Access to Mars from Earth–Moon libration point orbits: Manifold and direct options

• A procedure to compute maneuver-free transfers between EM and SE systems is developed.
• General procedures to compute transfers from EM halo orbits to Mars were developed.
• Multiple scenarios from EM halo orbits to Mars were investigated.
• All results were transitioned to a higher-fidelity model.

This investigation is focused specifically on transfers from Earth–Moon L1/L2 libration point orbits to Mars. Initially, the analysis is based on the circular restricted three-body problem to utilize the framework of the invariant manifolds. Various departure scenarios are compared, including arcs that leverage manifolds associated with the Sun–Earth L2 orbits as well as non-manifold trajectories. For the manifold options, ballistic transfers from Earth–Moon L2 libration point orbits to Sun–Earth L1/L2 halo orbits are first computed. This autonomous procedure applies to both departure and arrival between the Earth–Moon and Sun–Earth systems. Departure times in the lunar cycle, amplitudes and types of libration point orbits, manifold selection, and the orientation/location of the surface of section all contribute to produce a variety of options. As the destination planet, the ephemeris position for Mars is employed throughout the analysis. The complete transfer is transitioned to the ephemeris model after the initial design phase. Results for multiple departure/arrival scenarios are compared.