Transfers to Earth–Moon L3 halo orbits

• We present a method for designing transfers from Earth to Earth–Moon L3 Orbits.
• We introduce a pseudo-manifold to enable transfers with durations less than 90 days.
• All trajectories located utilized at least one lunar flyby.
• Transfers cost to L3 orbits are comparable to costs required to L1 or L2 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 L3 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 ΔVsΔVs of approximately 3.2 km/s and flight durations between 44 and 90 days.