Rein’s trajectories for the restricted three-body problem. Application to the Earth-Moon system

Abstract

This paper presents trajectories of a spacecraft moving in the gravitational field given by Rein’s model for the restricted three-body problem. For various initial conditions, closed orbits are determined using Maple’s numerical capabilities for ODE. Applications to the Earth-Moon system are considered, with trajectories computed around the stable L4 Lagrangian point.