In this research, a new control law for the trajectory correction maneuver (TCM) is proposed for a spacecraft assumed to be actuated by a low thruster such as an electric propulsion system. During the cruise phase of an interplanetary mission, trajectory errors accumulate continuously owing to unpredictable perturbation forces. In previous research, TCM algorithms were developed under the assumption that the thruster is impulsive. Since the required delta velocity for the TCM is relatively small and there are numerous advancements currently underway in electric propulsion systems, this paper proposes a new control law for the TCM using a low thruster. In the proposed control law, the B-plane targeting method widely used in interplanetary missions is employed as a target parameter and the Lyapunov feedback control theory is also used. The efficiency of the new control law is demonstrated through numerical simulations.