LEVERAGING RESONANT ORBIT MANIFOLDS TO DESIGN TRANSFERS BETWEEN LIBRATION POINT ORBITS IN MULTI-BODY REGIMES

摘要

Resonant orbits have been widely employed in mission design for planetaryflyby trajectories (JEO) and, more recently, as a source of long-term stability(IBEX). Yet, resonant orbits have not been explored extensively as transfermechanisms between non-resonant orbits in multi-body systems. To highlightthe benefit of employing resonant orbits for transfers and given the increasedinterest in employing libration point orbits for a variety of purposes, 2D and3D transfers from LEO to the vicinity of the Earth-Moon libration points viaresonant arcs are presented. Solutions are efficiently generated in the circularrestricted three-body model and transitioned to a higher-fidelity model for validation.Direct optimization can further reduce the propellant requirements anda system translation technique is defined to add versatility to the proposedtransfer design process, allowing for the quick translation of Earth-Moon transfersto other three-body systems.