This paper proposes a series of estimated solutions with Electric Propulsion, based on Edelbaum’s approximation, for the preliminary calculation of the propellant consumption and the required orbital changes in periapsis and apoapsis maneuvers during an interplanetary mission to Near-Earth Asteroids. A set of 75 fictitious asteroids is considered to study the influence of the orbital parameters on the response of the method, with a revolution period close to one year and small eccentricity and inclination, and the assumed time of flight for the mission is three years, so three burning arcs are performed. The estimation does not need numerical integration, but only the resolution of two three-variable algebraic systems is necessary to define the whole transfer; thus, the computational time and cost are significantly reduced.