%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@archivingpolicy denypublisher denyfinaldraft
%@dissemination WEBSCI; PORTALCAPES.
%3 3(10).pdf
%X In the present paper the swing-by maneuvers are studied and classified under the model given by the three-dimensional restricted three-body problem. The modification in the orbit of the spacecraft due to the close approach is shown in plots that specify from which type of orbits the spacecraft is coming and to which type 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...).
%N 1
%T Optimal maneuvers using a three dimensional gravity assist
%K Astrodynamics, swing-by, orbital maneuvers, gravity-assist, restricted problem.
%@secondarytype PRE PI
%@usergroup administrator
%@usergroup marciana
%@usergroup simone
%@group DMC-INPE-MCT-BR
%@group DMC-INPE-MCT-BR
%@secondarykey INPE--PRE/
%@issn 1562-8353
%@issn 1813-7385
%2 sid.inpe.br/iris@1916/2005/12.12.18.25.41
%@affiliation Instituto Nacional de Pesquisas Espaciais, Divisão de Mecânica Espacial e Controle  (INPE.DMC)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%B Nonlinear Dynamics and Systems Theory
%@versiontype publisher
%P 39-48
%4 sid.inpe.br/iris@1916/2005/12.12.18.25
%@documentstage not transferred
%D 2005
%V 5
%A Felipe, Gislaine de,
%A Prado, Antonio Fernando Bertachini de Almeida,
%@area ETES