In the last years the Moon has been in the interests of Space Economy, both for commercial and scientific purposes. More and more projects and missions concerning our natural satellite are designed and, therefore, low-cost transfers are required in the current environment. This thesis focuses on low-thrust Earth-Moon transfer trajectories that use electric propulsion, key of this new space exploration phase. In particular, the research is based on a three-body model, the Circular Restricted Three-Body Problem, chosen because of its accuracy with respect to others, like the Two- Body Problem. In addition, it provides the tools to understand the nuances and the complexity of the dynamics in the binary system.