Abstract:The idea of the present paper is to study orbital transfers for a spacecraft from the Lagrangian points in the Earth-Moon system to the Earth, as well as to the other Lagrangian points. The model used is the restricted three-body problem with the addition of the effects of the radiation pressure in the trajectory of the spacecraft. The basic maneuver is a bi-impulsive transfers under the dynamics explained before. The results show that the radiation pressure has an influence in the process, although not very l… Show more
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