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

Registro completo de metadados
MetadadosDescriçãoIdioma
Autor(es): dc.contributorINPE-
Autor(es): dc.contributorUniversidade Estadual Paulista (UNESP)-
Autor(es): dc.contributorITA-
Autor(es): dc.contributorGomSpace-
Autor(es): dc.contributorInstituto de Telecomunicações-
Autor(es): dc.contributorSão Paulo-
Autor(es): dc.contributorRUDN University-
Autor(es): dc.creatorSantos, L. B.T.-
Autor(es): dc.creatorSousa-Silva, P. A.-
Autor(es): dc.creatorTerra, M. O.-
Autor(es): dc.creatorMani, Karthik V.-
Autor(es): dc.creatorde Almeida, A. K.-
Autor(es): dc.creatorSanchez, D. M.-
Autor(es): dc.creatorPrado, A. F.B.A.-
Data de aceite: dc.date.accessioned2025-08-21T15:09:44Z-
Data de disponibilização: dc.date.available2025-08-21T15:09:44Z-
Data de envio: dc.date.issued2023-07-29-
Data de envio: dc.date.issued2023-07-29-
Data de envio: dc.date.issued2022-11-30-
Fonte completa do material: dc.identifierhttp://dx.doi.org/10.1016/j.asr.2022.08.035-
Fonte completa do material: dc.identifierhttp://hdl.handle.net/11449/245975-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/245975-
Descrição: dc.descriptionIn 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.-
Descrição: dc.descriptionDivision of Space Mechanics and Control National Institute for Space Research INPE-
Descrição: dc.descriptionSão Paulo State University UNESP-
Descrição: dc.descriptionTechnological Institute of Aeronautics ITA-
Descrição: dc.descriptionGomSpace-
Descrição: dc.descriptionInstituto de Telecomunicações, 3810-193 Aveiro-
Descrição: dc.descriptionPostgraduate Division - National Institute for Space Research (INPE) São Paulo-
Descrição: dc.descriptionAcademy of Engineering RUDN University, Miklukho-Maklaya street 6-
Descrição: dc.descriptionSão Paulo State University UNESP-
Formato: dc.format3362-3372-
Idioma: dc.languageen-
Relação: dc.relationAdvances in Space Research-
???dc.source???: dc.sourceScopus-
Palavras-chave: dc.subjectMission design-
Palavras-chave: dc.subjectMoon to L2 Halo orbit transfer-
Palavras-chave: dc.subjectOptimal transfers-
Palavras-chave: dc.subjectRestricted three-body problem-
Palavras-chave: dc.subjectStable manifold-
Título: dc.titleOptimal transfers from Moon to L2 halo orbit of the Earth-Moon system-
Tipo de arquivo: dc.typelivro digital-
Aparece nas coleções:Repositório Institucional - Unesp

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