%0 Journal Article
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%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@resumeid 8JMKD3MGP5W/3C9JGJA
%@archivingpolicy denypublisher denyfinaldraft
%@usergroup administrator
%@usergroup vinicius
%3 prado-orbital maneuvers.pdf
%X This paper is concerned with trajectories to transfer a spacecraft between the Lagrangian points of the Sun-Earth system and the primaries. The Lagrangian points have important applications in astronautics, since they are equilibrium points of the equation of motion and very good candidates to locate a satellite or a space station. The planar circular restricted three-body problem in two dimensions is used as the model for the Sun-Earth system, and Lamaître regularization is used to avoid singularities during the numerical integration required to solve the Lambert's three-body problem. The results show families of transfer orbits, parameterized by the transfer time.
%8 Apr.-June
%N 2
%T Orbital maneuvers between the lagrangian points and the primaries in the Earth-Sun system
%@electronicmailaddress prado@dem.inpe.br
%@secondarytype PRE PI
%K ENGENHARIA  E TECNOLOGIA ESPACIAIS, astrodynamics, lagrangian points, orbital maneuvers, impulsive transfers.
%@group DMC-INPE-MCT-BR
%@copyholder SID/SCD
%@secondarykey INPE-14437-PRE/9517
%@issn 0100-7386
%2 sid.inpe.br/mtc-m17@80/2006/12.11.13.34.43
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@project Dinâmica Órbital
%B Journal of the Brazilian Society of Mechanical Sciences and Engineering
%P 131-139
%4 sid.inpe.br/mtc-m17@80/2006/12.11.13.34
%D 2006
%V 28
%A Prado, Antonio Fernando Bertachini de Almeida,
%@dissemination WEBSCI; PORTALCAPES.
%@area ETES