Escape trajectory for the martian moon sample return mission using tube dynamics

Kazutoshi Takemura, Yasuhiro Kawakatsu, Hiroaki Yoshimura

研究成果: Conference contribution

1 被引用数 (Scopus)

抄録

We study trajectory design for a spacecraft escaping from Mars in the context of spatial restricted three-body problem (SR3BP) by using tube dynamics. First, we compute the halo and quasi-halo orbits around L1of Sun-Mars system together with the associated invariant manifolds. Then we investigate whether the spacecraft with a certain energy is inside of the tube to connect the manifold with the Phobos orbit. We also perform grid search with the SR3BP with the same energy as the invariant manifold. Comparing numerical results between grid search and the tube dynamics, we show how to determine the propriety for the escape trajectory by using the tube dynamics. Consequently we clarify the way to judge whether the spacecrafts can escape or not in the spatial problem.

本文言語English
ホスト出版物のタイトルSpace Flight Mechanics Meeting
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
210009
ISBN(印刷版)9781624105333
DOI
出版ステータスPublished - 2018
イベントSpace Flight Mechanics Meeting, 2018 - Kissimmee, United States
継続期間: 2018 1月 82018 1月 12

出版物シリーズ

名前Space Flight Mechanics Meeting, 2018
番号210009

Other

OtherSpace Flight Mechanics Meeting, 2018
国/地域United States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • 航空宇宙工学

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