@Article{CavalcaPradGomeMerg:2020:QuSaOr,
author = "Cavalca, Marina Pires de Oliveira and Prado, Antonio Fernando
Bertachini de Almeida and Gomes, Vivian M. 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 = "{"}Quasi satellite orbits{"} to observe a possible small moon of
Pallas",
journal = "New Astronomy",
year = "2020",
volume = "75",
pages = "UNSP 101317",
month = "Feb.",
keywords = "Astrodynamics, Restricted three-body problem, Quasi satellite
orbits, Space trajectories.",
abstract = "The purpose of this paper is to make a numerical search for
natural orbits that can be used for a spacecraft to study a
possible small moon of Pallas. There are many speculations about
the existence of a small companion around this large asteroid, so
finding and classifying orbits around this possible celestial body
is an interesting problem in astrodynamics and that can be used
for a spacecraft to observe this body. It is assumed that this
moon has a radius that can vary from 0.125 to 1 km and that is
located 750 or 500 km away from the center of Pallas. The idea is
to show the effects of this parameter in the orbits around this
moon. It means that the moon is much smaller than Pallas, so
Keplerlan orbits are not possible around it. To solve this
problem, it is possible to find some special orbits that are
called {"}Quasi Satellite Orbits{"} (QSO). They are orbits
dominated by the gravity of Pallas, but that use the smaller
perturbation from the moon to keep the spacecraft close to it. The
present work searches for orbits that make the spacecraft to
remain at given limits in its distance from the moon, like in the
range from 3 to 50 km, the values used as an example in the
present paper. This value is used because it is a good range to
observe the body without getting to close to it, so reducing the
risks of collisions. Each trajectory can be identified by the
initial conditions of the spacecraft with respect to the moon,
which means its initial position and velocity. The dynamics
considers the restricted three-body problem and the influence of
the solar radiation pressure, because some spacecraft may have
higher values for the area-to-mass ratio, which gives a
non-negligible effect in the trajectory of the spacecraft.",
doi = "10.1016/j.newast.2019.101317",
url = "http://dx.doi.org/10.1016/j.newast.2019.101317",
issn = "1384-1076",
language = "en",
targetfile = "cavalca_quasi.pdf",
urlaccessdate = "29 mar. 2024"
}