%0 Journal Article
%4 sid.inpe.br/mtc-m21b/2013/11.26.16.44.49
%2 sid.inpe.br/mtc-m21b/2013/11.26.16.44.50
%@doi 10.1155/2013/260830
%@issn 1024-123X
%F scopus 2013-11
%T A study of single- and double-averaged second-order models to evaluate third-body perturbation considering elliptic orbits for the perturbing body
%D 2013
%A Domingos, R. C.,
%A Prado, Antonio Fernando Bertachini de Almeida,
%A Moraes, R. Villhena de,
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE), 12227-010 São José dos Campos, SP, Brazil
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Universidade Federal de São Paulo (UNIFESP), 12231-280 São José dos Campos, SP, Brazil
%@electronicmailaddress
%@electronicmailaddress prado@dem.inpe.br
%B Mathematical Problems in Engineering
%V 2013
%N ID260830
%K Critical angles, Disturbing function, Elliptic orbit, Initial eccentricity, Legendre polynomials, Restricted three-body problem, Second-order models, Third-body perturbations, Astronomy, Equations of motion, Orbits, Spacecraft.
%X The equations for the variations of the Keplerian elements of the orbit of a spacecraft perturbed by a third body are developed using a single average over the motion of the spacecraft, considering an elliptic orbit for the disturbing body. A comparison is made between this approach and the more used double averaged technique, as well as with the full elliptic restricted three-body problem. The disturbing function is expanded in Legendre polynomials up to the second order in both cases. The equations of motion are obtained from the planetary equations, and several numerical simulations are made to show the evolution of the orbit of the spacecraft. Some characteristics known from the circular perturbing body are studied: circular, elliptic equatorial, and frozen orbits. Different initial eccentricities for the perturbed body are considered, since the effect of this variable is one of the goals of the present study. The results show the impact of this parameter as well as the differences between both models compared to the full elliptic restricted three-body problem. Regions below, near, and above the critical angle of the third-body perturbation are considered, as well as different altitudes for the orbit of the spacecraft. © 2013 R. C. Domingos et al.
%@language en