Additional Information
| Author(s) | Bărbosu, Mihai, Oproiu, Tiberiu |
|---|
Rein’s trajectories for the restricted three-body problem. Application to the Earth-Moon system
Mihai Bărbosu ♦ Tiberiu Oproiu
Abstract
creative_2013_22_1_019_022_abstractThis 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.
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