A transfer trajectory framework for the exploration of Phobos and Deimos leveraging resonant orbits

Abstract

While the interest in future missions devoted to Phobos and Deimos increases, missions that explore both moons are expensive in terms of maneuver capabilities partly due to the lack of readily available low-energy transfer options. A design framework that generates transfer trajectories between the Martian moons while leveraging resonant orbits to mitigate this challenge is introduced. Mars–Deimos resonant orbits that offer repeated flybys of Deimos and arrive at Mars–Phobos libration point orbits are investigated, and a nominal mission scenario with transfer trajectories connecting the two is presented here. The flyby characteristics of the Deimos resonant orbits are quantified to validate their usefulness to perform observations of the moon. A strategy to select the appropriate resonant orbits is discussed, and the associated transfer costs are analyzed, both for impulsive and low-thrust propulsion capabilities, within the context of the coupled spatial circular restricted three body problem. The trajectory concepts are then validated in a higher-fidelity ephemeris model. Finally, to prove the validity and flexibility of the proposed framework, different mission scenarios are also considered and the corresponding costs are provided.