Multi-body resonance orbit generation and application within a hybrid optimal control framework

This paper details early work to incorporate resonance orbits, their invariant manifolds, and associated families into an automated global optimization tool for solution of optimal impulsive and low-thrust spacecraft trajectories in multibody environments. Previous work by the authors have shown the ability to use other key dynamical structure of the circular restricted three-body problem (e.g. libration point orbits and their invariant manifolds) within the same automated global optimization framework to produce low-energy trajectory solutions. We first show how to generate resonance orbits of the first species, providing examples of the Earth-Moon and Jupiter-Europa systems, and proceed to show how these structures are used within the optimization framework. Several non-trivial impulsive and low-thrust trajectory problems from low-Earth to resonance orbits, and resonance-resonance transfers are shown with Pareto front solutions.