Cycler orbits utilizing low thrust propulsion systems

M. Morimoto, H. Yamakawa, C. Uesugi

Research output: Contribution to conferencePaper

Abstract

Earth return orbits are investigated using continuous acceleration provided by low-thrust propulsion system. The problem is formulated as an optimal control problem, and solved by calculus of variation approach. The applicability of low-thrust Earth return trajectories to cycler orbits between the Earth and Mars is to be discussed. Cycler orbits are trajectories, which encounter the same planets on a regular interval repeatedly. Future study aims at constructing the cycler orbits with low thrust propulsion analytically in the restricted three body problem and Hill's equations.

Original languageEnglish
Pages183-189
Number of pages7
Publication statusPublished - 2004 Dec 1
Externally publishedYes
EventInternational Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada
Duration: 2004 Oct 42004 Oct 8

Conference

ConferenceInternational Astronautical Federation - 55th International Astronautical Congress 2004
CountryCanada
CityVancouver
Period04/10/404/10/8

    Fingerprint

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Morimoto, M., Yamakawa, H., & Uesugi, C. (2004). Cycler orbits utilizing low thrust propulsion systems. 183-189. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.