Design of Earth-Moon Free Return Transfer Trajectory under Ephemeris Model during the Entire Flight Process

被引：0

作者：

Peng Q. ^{[1
,2
]}

He X. ^{[2
,3
]}

Chen T. ^{[2
]}

Wu X. ^{[1
]}

Xu M. ^{[2
]}

机构：

[1] China Astronauts Research and Training Center, Beijing

[2] School of Astronautics, Beihang University, Beijing

[3] Shenyuan Honors College, Beihang University, Beijing

来源：

Yuhang Xuebao/Journal of Astronautics | 2023年 / 44卷 / 01期

关键词：

Earth-Moon transfer; Ephemeris model; Free return; Manned lunar landing; Orbital design;

D O I：

10.3873/j.issn.1000-1328.2023.01.005

中图分类号：

O29 [应用数学];

学科分类号：

070104 ;

摘要：

Aiming at the need of manned lunar landing missions, the trajectory design problem of Earth-Moon transfer with free return capability under the ephemeris model is studied. The three-dimensional Earth-Moon free return trajectory is solved under the three-body model, by which the distribution of free return trajectories in the eislunar space is obtained. Under the assumption of two-body model, the three-pulse maneuvers strategy near the Moon is proposed. Furthermore, a two-step optimization correction method is proposed, during which the orbital altitude and reentry corridor are respectively considered as the main constraints. The interior-point method and SQP algorithm are used to optimize and correct the initial states of free return trajectory under the ephemeris model. Then, the lunar three-pulse maneuvers are optimized and corrected by SQP algorithm, and then the entire Earth-Moon transfer trajectory consisting of free return segment and lunar three-pulse maneuvers segment are obtained. The simulation results have verified the feasibility of the proposed method. © 2023 China Spaceflight Society. All rights reserved.

引用

页码：43 / 51

页数：8

共 21 条

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