Domingos, Rita de C. [UNESP]de Moraes, Rodolpho V. [UNESP]de Almeida Prado, A. F. B.2014-05-202014-05-202008-01-01Spaceflight Mechanics 2008, Vol 130, Pts 1 and 2. San Diego: Univelt Inc, v. 130, p. 1571-1578, 2008.1081-6003http://hdl.handle.net/11449/39880In 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.1571-1578engTrabalho apresentado em eventoWOS:000258397800096Acesso aberto