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 proceedingConference 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 languageEnglish
    Title of host publicationSpace Flight Mechanics Meeting
    PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
    Edition210009
    ISBN (Print)9781624105333
    DOIs
    Publication statusPublished - 2018 Jan 1
    EventSpace Flight Mechanics Meeting, 2018 - Kissimmee, United States
    Duration: 2018 Jan 82018 Jan 12

    Other

    OtherSpace Flight Mechanics Meeting, 2018
    CountryUnited States
    CityKissimmee
    Period18/1/818/1/12

    ASJC Scopus subject areas

    • Aerospace Engineering

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  • Cite this

    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