Show simple item record

dc.contributor.authorDomingos, Rita de C. [UNESP]
dc.contributor.authorde Moraes, Rodolpho V. [UNESP]
dc.contributor.authorde Almeida Prado, A. F. B.
dc.identifier.citationSpaceflight Mechanics 2008, Vol 130, Pts 1 and 2. San Diego: Univelt Inc, v. 130, p. 1571-1578, 2008.
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.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.rights.accessRightsAcesso aberto
unesp.campusUniversidade Estadual Paulista (UNESP), Faculdade de Engenharia, Guaratinguetápt[3]
Localize o texto completo

Files in this item


There are no files associated with this item.

This item appears in the following Collection(s)

Show simple item record