@Article{FerreiraPradWint:2018:PlPoSw,
author = "Ferreira, Alessandra F. S. and Prado, Antonio Fernando Bertachini
de Almeida and Winter, Othon C.",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto
Nacional de Pesquisas Espaciais (INPE)} and {Universidade Estadual
Paulista (UNESP)}",
title = "Planar powered Swing-By maneuvers to brake a spacecraft",
journal = "Computational and Applied Mathematics",
year = "2018",
volume = "37",
number = "Suppl. 1",
pages = "202--219",
month = "Dec.",
keywords = "Powered Swing-By, Close approach, Impulsive maneuvers, Spacecraft
trajectory, Energy decrease.",
abstract = "The Swing-By maneuver is a technique used in many space mission to
modify the trajectory of a spacecraft. The most usual goal is to
increase the energy of the spacecraft, but it is also possible to
reduce this energy. An important application is to break a
spacecraft coming to the Earth using a Swing-By with the moon,
which is the example used in the present paper. Other
possibilities also exist, such as reducing the velocity of a
spacecraft going to the planets Mercury or Venus. The goal is to
help a possible capture by the planet, or at least to provide a
passage with smaller velocities to allow better observations
during the passage. Therefore, the goal of the present paper is to
study the energy loss that a spacecraft may have during a powered
Swing-By maneuver, which is a maneuver that combines a close
approach by a celestial body with the application of an impulsive
maneuver. The behavior of the energy variation is analyzed as a
function of the parameters related to the pure gravity maneuver:
periapsis radius, angle of approach and approach velocity; and the
parameters related to the impulsive maneuver: the location of
application of the impulse and its direction and magnitude. The
maneuver is performed in a system composed by two bodies, such as
the Earth-moon system, around the secondary body, and the energy
is measured with respect to the primary body of the system. This
problem is solved by developing a mathematical algorithm that
guides larger efforts in terms of computer simulations. The
results show maps of conditions made from the numerical
simulations for different points of application and direction of
the impulse, where the maneuver is advantageous and how much more
energy can be removed from the spacecraft.",
doi = "10.1007/s40314-017-0483-4",
url = "http://dx.doi.org/10.1007/s40314-017-0483-4",
issn = "2238-3603",
language = "en",
targetfile = "ferreira_planar.pdf",
urlaccessdate = "28 mar. 2024"
}