The continued development of small satellite technology has expanded the menu of missions that these craft could potentially carry out to Lagrange points, the Moon, and even near Earth objects. Several small sats will be launched as secondary payloads on Explorer Mission 1 (EM-1) in 2018, and will explore different science objectives in the cislunar region. However, due to their limited power and propulsion capabilities as well as a high velocity release condition from EM-1, designing feasible solutions is a challenging task. In addition, launch conditions and spacecraft parameters have larger variability and change more often during the mission design and production phases in comparison to larger explorer and flagship type missions; driving the need for an efficient and robust automated tool set that enables rapid prototyping of mission concepts. In this paper, we apply a hybrid optimal control framework that leverages dynamical structures found in multi-body regimes to explore low-energy solutions to EM-1 small satellite type missions. The hybrid optimal control framework supports a flexible and automated approach that still allows full user guidance via appropriately formed objectives and constraints, while enabling a search of the design space in an intelligent manner that can yield non-intuitive results.