An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.
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。
This paper makes an undated assessment of the technical and economic feasibility of transferring satellites from low Earth Orbit to Geostationary Orbit using low thrust propulsion.
本文对利用低推力推进装置将卫星从低地轨道转移到静地轨道的可行性在技术上和经济上重新作了评价。
Electrodynamic tethers with low thrust-to-weight ratios can only perform orbital transfers over a large number of revolutions, which poses a real challenge to short time scale optimal control methods.
电动力绳系卫星的推力幅值较小且方向固定，完成轨道机动任务的周期长，其最优控制问题的求解比较困难。
First, the optimization model of interplanetary low-thrust trajectory was established using modified equinoctial elements.
首先，基于归一化的改进春分点根数建立了星际小推力转移轨道的优化模型；
A novel rapid method to design optimal-fuel interplanetary trajectory for low-thrust propulsion is presented based on normal trajectory approach.
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。
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