Low energy escape trajectory for the Mars moon sample return mission

Makoto Horikawa, Yasuhiro Kawakatsu, Hiroaki Yoshimura

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    3 Citations (Scopus)

    Abstract

    In this paper, we investigate the low-energy escape trajectory design for a mission called Martian Moons eXplorer to achieve the world's first sample return from Martian moon. The hybrid usage of chemical and electric propulsion with combination of the three-body and two-body problems has come into consideration in order to seek a fast low-energy escape from Mars. We first study the needs of pre-departure sequence. Then, we determine the transition point from a low-energy three-body phase to a low-thrust two-body phase, in which the tube dynamics is employed for the low-energy three-body phase. We finally develop charts to reveal the relation between the velocity in Mars Escape Injection maneuver and the required time of flight.

    Original languageEnglish
    Title of host publicationSpaceflight Mechanics 2016
    PublisherUnivelt Inc.
    Pages1479-1488
    Number of pages10
    Volume158
    ISBN (Print)9780877036333
    Publication statusPublished - 2016
    Event26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States
    Duration: 2016 Feb 142016 Feb 18

    Other

    Other26th AAS/AIAA Space Flight Mechanics Meeting, 2016
    CountryUnited States
    CityNapa
    Period16/2/1416/2/18

    ASJC Scopus subject areas

    • Aerospace Engineering
    • Space and Planetary Science

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  • Cite this

    Horikawa, M., Kawakatsu, Y., & Yoshimura, H. (2016). Low energy escape trajectory for the Mars moon sample return mission. In Spaceflight Mechanics 2016 (Vol. 158, pp. 1479-1488). Univelt Inc..