Trajectory optimization for multiple asteroid rendezvous mission through hybrid propulsion

In this paper we investigate optimal trajectories for Near-Earth Asteroid (NEA) rendezvous missions using a hybrid propulsion system, combining solar sailing and solar electric propulsion (SEP). An approach based on physical programming and Gauss pseudo-spectral method is proposed for the rendezvous trajectory multi-objective optimization, aiming at minimizing both total propellant consumption and mission duration. For missions to one NEA, results show that hybrid propulsion is capable of producing different trajectories according to the designer's preference on saving propellant consumption or flight time. The results also show that the hybrid propulsion makes more possibilities on rendezvous trajectory in varied NEA exploration missions.