The design of efficient control strategies for spacecraft operating in multi-body gravita- tional environments represents a fundamental challenge in astrodynamics. In particular, the Circular Restricted Three-Body Problem (CR3BP) provides a representative frame- work for modeling the motion of a spacecraft under the influence of two primary bodies, such as the Earth–Moon (EM) system. Although this model exhibits a rich dynamical structure, including periodic orbits and invariant manifolds, the inherent instability of these solutions makes their direct control particularly challenging. Traditional control approaches based on trajectory tracking are often inadequate in this context, as they require continuous control effort and fail to exploit the natural dynamics of the system.