### Abstract

A low energy transfer from the Earth to the Moon is proposed in the context of the 4-body Problem. We propose a new model by regarding the Sun-Earth-Moon-Spacecraft (S/C) 4-body system as the coupled system of the Sun-perturbed 3-body system and the Moon-perturbed 3-body system. In particular, we clarify the tube structures of invariant manifolds of the 4-body Problem by investigating the Lagrangian coherent structures of such a coupled 3-body system with perturbations. Lastly, we construct a low-energy transfer trajectory from the Earth to the Moon by patching two trajectories obtained from the perturbed systems at a Poincare section. We develop an optimal trajectory by minimizing the Delta-v at the Poincaré section.

Original language | English |
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Title of host publication | Spaceflight Mechanics 2016 |

Publisher | Univelt Inc. |

Pages | 1497-1512 |

Number of pages | 16 |

Volume | 158 |

ISBN (Print) | 9780877036333 |

Publication status | Published - 2016 |

Event | 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States Duration: 2016 Feb 14 → 2016 Feb 18 |

### Other

Other | 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 |
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Country | United States |

City | Napa |

Period | 16/2/14 → 16/2/18 |

### Fingerprint

### ASJC Scopus subject areas

- Aerospace Engineering
- Space and Planetary Science

### Cite this

*Spaceflight Mechanics 2016*(Vol. 158, pp. 1497-1512). Univelt Inc..

**The Earth-Moon low-energy transfer in the 4-body problem.** / Onozaki, Kaori; Yoshimura, Hiroaki; Ross, Shane D.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

*Spaceflight Mechanics 2016.*vol. 158, Univelt Inc., pp. 1497-1512, 26th AAS/AIAA Space Flight Mechanics Meeting, 2016, Napa, United States, 16/2/14.

}

TY - GEN

T1 - The Earth-Moon low-energy transfer in the 4-body problem

AU - Onozaki, Kaori

AU - Yoshimura, Hiroaki

AU - Ross, Shane D.

PY - 2016

Y1 - 2016

N2 - A low energy transfer from the Earth to the Moon is proposed in the context of the 4-body Problem. We propose a new model by regarding the Sun-Earth-Moon-Spacecraft (S/C) 4-body system as the coupled system of the Sun-perturbed 3-body system and the Moon-perturbed 3-body system. In particular, we clarify the tube structures of invariant manifolds of the 4-body Problem by investigating the Lagrangian coherent structures of such a coupled 3-body system with perturbations. Lastly, we construct a low-energy transfer trajectory from the Earth to the Moon by patching two trajectories obtained from the perturbed systems at a Poincare section. We develop an optimal trajectory by minimizing the Delta-v at the Poincaré section.

AB - A low energy transfer from the Earth to the Moon is proposed in the context of the 4-body Problem. We propose a new model by regarding the Sun-Earth-Moon-Spacecraft (S/C) 4-body system as the coupled system of the Sun-perturbed 3-body system and the Moon-perturbed 3-body system. In particular, we clarify the tube structures of invariant manifolds of the 4-body Problem by investigating the Lagrangian coherent structures of such a coupled 3-body system with perturbations. Lastly, we construct a low-energy transfer trajectory from the Earth to the Moon by patching two trajectories obtained from the perturbed systems at a Poincare section. We develop an optimal trajectory by minimizing the Delta-v at the Poincaré section.

UR - http://www.scopus.com/inward/record.url?scp=85007370986&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85007370986&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9780877036333

VL - 158

SP - 1497

EP - 1512

BT - Spaceflight Mechanics 2016

PB - Univelt Inc.

ER -