@Article{GomesMurcPradGole:2016:AtClAp,
author = "Gomes, Vivian Martins and Murcia Pineros, Jhonathan Orlando and
Prado, Antonio Fernando Bertachini de Almeida and Golebiewska,
Justyna",
affiliation = "{Universidade Estadual Paulista (UNESP)} and {Instituto Nacional
de Pesquisas Espaciais (INPE)} and {Instituto Nacional de
Pesquisas Espaciais (INPE)} and {Adam Mickiewicz University}",
title = "Atmospheric close approaches with the Earth considering drag and
lift forces",
journal = "Computational \& Applied Mathematics",
year = "2016",
volume = "35",
number = "3",
pages = "817--833",
month = "Oct.",
keywords = "Astrodynamics, Swing-by, Orbital maneuvers, Aero-gravity maneuver,
Close approach.",
abstract = "A maneuver called {"}Aero-Gravity Assisted{"} is known in the
literature to increase the energy gains given by a close approach
between a spacecraft and a planet using the atmosphere of the
planet. In a sequence of studies related to this problem, the
present paper studies close approaches between a spacecraft and
the Earth, in situations where the passage is close enough to the
surface of the Earth such that the spacecraft crosses its
atmosphere. The dynamical model considers the atmosphere of the
Earth, in terms of drag and lift, the gravitational fields of the
Earth and the Sun, assumed to be points of mass, and the
spacecraft. The Earth and the Sun are assumed to be in circular
coplanar orbits around their common center of mass. The equations
of motion are the ones given by the circular planar restricted
three-body problem with the addition of the forces generated by
the atmospheric drag and lift. The primary objective is to map the
variations of energy of the orbits of the spacecraft due to this
close approach. The results show how the atmosphere affects the
trajectory of the spacecraft, generating situations where the
variation of energy changes sign with respect to the gravity part
of the maneuver or where they have a zero net result, based in the
equilibrium between atmospheric and gravity forces. This result
opens the possibility of changing only the eccentricity of the
orbit, keeping fixed its semi-major axis.",
doi = "10.1007/s40314-015-0256-x",
url = "http://dx.doi.org/10.1007/s40314-015-0256-x",
issn = "2238-3603",
language = "en",
targetfile = "gomes_atmospheric.pdf",
urlaccessdate = "27 nov. 2020"
}