Spin stabilization of a spacecraft for an orbit maneuver

A method for controlling a spacecraft in a transfer orbit, 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 a plurality of electric thrusters installed on the zenith side of the bus by a two-axis gimbal assembly, the method comprising:

• identifying a target spin axis for the spacecraft in the transfer orbit;
• determining gimbal angles for at least one of the electric thrusters that so that thrust forces from the at least one electric thruster are parallel to the target spin axis;
• initiating a bum of the at least one electric thruster at the gimbal angles;
• and
• controlling the momentum subsystem to compensate for a thruster torque produced by the burn of the at least one electric thruster at the gimbal angles.

An apparatus comprising:

• a controller configured to control a spacecraft in a transfer orbit, wherein the spacecraft comprises:
• a bus having a nadir side and a zenith side opposite the nadir side;
• a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft;
• and
• a propulsion subsystem that includes a plurality of electric thrusters installed on the zenith side of the bus, wherein each of the electric thrusters is coupled to the bus by a two-axis gimbal assembly;
• the controller is configured to identify a target spin axis for the spacecraft, to determine gimbal angles for at least one of the electric thrusters so that thrust forces from the at least one electric thruster are parallel to the target spin axis, to initiate a burn of the at least one electric thruster at the gimbal angles, and to control the momentum subsystem to compensate for a thruster torque produced by the burn of the at least one electric thruster at the gimbal angles.