pressurization suction method. The analysis shows that the ratio of the total power required by the spacecraft to the windward surface should be greater than 2kW/m2, and that the specific impulse of the plasma thruster should be greater than 4×104m/s, so as to meet the requirements of push drag balance. It is pointed out that in order to realize the application of suction system in earth orbit, the key technology is to increase gas collection efficiency and reduce collection power consumption, while the efficiency of plasma thruster needs to be further improved.