Optimal transfers from Moon to \(L_2\) halo orbit of the Earth-Moon system

In this paper, we seek optimal solutions for a transfer from a parking orbit around the Moon to a halo orbit around \(L_2\) of the Earth-Moon system, by applying a single maneuver and exploiting the stable invariant manifold of the hyperbolic parking solution at arrival. For that, we propose an opti...

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Bibliographic Details
Published inarXiv.org
Main Authors Santos, L B T, Allan Kardec de Almeida Jr, Sousa-Silva, P A, Terra, M O, Sanchez, D M, S Aljbaae A F B A Prado, Monteiro, F
Format Paper
LanguageEnglish
Published Ithaca Cornell University Library, arXiv.org 23.07.2023
Subjects
Cubesat
Earth-Moon system
Lunar orbits
Maneuvers
Manifolds
Nonlinear programming
Optimization
Parking orbits
Three body problem
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Summary:In this paper, we seek optimal solutions for a transfer from a parking orbit around the Moon to a halo orbit around \(L_2\) of the Earth-Moon system, by applying a single maneuver and exploiting the stable invariant manifold of the hyperbolic parking solution at arrival. For that, we propose an optimization problem considering as variables both the orbital characteristics of a parking solution around the Moon, (namely, its Keplerian elements) and the characteristics of a transfer trajectory guided by the stable manifold of the arrival Halo orbit. The problem is solved by a nonlinear programming method (NLP), aiming to minimize the cost of \(\Delta V\) to perform a single maneuver transfer, within the framework of the Earth-Moon system of the circular restricted three-body problem. Results with low \(\Delta V\) and suitable time of flight show the feasibility of this kind of transfer for a Cubesat.
ISSN:2331-8422
DOI:10.48550/arxiv.2307.12353