Trabalho apresentado em evento
Third body perturbation using a single averaged model considering elliptic orbits for the disturbing body
Fecha
2008-01-01Registro en:
Spaceflight Mechanics 2008, Vol 130, Pts 1 and 2. San Diego: Univelt Inc, v. 130, p. 1571-1578, 2008.
1081-6003
WOS:000258397800096
Autor
Universidade Estadual Paulista (Unesp)
Resumen
In 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.