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
EditorsMartin T. Ozimek, Renato Zanetti, Angela L. Bowes, Ryan P. Russell, Martin T. Ozimek
PublisherUnivelt Inc.
Pages1479-1488
Number of pages10
ISBN (Print)9780877036333
Publication statusPublished - 2016
Event26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States
Duration: 2016 Feb 142016 Feb 18

Publication series

NameAdvances in the Astronautical Sciences
Volume158
ISSN (Print)0065-3438

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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