%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@archivingpolicy denypublisher denyfinaldraft
%3 6(17).pdf
%X This paper presents a survey on space trajectories in the circular restricted three-body problem. In this situation, a spacecraft moves under the gravitational forces of two bodies, which are assumed to be in circular orbits. First of all, there is a search for orbits that can be used to transfer a spacecraft from one body back to the same body or to transfer a spacecraft from one body to the respective Lagrangian points L4 and L5. The method employed is to solve the Two-Point Boundary Value Problem. The close approach between the spacecraft and the celestial bodies involved is also studied in the three-dimensional space. Then, the gravitational capture is studied. It is a characteristic of some dynamical systems, like the three- or four-body system, where a hyperbolic orbit around a celestial body can be transformed in an elliptic orbit without the use of any propulsive system.
%N 4
%T A survey on space trajectories in the model of three bodies
%@electronicmailaddress prado@dem.inpe.br
%K astrodynamics, orbital maneuvers, restricted problem, gravitational capture, swing-by, Lagrangian points.
%@secondarytype PRE PI
%@usergroup administrator
%@usergroup marciana
%@usergroup vinicius
%@group DMC-INPE-MCT-BR
%@copyholder SID/SCD
%@secondarykey INPE-14931-PRE/9843
%@issn 1562-8353
%@issn 1813-7385
%2 sid.inpe.br/mtc-m17@80/2006/12.11.12.58.55
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@project FAPESP (Contract 2003/03262-4); CNPq (Grant 300828/2003-9).
%B Nonlinear Dynamics and Systems Theory
%@versiontype publisher
%P 389-400
%4 sid.inpe.br/mtc-m17@80/2006/12.11.12.58
%@documentstage not transferred
%D 2006
%V 6
%A Prado, Antonio Fernando Bertachini de Almeida,
%@dissemination WEBSCI; PORTALCAPES.
%@area ETES