Stationkeeping controllers for Earth–Moon L1 and L2 libration points halo orbits

Registro completo de metadados
MetadadosDescriçãoIdioma
Autor(es): dc.contributorTechnological Institute of Aeronautics-
Autor(es): dc.contributorUniversidade Estadual Paulista (UNESP)-
Autor(es): dc.creatorMarsola, Thiago César Lousada-
Autor(es): dc.creatorda Silva Fernandes, Sandro-
Autor(es): dc.creatorBalthazar, José Manoel-
Data de aceite: dc.date.accessioned2025-08-21T18:54:19Z-
Data de disponibilização: dc.date.available2025-08-21T18:54:19Z-
Data de envio: dc.date.issued2022-05-01-
Data de envio: dc.date.issued2022-05-01-
Data de envio: dc.date.issued2021-07-01-
Fonte completa do material: dc.identifierhttp://dx.doi.org/10.1007/s40430-021-03071-9-
Fonte completa do material: dc.identifierhttp://hdl.handle.net/11449/233161-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/233161-
Descrição: dc.descriptionThis paper considers the dynamics of the circular restricted three-body problem (CRTBP) for the Earth–Moon system designing stationkeeping controllers at periodic orbits. Taking into account the L1 and L2 equilibrium points in this dynamics, it is constructed a family of periodic orbits in the vicinity of these libration points, called halo orbits. The orbits are constructed using an analytical approach as a first guess with a numerical method in addition, in order to correct the linear approximation procedure. Withal the stability of these libration points, trajectories are analyzed and proved to be unstable; a spacecraft moving near these points must use some correction maneuver to remain close to the nominal orbit. Two types of controllers are proposed for stationkeeping maneuvers performed by low-thrust power-limited propulsion system. The first controller is based on the linear quadratic regulator (LQR) and the second one is based on the nonlinear feedback control which uses the state-dependent Riccati equation control (SDRE). Finally, a parameters comparison analysis is performed taking into account different values of the weight matrices for both controllers at both halo orbits.-
Descrição: dc.descriptionTechnological Institute of Aeronautics, Praça Marechal Eduardo Gomes 50-
Descrição: dc.descriptionState University of São Paulo—UNESP, Av. Eng. Luís Edmundo Carrijo Coube-
Descrição: dc.descriptionState University of São Paulo—UNESP, Av. Eng. Luís Edmundo Carrijo Coube-
Idioma: dc.languageen-
Relação: dc.relationJournal of the Brazilian Society of Mechanical Sciences and Engineering-
???dc.source???: dc.sourceScopus-
Palavras-chave: dc.subjectHalo orbits-
Palavras-chave: dc.subjectLibration points-
Palavras-chave: dc.subjectLinear Quadratic Regulator (LQR)-
Palavras-chave: dc.subjectState-Dependent Riccati Equation (SDRE)-
Palavras-chave: dc.subjectStationkeeping control-
Título: dc.titleStationkeeping controllers for Earth–Moon L1 and L2 libration points halo orbits-
Tipo de arquivo: dc.typevídeo-
Aparece nas coleções:Repositório Institucional - Unesp

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