In this paper we introduce a framework for the automated solution of low energy trajectories. Specifically, we are interested in solving constrained global spacecraft trajectory optimization problems in multi-body regimes (e.g. cislunar missions) that leverage the natural global transport of the multi-body dynamical system to provide low propellant control solutions. A main difficulty in automated global solution of this type of problem has been automating dynamical systems techniques to find ideal candidate boundary conditions and then connecting these structures in a natural way for global and local optimization schemes to be successful. We demonstrate the evolving capability of our framework by solving a multi-phase low-thrust cislunar trajectory problem.