Design and analysis of a direct transfer trajectory from a near rectilinear halo orbit to a low lunar orbit

被引：19
|
作者：
Lu, Lin [1 ]
Li, Haiyang [1 ]
Zhou, Wanmeng [2 ]
Liu, Jianghui [3 ]
机构：
[1] Natl Univ Def Technol, Coll Aerosp Sci & Engn, Changsha 410073, Peoples R China
[2] China Astronaut Res & Training Ctr, Beijing 100094, Peoples R China
[3] PLA Unit 91395, Beijing 102443, Peoples R China
来源：
ADVANCES IN SPACE RESEARCH | 2021年 / 67卷 / 03期
基金：
中国国家自然科学基金;
关键词：
Near rectilinear halo orbit; Circular restricted three-body problem; Optimal direct transfer trajectory; Reachable domain calculation; REACHABLE DOMAIN; SPACECRAFT;
D O I：
10.1016/j.asr.2020.11.003
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A near rectilinear halo orbit (NRHO) is regarded as a potential orbit for a future deep space station that can effectively support sustainable crewed lunar exploration missions. In this paper, the L-2 southern NRHOs are selected as the research object, and a direct transfer trajectory from an NRHO to a low lunar orbit (LLO) is designed and analyzed. First, based on the circular restricted three-body problem, the characteristics of NRHOs are discussed including geometric behaviour, stability and synodic resonance. Second, optimal direct transfer trajectories are obtained by combining a local gradient optimization with a numerical continuation strategy. A reachable domain calculation model is established. Finally, simulations are carried out to verify the feasibility of the trajectory design method. The relationship between the velocity change and the reachable domain is further analysed through simulation calculations. (C) 2020 COSPAR. Published by Elsevier Ltd. All rights reserved.
引用
收藏
页码：1143 / 1154
页数：12
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