针对星际探测任务中燃料最省小推力转移轨道问题，提出一种基于标称轨道的快速设计方法。
A novel rapid method to design optimal-fuel interplanetary trajectory for low-thrust propulsion is presented based on normal trajectory approach.
针对近距离相对运动的轨道控制问题，提出用常值小推力完成最优转移的方法。
An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.
分析认为PPT是一种先进的小推力动力装置，特别适合于微小卫星的轨道转移、姿态控制、位置保持以及星座编队飞行。
It was showed that PPT was a kind of advanced propeller with small thrust, which was suitable to orbit transfer, attitude control, station keeping and formation flying for small and micro satellite.
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