@Article{AlmeidaJúniorPradYokoMerg:2020:SeOrOb,
author = "Almeida J{\'u}nior, Allan Kardec de and Prado, Antonio Fernando
Bertachini de Almeida and Yokoyama, Tadashi 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 = "Searching for orbits to observe the poles of celestial bodies",
journal = "Advances in Space Research",
year = "2020",
volume = "66",
number = "10",
pages = "2378--2401",
month = "Nov.",
keywords = "Astrodynamics, Nonlinear systems, Artificial equilibrium points,
Restricted three-body problem.",
abstract = "The objective of the present paper is to show a method to find
orbits near artificial equilibrium points for a satellite equipped
with a continuous thrust that allows it to stay near the poles of
a celestial body. The physical system includes the presence of a
moon of the celestial body under observation, and the perturbation
caused by this moon is counteracted by an algorithm to help the
satellite to stay close to its original position, instead of
escape from it. The equations of motion are changed under some
approximations, and analytical solutions for these equations are
obtained and analyzed. Initial conditions are used such that their
secular terms are nullified. These solutions are restricted to a
short period of time, but we propose a method in which there are
periodic updates in the thrust. Thus, the solutions can be
extended for the duration of the mission. A numerical simulation
is obtained, whose results are required to be in agreement with
the analytical solution using these periodic adjustments of the
thrust. This agreement means that the motion of the spacecraft
remains bounded close to its initial position for longer times.
Several systems with different sizes and mass parameters are used
to show the results of the research, like Sun-Earth-Moon,
Sun-Ida-Dactyl, Sun-Saturn-Titan and Sun-Mars-Phobos systems. The
results also indicate the locations of points that require minimum
magnitude of the thrust.",
doi = "10.1016/j.asr.2020.07.043",
url = "http://dx.doi.org/10.1016/j.asr.2020.07.043",
issn = "0273-1177 and 1879-1948",
language = "en",
targetfile = "almeida junior_searching.pdf",
urlaccessdate = "29 mar. 2024"
}