@Article{DomingosPradMora:2013:StSiDo,
author = "Domingos, R. C. and Prado, Antonio Fernando Bertachini de Almeida
and Moraes, R. Villhena de",
affiliation = "Instituto Nacional de Pesquisas Espaciais (INPE), 12227-010
S{\~a}o Jos{\'e} dos Campos, SP, Brazil and {Instituto Nacional
de Pesquisas Espaciais (INPE)} and Universidade Federal de
S{\~a}o Paulo (UNIFESP), 12231-280 S{\~a}o Jos{\'e} dos Campos,
SP, Brazil",
title = "A study of single- and double-averaged second-order models to
evaluate third-body perturbation considering elliptic orbits for
the perturbing body",
journal = "Mathematical Problems in Engineering",
year = "2013",
volume = "2013",
number = "ID260830",
keywords = "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.",
abstract = "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.",
doi = "10.1155/2013/260830",
url = "http://dx.doi.org/10.1155/2013/260830",
issn = "1024-123X",
label = "scopus 2013-11",
language = "en",
urlaccessdate = "21 maio 2024"
}