Transfers to earth-moon L₃ halo orbits

A method is presented for designing trajectories from Earth to Earth-Moon L₃ halo orbits using dynamical systems theory in the Circular Restricted Three-Body Problem. Stable pseudo-manifold trajectories of L ₃ halo orbits, which behave in a similar manner to stable invariant manifold trajectories, are mapped and close approaches with the Earth are located. In the three-body model, only two deterministic maneuvers are necessary to complete the transfer; an injection maneuver from Earth orbit onto the stable pseudo-manifold trajectory, and a smaller maneuver to transfer from the pseudo-manifold trajectory onto the halo orbit. The transfers analyzed have ΔVs of approximately 3.2 km/s and flight durations between 44 and 90 days.