Minimum fuel trajectory design using sparse optimal control in three-body problem

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

1 被引用数 (Scopus)

抄録

This study formulates a successive multiple sparse optimal control method to minimize a fuel consumption of spacecraft in three-body problem. This method uses a convex optimization under linearlized dynamics, however it enables to find an optimal solution that satisfies a nonlinear dynamics by successive convexification. Furthermore, the divergence of the state constraint due to the instability of the three-body system can be avoided by dividing the state constraint into several sections. This method is applied to a transfer from Near Rectilinear halo orbit (NRHO) to Low lunar orbit (LLO) in the Earth-Moon system.

本文言語英語
ホスト出版物のタイトルAIAA Scitech 2020 Forum
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624105951
DOI
出版ステータス出版済み - 2020
イベントAIAA Scitech Forum, 2020 - Orlando, 米国
継続期間: 1 6 20201 10 2020

出版物シリーズ

名前AIAA Scitech 2020 Forum
1 PartF

会議

会議AIAA Scitech Forum, 2020
国/地域米国
CityOrlando
Period1/6/201/10/20

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学

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