Escape trajectories from the L2 point of the earth-moon system

Keita Tanaka, Jun'Ichiro Kawaguchi

Research output: Contribution to journalArticlepeer-review

Abstract

To use the L2 point of the Earth-Moon (EM) system as a space transportation hub, it is absolutely necessary to know the available orbital energy of a spacecraft departing from EM L2 and how to obtain required excess velocity to the target planet. This paper presents a successful acceleration strategy using the combination of an impulsive maneuver and the Sun gravitational perturbation. Applying this strategy enables the spacecraft to efficiently convert the energy of the maneuver into its orbital energy.

Original languageEnglish
Pages (from-to)238-244
Number of pages7
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Volume57
Issue number4
DOIs
Publication statusPublished - 2014 Jul
Externally publishedYes

Keywords

  • Escape Trajectories
  • Sun-Earth-Moon Four-Body Problem

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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