Methodology of Optimal Control of Low-Thrust Spacecraft Transfer Between Halo Orbits Around the Earth-Moon L2 Libration Point

被引：0
作者：
Du C. [1 ,2 ]
Starinova O.L. [1 ,3 ]
Demina A.Y. [1 ]
机构：
[1] Samara University, Samara
[2] Northwestern Polytechnical University, Xi’an
[3] Nanjing University of Science and Technology, Nanjing
来源：
Gyroscopy and Navigation | 2023年 / 14卷 / 03期
基金：
俄罗斯科学基金会;
关键词：
Earth−Moon system; electric propulsion engines; optimal control; restricted three-body problem (RTBP);
D O I：
10.1134/S2075108723030033
中图分类号：
学科分类号：
摘要：
Abstract—The paper considers the problem of optimal control of an electric propulsion spacecraft maneuvering between the spatial halo orbits around the L2 libration point in the Earth−Moon system. The proposed methodology finds the initial approximations for calculating the transfer trajectories within the framework of restricted three-body problem and improves the computational efficiency of calculations. A low-thrust transfer between the halo orbits is calculated to confirm the validity of this computational procedure. © 2023, Pleiades Publishing, Ltd.
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收藏
页码：205 / 212
页数：7
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