%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%3 prado_close.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's orbit. The swing-by trajectories are studied and classified under the model given by the elliptic restricted three-body problem. Several simulations are made to show the effects of the eccentricity of the primaries in this maneuver. The position of the secondary in its orbit (specified by its true anomaly) also has effects on the results, and they are quantified. To show the results, the orbit of the spacecraft is 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 the spacecraft's orbit is coming and to which group it is going. Several families of orbits are found and shown in detail. An analysis about the trends as parameters vary is performed, and the influence of each of them is shown and explained. The results presented can also be used to find optimal sets of parameters for several types of problems, such as finding an escape orbit that has minimum velocity at periapsis and other related problems.
%8 July-Aug.
%N 4
%@secondarydate 19980708
%T Close-Approach trajectories in the elliptic restricted problem
%K ENGENHARIA E TECNOLOGIA ESPACIAL, MANOBRA ORBITAL, MECANICA ESPACIAL, TECNICA SWINGBY.
%@secondarytype PRE PI
%@archivingpolicy denypublisher allowfinaldraft
%@usergroup administrator
%@group DMC-INPE-MCT-BR
%@secondarykey INPE-6733-PRE/2755
%F 7900
%@issn 0731-5090
%@issn 1533-3884
%2 sid.inpe.br/iris@1905/2005/07.29.06.02.55
%B Journal of Guidance, Control, and Dynamics
%@versiontype publisher
%P 797-802
%4 sid.inpe.br/iris@1905/2005/07.29.06.02
%@documentstage not transferred
%D 1997
%V 20
%A Prado, Antonio Fernando Bertachini de Almeida,
%@dissemination WEBSCI; COMPENDEX.
%@area ETES