%0 Book Section
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%3 9233.pdf
%X In the present paper the swing-by maneuvers are studied under the model given by the threedimensional circular restricted three-body problem. This maneuver can be identified by five independent parameters: Vp, the magnitude of the velocity of the spacecraft at periapsis; y, the angle between the velocity vector at periapsis and the intersection between the horizontal plane that passes by the periapsis and the plane perpendicular to the periapsis that holds Vp;rp; r, the distance between the spacecraft and the celestial body during the closest approach; a, the angle between the projection of the periapsis line in the x-y plane and the line that connects the two primaries; á, the angle between the periapsis line and the x-y plane. A numerical algorithm to study this problem was build and used to generate several results. Based in those results, it is possible to control the orbit of the spacecraft with the use of the gravitational forces.
%@secondarydate 20020511
%E Balthazar, José Manoel,
%E  Gonçalves, Paulo Batista,
%E  Brasil, Reyolando M. F. L. R. F. .,
%T Gravitational control of a spacecraft passing by a planet in the three-dimensional space
%S Nonlinear dynamics, chaos, control and their applications to engineering sciences
%@format ISBN:85-900351-3-1
%@secondarytype PRE LN
%K ENGENHARIA E TECNOLOGIA ESPACIAL, swing-by, maneuvers, three-body problem.
%B Nonlinear dynamics, chaos, control and their applications to engineering sciences
%@usergroup administrator
%@group DMC-INPE-MCT-BR
%@secondarykey INPE-9233-PRE/4905
%F 10155
%2 sid.inpe.br/iris@1905/2005/08.03.22.34.58
%I ABCM;SBMAC
%P Cap. 12, 159-168
%4 sid.inpe.br/iris@1905/2005/08.03.22.34.51
%D 2002
%@documentstage not transferred
%A Felipe, Gislaine,
%A Prado, Antonio Fernando Bertachini de Almeida,
%@area ETES