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

Kazutoshi Takemura; Yasuhiro Kawakatsu; Hiroaki Yoshimura

doi:10.2514/6.2018-1688

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

Kazutoshi Takemura, Yasuhiro Kawakatsu, Hiroaki Yoshimura

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

1 Citation (Scopus)

Abstract

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.

Original language	English
Title of host publication	Space Flight Mechanics Meeting
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
Edition	210009
ISBN (Print)	9781624105333
DOIs	https://doi.org/10.2514/6.2018-1688
Publication status	Published - 2018 Jan 1
Event	Space Flight Mechanics Meeting, 2018 - Kissimmee, United States Duration: 2018 Jan 8 → 2018 Jan 12

Other

Other	Space Flight Mechanics Meeting, 2018
Country	United States
City	Kissimmee
Period	18/1/8 → 18/1/12

ASJC Scopus subject areas

Aerospace Engineering

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Takemura, K., Kawakatsu, Y., & Yoshimura, H. (2018). Escape trajectory for the martian moon sample return mission using tube dynamics. In Space Flight Mechanics Meeting (210009 ed.). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-1688

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abstract = "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.",

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