Cycler orbits utilizing low thrust propulsion systems

M. Morimoto, H. Yamakawa, C. Uesugi

研究成果: Paper査読

抄録

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.

本文言語English
ページ183-189
ページ数7
出版ステータスPublished - 2004 12 1
外部発表はい
イベントInternational Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada
継続期間: 2004 10 42004 10 8

Conference

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

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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