### 抄録

Inspired by successful extended missions such as the ISEE-3, an investigation for the extended mission that involves a lunar encounter following a Sun-Earth halo orbit mission is considered valuable. Most previous studies present the orbit-to-orbit transfers where the lunar phase is not considered. Intended for extended missions, the present work aims to solve for the minimum phasing ∆V for various initial lunar phases. Due to the solution multiplicity of the two-point boundary value problem, the general constrained optimization algorithm that does not identify multiple feasible solutions is shown to miss minima. A two-step differential corrector with a two-body Lambert solver is developed for identifying multiple solutions. The minimum ∆V associated with the short-way and long-way approaches can be recovered. It is acquired that the required ∆V to cover all initial lunar phases is around 45 m/s for the halo orbit with out-of-plane amplitude A
_{z}
greater than 3.5×10
^{5}
km, and 14 m/s for a small halo orbit with A
_{z}
=1×10
^{5}
km. In addition, the paper discusses the phasing planning based on the ∆V result and the shift of lunar phase with halo orbit revolution.

元の言語 | 英語 |
---|---|

ページ（範囲） | 464-473 |

ページ数 | 10 |

ジャーナル | Acta Astronautica |

巻 | 127 |

DOI | |

出版物ステータス | 出版済み - 10 1 2016 |

### Fingerprint

### All Science Journal Classification (ASJC) codes

- Aerospace Engineering

### これを引用

*Acta Astronautica*,

*127*, 464-473. https://doi.org/10.1016/j.actaastro.2016.05.003

**Phasing Delta-V for transfers from Sun–Earth halo orbits to the Moon.** / Chen, Hongru; Kawakatsu, Yasuhiro; Hanada, Toshiya.

研究成果: ジャーナルへの寄稿 › 記事

*Acta Astronautica*, 巻. 127, pp. 464-473. https://doi.org/10.1016/j.actaastro.2016.05.003

}

TY - JOUR

T1 - Phasing Delta-V for transfers from Sun–Earth halo orbits to the Moon

AU - Chen, Hongru

AU - Kawakatsu, Yasuhiro

AU - Hanada, Toshiya

PY - 2016/10/1

Y1 - 2016/10/1

N2 - Inspired by successful extended missions such as the ISEE-3, an investigation for the extended mission that involves a lunar encounter following a Sun-Earth halo orbit mission is considered valuable. Most previous studies present the orbit-to-orbit transfers where the lunar phase is not considered. Intended for extended missions, the present work aims to solve for the minimum phasing ∆V for various initial lunar phases. Due to the solution multiplicity of the two-point boundary value problem, the general constrained optimization algorithm that does not identify multiple feasible solutions is shown to miss minima. A two-step differential corrector with a two-body Lambert solver is developed for identifying multiple solutions. The minimum ∆V associated with the short-way and long-way approaches can be recovered. It is acquired that the required ∆V to cover all initial lunar phases is around 45 m/s for the halo orbit with out-of-plane amplitude A z greater than 3.5×10 5 km, and 14 m/s for a small halo orbit with A z =1×10 5 km. In addition, the paper discusses the phasing planning based on the ∆V result and the shift of lunar phase with halo orbit revolution.

AB - Inspired by successful extended missions such as the ISEE-3, an investigation for the extended mission that involves a lunar encounter following a Sun-Earth halo orbit mission is considered valuable. Most previous studies present the orbit-to-orbit transfers where the lunar phase is not considered. Intended for extended missions, the present work aims to solve for the minimum phasing ∆V for various initial lunar phases. Due to the solution multiplicity of the two-point boundary value problem, the general constrained optimization algorithm that does not identify multiple feasible solutions is shown to miss minima. A two-step differential corrector with a two-body Lambert solver is developed for identifying multiple solutions. The minimum ∆V associated with the short-way and long-way approaches can be recovered. It is acquired that the required ∆V to cover all initial lunar phases is around 45 m/s for the halo orbit with out-of-plane amplitude A z greater than 3.5×10 5 km, and 14 m/s for a small halo orbit with A z =1×10 5 km. In addition, the paper discusses the phasing planning based on the ∆V result and the shift of lunar phase with halo orbit revolution.

UR - http://www.scopus.com/inward/record.url?scp=84976577671&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84976577671&partnerID=8YFLogxK

U2 - 10.1016/j.actaastro.2016.05.003

DO - 10.1016/j.actaastro.2016.05.003

M3 - Article

VL - 127

SP - 464

EP - 473

JO - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

ER -