This thesis focuses on the problem of the phasing maneuver for a solar electric platform. By giving as input the orbital elements, in order to define the initial and final orbit, the position we want the satellite to reach, the phasing altitude, and the propulsive system, system mass and dymensions that characterize the platform, the program performs the phasing maneuver. The phasing maneuver controls the position of the solar electric platform in terms of longitude (for geostationary orbit), true longitude (equatorial orbit) or argument of latitude (inclined orbit). For the analysis of the maneuver to be performed, we start from chemical propulsion's manuver logic.