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dc.contributor.authorDomingos, Rita de C. [UNESP]
dc.contributor.authorde Moraes, Rodolpho V. [UNESP]
dc.contributor.authorde Almeida Prado, A. F. B.
dc.date.accessioned2014-05-20T15:30:32Z
dc.date.available2014-05-20T15:30:32Z
dc.date.issued2008-01-01
dc.identifierhttp://www.univelt.com/book=1740
dc.identifier.citationSpaceflight Mechanics 2008, Vol 130, Pts 1 and 2. San Diego: Univelt Inc, v. 130, p. 1571-1578, 2008.
dc.identifier.issn1081-6003
dc.identifier.urihttp://hdl.handle.net/11449/39880
dc.description.abstractIn the present work, we expanded the study done by Solorzanol(1) including the eccentricity of the perturbing body. The assumptions used to develop the single-averaged analytical model are the same ones of the restricted elliptic three-body problem. The disturbing function was expanded in Legendre polynomials up to fourth-order. After that, the equations of motion are obtained from the planetary equations and we performed a set of numerical simulations. Different initial eccentricities for the perturbing and perturbed body are considered. The results obtained perform an analysis of the stability of a near-circular orbits and investigate under which conditions this orbit remain near-circular.en
dc.format.extent1571-1578
dc.language.isoeng
dc.publisherUnivelt Inc
dc.relation.ispartofSpaceflight Mechanics 2008, Vol 130, Pts 1 and 2
dc.sourceWeb of Science
dc.titleThird body perturbation using a single averaged model considering elliptic orbits for the disturbing bodyen
dc.typeTrabalho apresentado em evento
dcterms.rightsHolderUnivelt Inc
dc.contributor.institutionUniversidade Estadual Paulista (UNESP)
dc.description.affiliationUNESP, Grp Dinam Orbital & Planetol, Guarantingueta, SP, Brazil
dc.description.affiliationUnespUNESP, Grp Dinam Orbital & Planetol, Guarantingueta, SP, Brazil
dc.identifier.wosWOS:000258397800096
dc.rights.accessRightsAcesso aberto
unesp.campusUniversidade Estadual Paulista (UNESP), Faculdade de Engenharia, Guaratinguetápt
unesp.author.orcid0000-0002-7966-3231[3]
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