%0 Book Section
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%3 2000_felipe3.pdf
%X 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.
%@secondarydate 20010416
%E Prado, Antonio Fernando Bertachini de Almeida.,
%T Optimal maneuvers in three-dimensional swing by trajectories
%S Advances in Space Dynamics
%@format ISBN:85-901487-1-8
%@secondarytype PRE LN
%K ENGENHARIA E TECNOLOGIA ESPACIAL, astrodinâmica, trajetorias espaciais, mecanica celeste, manobras de orbitas, astrodynamics, spacecraft trajectories, celestial mechanics, orbital maneuvers.
%B Colóquio Brasileiro de Dinâmica Orbital, 9 Advances in Space Dynamics
%@usergroup administrator
%@group DMC-INPE-MCT-BR
%@secondarykey INPE-8044-PRE/3860
%F 8990
%2 sid.inpe.br/iris@1905/2005/07.29.22.33.08
%P 84-98
%4 sid.inpe.br/iris@1905/2005/07.29.22.33.01
%D 2000
%@documentstage not transferred
%A Felipe, Gislaine de,
%A Prado, Antonio Fernando Bertachini de Almeida,
%@area ETES