%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@secondarymark B_ENGENHARIAS_I B_ENGENHARIAS_II B_ENGENHARIAS_III B_ENGENHARIAS_IV C_GEOCIÊNCIAS C_INTERDISCIPLINAR
%D 2008
%4 dpi.inpe.br/plutao@80/2008/12.04.12.20.06
%T Transfer orbits to/from the Lagrangian points in the restricted four-body problem
%@usergroup lattes
%@usergroup marciana
%V 63
%@affiliation
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%F lattes: 7340081273816424 2 CabettePrad:2008:TrOrTo
%@versiontype publisher
%X he well-known Lagrangian points that appear in the planar restricted three-body problem are very important for astronautical applications. They are five points of equilibrium in the equations of motion, what means that a particle located at one of those points with zero velocity will remain there indefinitely. The collinear points (L-1, L-2 and L-3) are always unstable and the triangular points (L-4 and L-5) are stable in the present case studied (Earth-Sun system). They are all very good points to locate a space-station, since they require a small amount of AV (and fuel), the control to be used, for station-keeping. The triangular points are especially good for this purpose, since they are stable equilibrium points. In this paper, the planar restricted four-body problem applied to the Sun-Earth-Moon-Spacecraft is combined with numerical integration and gradient methods to solve the two-point boundary value problem. This combination is applied to the search of families of transfer orbits between the Lagrangian points and the Earth, in the Earth-Sun system, with the minimum possible cost of the control used. So, the final goal of this paper is to find the magnitude of the two impulses to be applied in the spacecraft to complete the transfer: the first one when leaving/arriving at the Lagrangian point and the second one when arriving/living at the Earth. The dynamics given by the restricted four-body problem is used to obtain the trajectory of the spacecraft, but not the position of the equilibrium points. Their position is taken from the restricted three-body model. The goal to use this model is to evaluate the perturbation of the Sun in those important trajectories, in terms of fuel consumption and time of flight. The solutions will also show how to apply the impulses to accomplish the transfers under this force model. The results showed a large collection of transfers, and that there are initial conditions (position of the Sun with respect to the other bodies) where the force of the Sun can be used to reduce the cost of the transfers.
%@area ETES
%@electronicmailaddress
%@electronicmailaddress abertachini@terra.com.br
%@documentstage not transferred
%K Astrodinamica.
%@archivingpolicy denypublisher denyfinaldraft24
%@e-mailaddress abertachini@terra.com.br
%@doi 10.1016/j.actaastro.2008.05.005
%@issn 0094-5765
%@group
%@group DMC-ETE-INPE-MCT-BR
%N 11-12
%@dissemination WEBSCI; PORTALCAPES; COMPENDEX.
%P 1221-1232
%A Santos Cabette, Regina Elaine,
%A Prado, Antonio Fernando Bertachini de Almeida,
%B Acta Astronautica
%2 dpi.inpe.br/plutao@80/2008/12.04.12.20.07
%@secondarytype PRE PI