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Design of Interplanetary Low-Thrust Trajectory Including Escape and Capture Phase
Author(s): 
Pages: 774-779
Year: Issue:  7
Journal: Transactions of Beijing Institute of Technology

Abstract: 提出一种包含逃逸和俘获阶段的行星际小推力全程轨道设计方法. 该方法采用分步式设计思想,针对地球逃逸、日心转移和目标星俘获三段轨道的转移特点,分别采用加权组合控制律和混合法进行顺序设计,并基于拼接条件在地球和目标星引力影响球处完成不同轨道段间的拼接. 该方法降低了多引力场穿越轨道动力学的强非线性,具有较高的计算效率和良好的收敛性. 以地球-火星转移为例对设计方法进行了仿真计算,数值结果表明:该方法可...
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