Attitude stability analyses for small artificial satellites

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MetadadosDescriçãoIdioma
Autor(es): dc.contributorNational Institute for Space Research (INPE)-
Autor(es): dc.contributorUniversidade Estadual Paulista (UNESP)-
Autor(es): dc.contributorFaculty of Tecnology (FATEC)-
Autor(es): dc.contributorSão Paulo Salesian University (UNISAL)-
Autor(es): dc.contributorUniversidade Federal do Rio de Janeiro (UFRJ)-
Autor(es): dc.creatorSilva, W. R.-
Autor(es): dc.creatorZanardi, M. C.-
Autor(es): dc.creatorFormiga, J. K.S.-
Autor(es): dc.creatorCabette, R. E.S.-
Autor(es): dc.creatorStuchi, T. J.-
Data de aceite: dc.date.accessioned2025-08-21T22:49:18Z-
Data de disponibilização: dc.date.available2025-08-21T22:49:18Z-
Data de envio: dc.date.issued2022-04-29-
Data de envio: dc.date.issued2022-04-29-
Data de envio: dc.date.issued2013-01-01-
Fonte completa do material: dc.identifierhttp://dx.doi.org/10.1088/1742-6596/465/1/012022-
Fonte completa do material: dc.identifierhttp://hdl.handle.net/11449/227388-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/227388-
Descrição: dc.descriptionThe objective of this paper is to analyze the stability of the rotational motion of a symmetrical spacecraft, in a circular orbit. The equilibrium points and regions of stability are established when components of the gravity gradient torque acting on the spacecraft are included in the equations of rotational motion, which are described by the Andoyer's variables. The nonlinear stability of the equilibrium points of the rotational motion is analysed here by the Kovalev-Savchenko theorem. With the application of the Kovalev-Savchenko theorem, it is possible to verify if they remain stable under the influence of the terms of higher order of the normal Hamiltonian. In this paper, numerical simulations are made for a small hypothetical artificial satellite. Several stable equilibrium points were determined and regions around these points have been established by variations in the orbital inclination and in the spacecraft principal moment of inertia. The present analysis can directly contribute in the maintenance of the spacecraft's attitude.-
Descrição: dc.descriptionSpace Mechanics and Control Division National Institute for Space Research (INPE), Sao Paulo, Sao Jose dos Campos, 12227-010-
Descrição: dc.descriptionDepartment of Mathematics Group of Orbital Dynamics and Planetology São Paulo State University (UNESP), São Paulo, Guaratinguetá 12516-410-
Descrição: dc.descriptionFaculty of Tecnology (FATEC), Sao Paulo, Sao Jose dos Campos, 12248-004-
Descrição: dc.descriptionSão Paulo Salesian University (UNISAL), São Paulo, Lorena, 12600-100-
Descrição: dc.descriptionRio de Janeiro Federal University (UFRJ) Rio de Janeiro, Rio de Janeiro, 21941-010-
Descrição: dc.descriptionDepartment of Mathematics Group of Orbital Dynamics and Planetology São Paulo State University (UNESP), São Paulo, Guaratinguetá 12516-410-
Idioma: dc.languageen-
Relação: dc.relationJournal of Physics: Conference Series-
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Título: dc.titleAttitude stability analyses for small artificial satellites-
Tipo de arquivo: dc.typeaula digital-
Aparece nas coleções:Repositório Institucional - Unesp

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