A system comprising a spacecraft and a controller, wherein the spacecraft comprises: a bus having a nadir side and a zenith side opposite the nadir side; a momentum subsystem configured to store angular momentum relative to a center of mass of the spacecraft; and a propulsion subsystem that includes only electric thrusters, the electric thrusters comprising a plurality of electric thrusters installed on the zenith side of the bus to produce a change in velocity (delta-V) on the spacecraft, said change in velocity aligned with a target spin axis about which the spacecraft is configured to spin, wherein each of the electric thrusters is coupled to the bus by a two-axis gimbal assembly (324- 327), wherein each of the electric thrusters is configured to burn at gimbal angles for the each of the electric thrusters; wherein the momentum subsystem is configured to compensate for a thruster torque produced by the burn of at least one electric thruster at the gimbal angles; the controller is configured to identify the target spin axis for the spacecraft, to determine the gimbal angles for the electric thrusters so that thrust forces from the at least one electric thruster are parallel to the target spin axis, and to initiate a burn of the at least one electric thruster at the gimbal angles; and the gimbal angles are determined such that the thrust forces for each of the electric thrusters are parallel to the target spin axis and are not going through the center of mass of the spacecraft. the spacecraft comprises: a bus having a nadir side and a zenith side opposite the nadir side; a momentum subsystem configured to store angular momentum relative to a center of mass of the spacecraft; and a propulsion subsystem that includes only electric thrusters, the electric thrusters comprising a plurality of electric thrusters installed on the zenith side of the bus to produce a change in velocity (delta-V) on the spacecraft, said change in velocity aligned with a target spin axis about which the spacecraft is configured to spin, wherein each of the electric thrusters is coupled to the bus by a two-axis gimbal assembly (324- 327), wherein each of the electric thrusters is configured to burn at gimbal angles for the each of the electric thrusters; wherein the momentum subsystem is configured to compensate for a thruster torque produced by the burn of at least one electric thruster at the gimbal angles; a bus having a nadir side and a zenith side opposite the nadir side; a momentum subsystem configured to store angular momentum relative to a center of mass of the spacecraft; and a propulsion subsystem that includes only electric thrusters, the electric thrusters comprising a plurality of electric thrusters installed on the zenith side of the bus to produce a change in velocity (delta-V) on the spacecraft, said change in velocity aligned with a target spin axis about which the spacecraft is configured to spin, wherein each of the electric thrusters is coupled to the bus by a two-axis gimbal assembly (324- 327), wherein each of the electric thrusters is configured to burn at gimbal angles for the each of the electric thrusters; wherein the momentum subsystem is configured to compensate for a thruster torque produced by the burn of at least one electric thruster at the gimbal angles; the controller is configured to identify the target spin axis for the spacecraft, to determine the gimbal angles for the electric thrusters so that thrust forces from the at least one electric thruster are parallel to the target spin axis, and to initiate a burn of the at least one electric thruster at the gimbal angles; and the gimbal angles are determined such that the thrust forces for each of the electric thrusters are parallel to the target spin axis and are not going through the center of mass of the spacecraft.