  In this paper, we seek optimal solutions for a transfer from a parking orbit
around the Moon to a halo orbit around $L_2$ of the Earth-Moon system, by
applying a single maneuver and exploiting the stable invariant manifold of the
hyperbolic parking solution at arrival. For that, we propose an optimization
problem considering as variables both the orbital characteristics of a parking
solution around the Moon, (namely, its Keplerian elements) and the
characteristics of a transfer trajectory guided by the stable manifold of the
arrival Halo orbit. The problem is solved by a nonlinear programming method
(NLP), aiming to minimize the cost of $\Delta V$ to perform a single maneuver
transfer, within the framework of the Earth-Moon system of the circular
restricted three-body problem. Results with low $\Delta V$ and suitable time of
flight show the feasibility of this kind of transfer for a Cubesat.
