Third body perturbation using a single averaged model considering elliptic orbits for the disturbing body

dc.contributorUniversidade Estadual Paulista (Unesp)
dc.date.accessioned2014-05-20T15:30:32Z
dc.date.accessioned2022-10-05T16:59:41Z
dc.date.available2014-05-20T15:30:32Z
dc.date.available2022-10-05T16:59:41Z
dc.date.created2014-05-20T15:30:32Z
dc.date.issued2008-01-01
dc.identifierSpaceflight Mechanics 2008, Vol 130, Pts 1 and 2. San Diego: Univelt Inc, v. 130, p. 1571-1578, 2008.
dc.identifier1081-6003
dc.identifierhttp://hdl.handle.net/11449/39880
dc.identifierWOS:000258397800096
dc.identifier.urihttp://repositorioslatinoamericanos.uchile.cl/handle/2250/3910928
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.
dc.languageeng
dc.publisherUnivelt Inc
dc.relationSpaceflight Mechanics 2008, Vol 130, Pts 1 and 2
dc.rightsAcesso aberto
dc.sourceWeb of Science
dc.titleThird body perturbation using a single averaged model considering elliptic orbits for the disturbing body
dc.typeTrabalho apresentado em evento


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