TY - JOUR

T1 - Cycler orbit design using low-thrust in the Sun-Earth-Moon system

AU - Miyahara, Keitaro

AU - Kayama, Yuki

AU - Bando, Mai

AU - Hokamoto, Shinji

N1 - Publisher Copyright:
© 2020 by the International Astronautical Federation (IAF). All rights reserved.

PY - 2020

Y1 - 2020

N2 - 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.

AB - 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.

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M3 - Conference article

AN - SCOPUS:85100947427

VL - 2020-October

JO - Proceedings of the International Astronautical Congress, IAC

JF - Proceedings of the International Astronautical Congress, IAC

SN - 0074-1795

T2 - 71st International Astronautical Congress, IAC 2020

Y2 - 12 October 2020 through 14 October 2020

ER -