Conclusion
Space Trajectories. Three-Body Problem

The restricted circular three-body problem (CR3BP) reveals the possibility of economic transfers based on orbit-invariant varieties. In reality, the stars are not in circular orbits and the vehicle is subject to perturbing forces. Targeting Correction Maneuvers (TCM) and station-keeping maneuvers are required to follow a planned path with the CR3BP model. In-orbit rendezvous and eclipse constraints will also have to be taken into account for the establishment of a future lunar station on a halo orbit.