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.