Cycler orbit design using low-thrust in the Sun-Earth-Moon system

Keitaro Miyahara, Yuki Kayama, Mai Bando, Shinji Hokamoto

Research output: Contribution to journalConference articlepeer-review

Abstract

Recently, a lot of studies have been focusing on the transfer to the Moon. Cycler orbits which can periodically encounter the Earth and the Moon using swingbys can provide a low-cost transportation system to the Moon. In previous studies, several methods to design cycler orbits have been developed based on the two-body problem. This paper improves the previous studies in terms of the following three factors. First, a cycler orbit is designed in the three-body problem. This expansion is basically difficult due to the sensitivity of the three-body dynamics. To overcome this problem, the orbit generated in the two-body problem of the Earth is used as an initial guess and expanded to the orbit in the three-body problem using multiple-shooting differential correction and mass continuation. Second, the accessibility of the other orbits in the cis-lunar region is investigated. It verifies whether the cycler orbit can connect to a family of Lyapunov orbit in the Earth-Moon system and calculates the required velocity change amount. Finally, the influence of perturbation from the Sun is taken into account. Then a new control method is proposed based on the linear quadratic regulator that enables to eliminate the influence of the Sun in the BCR4BP.

Original languageEnglish
JournalProceedings of the International Astronautical Congress, IAC
Volume2020-October
Publication statusPublished - 2020
Event71st International Astronautical Congress, IAC 2020 - Virtual, Online
Duration: Oct 12 2020Oct 14 2020

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics
  • Space and Planetary Science

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