Low-energy escape from the Sun-Earth L2 halo orbit utilizing unstable manifolds and lunar gravity assist

Hongru Chen, Yasuhiro Kawakatsu, Toshiya Hanada

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

Abstract

The paper investigates the escape strategy using the unstable manifolds of the Sun-Earth L2 halo orbit and lunar gravity assist. There are four cases of intersection of the manifold tubes associated with halo orbits and the orbit of the Moon. The four intersections have different V with respect to the Moon. The corresponding lunar gravity assists can result in a range of escape trajectories, granting choices for the extended mission of halo orbits. In order to satisfy the lunar encounter requirements, the strategy and ΔV costs of phasing maneuvers are presented as well.

Original languageEnglish
Title of host publicationAdvances In The Astronautical Sciences
PublisherUnivelt Inc.
Pages3679-3691
Number of pages13
Volume152
ISBN (Electronic)9780877036111
Publication statusPublished - 2014
Event24th AAS/AIAA Space Flight Mechanics Meeting, 2014 - Mexico, United States
Duration: Jan 26 2014Jan 30 2014

Other

Other24th AAS/AIAA Space Flight Mechanics Meeting, 2014
CountryUnited States
CityMexico
Period1/26/141/30/14

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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  • Cite this

    Chen, H., Kawakatsu, Y., & Hanada, T. (2014). Low-energy escape from the Sun-Earth L2 halo orbit utilizing unstable manifolds and lunar gravity assist. In Advances In The Astronautical Sciences (Vol. 152, pp. 3679-3691). Univelt Inc..