@InCollection{FelipePrad:2000:OpMaTh,
author = "Felipe, Gislaine de and Prado, Antonio Fernando Bertachini de
Almeida",
title = "Optimal maneuvers in three-dimensional swing by trajectories",
booktitle = "Col{\'o}quio Brasileiro de Din{\^a}mica Orbital, 9 Advances in
Space Dynamics",
year = "2000",
editor = "Prado, Antonio Fernando Bertachini de Almeida.",
pages = "84--98",
keywords = "ENGENHARIA E TECNOLOGIA ESPACIAL, astrodin{\^a}mica, trajetorias
espaciais, mecanica celeste, manobras de orbitas, astrodynamics,
spacecraft trajectories, celestial mechanics, orbital maneuvers.",
abstract = "The swing-by maneuver uses a close approach with a celestial body
to modify the velocity, energy and angular momentum of a
spacecraft. The literature has several papers studying this
problem, usually using a patched-conic approximation. In the
present paper the swing-by maneuvers are studied and classified
under the model given by the three-dimensional restricted
three-body problem. To show the results, the orbits of the
spacecraft are classified in four groups: elliptic direct,
elliptic retrograde, hyperbolic direct and hyperbolic retrograde.
Then, the modification in the orbit of the spacecraft due to the
close approach is shown in plots that specify from which group of
orbits the spacecraft is coming and to which group it is going.
The results generated here are used to solve optimal problems,
such as finding trajectories that satisfy some given constraints
(such as achieving an escape or a capture) with some parameters
being extremized (position, velocity, etc ...). Three optimal
problems are solved in this paper to show this application.",
label = "8990",
seriestitle = "Advances in Space Dynamics",
targetfile = "2000_felipe3.pdf",
urlaccessdate = "18 jan. 2021"
}