Optimal transfers from Moon to L2 halo orbit of the Earth-Moon system

• Autor(a) principal: Santos, L. B.T.
• Data de Publicação: 2022
• Outros Autores: Sousa-Silva, P. A. [UNESP], Terra, M. O., Mani, Karthik V., de Almeida, A. K., Sanchez, D. M., Prado, A. F.B.A.
• Tipo de documento: Artigo
• Idioma: eng
• Título da fonte: Repositório Institucional da UNESP
• Texto Completo: http://dx.doi.org/10.1016/j.asr.2022.08.035; http://hdl.handle.net/11449/245975
• topic: Mission design; Moon to L2 Halo orbit transfer; Optimal transfers; Restricted three-body problem; Stable manifold

In this paper, optimal solutions are investigated for a transfer from a parking orbit around the Moon to a halo orbit around L2 of the Earth-Moon system. The transfers are executed by applying a single maneuver and exploiting the stable invariant manifold of the hyperbolic parking solution at arrival. In this regard, an optimization problem is proposed where both the orbital characteristics of a parking solution around the Moon (its Keplerian elements) and the characteristics of a transfer trajectory (guided by the stable manifold of the arrival Halo orbit) are considered as variables. The problem involved in the single maneuver transfer is solved using a nonlinear programming method (NLP), which aims to minimize the cost of ΔV within the framework of the Earth-Moon system using the circular restricted three-body problem. The feasibility of this kind of transfer for a Cubesat is shown in this paper through results with low ΔV combined with suitable times of flight.