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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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；

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