Transferência orbitais envolvendo órbitas do tipo halo / Transfers involving orbits of type halo

AUTOR(ES)
DATA DE PUBLICAÇÃO

2004

RESUMO

In space activities, it is of great importance the study of trajectories that the space vehicles should follow to complete a mission. In the present work, maneuvers involving Halo orbits for several systems of primary are studied. To accomplish this study the method of Lindstedt-Poincaré is used for the etermination of the orbits and the method of Lambert is used for the transfers involved in both cases for the transfers with free time for the rendez-vous maneuvers. To exemplify the techniques developed here a complete mission in the Earth-Moon system involving the restricted three bodies problem is calculated in details. It is still studied in this work the same maneuvers for the restricted bi-circular problem of four bodies. To proceed, a propelled model for the swing-by is studied and its efficiency in transfering a spacecraft from a parking orbit around the Earth to a Halo orbit in the Earth-Sun system using a swing-by with the Moon is measured.

ASSUNTO(S)

orbital mechanics transferência de órbitas spacecraf orbits Órbitas de veículos espaciais orbital rendezvous technology and space engineering tecnologia e engenharia espacial Órbita de rendezvous transfer orbits manobra orbital problemas de três corpos orbital maneuvers three body problems mecânica orbital

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