@Article{AlmeidaJúniorPradYokoMerg:2018:SpMoAr,
author = "Almeida J{\'u}nior, Allan Kardec de and Prado, Antonio Fernando
Bertachini de Almeida and Yokoyama, T. and Merguizo Sanchez,
Diogo",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto
Nacional de Pesquisas Espaciais (INPE)} and {Universidade Estadual
Paulista (UNESP)} and {Instituto Nacional de Pesquisas Espaciais
(INPE)}",
title = "Spacecraft motion around artificial equilibrium points",
journal = "Nonlinear Dynamics",
year = "2018",
volume = "91",
number = "3",
pages = "1489",
keywords = "Astrodynamics, Equilibrium points, Restricted three-body problem,
Nonlinear systems.",
abstract = "The main goal of this paper is to describe the motion of a
spacecraft around an artificial equilibrium point in the circular
restricted three-body problem. The spacecraft is under the
gravitational influence of the Sun and the Earth, as primary and
secondary bodies, subjected to the force due to the solar
radiation pressure and some extra perturbations. Analytical
solutions for the equations of motion of the spacecraft are found
using several methods and for different extra perturbations. These
solutions are strictly valid at the artificial equilibrium point,
but they are used as approximations to describe the motion around
this artificial equilibrium point. As an application of the
method, the perturbation due to the gravitational influence of
Jupiter and Venus is added to a spacecraft located at a chosen
artificial equilibrium point, near the Lagrangian point of the
Sun-Earth system. The system is propagated starting from this
point using analytical and numerical solutions. Comparisons
between analytical-analytical and analytical-numerical solutions
for several kinds of perturbations are made to guide the choice of
the best analytical solution, with the best accuracy.",
doi = "10.1007/s11071-017-3959-2",
url = "http://dx.doi.org/10.1007/s11071-017-3959-2",
issn = "0924-090X",
label = "self-archiving-INPE-MCTIC-GOV-BR",
language = "en",
targetfile = "almeida_spacecraft.pdf",
urlaccessdate = "28 abr. 2024"
}