  Attitude control of spacecraft during an impulsive orbital maneuver is a
vital task. Many spacecraft and launchers use the gimbaled thrust vector
control (TVC) in their attitude control system during an orbital maneuver.
Mathematical modeling of the gimbal actuator is an important task because we
should show the applicability of the gimbaled-TVC in a spacecraft. In this
paper, a spin-stabilized spacecraft equipped with one degree of freedom (DoF)
gimbaled-thruster and two reaction wheels (RWs) is considered. The control
goals are disturbance rejection and thrust vector (spin-axis) stabilization
based on one DoF gimbal actuator and two RWs. The gimbal is assumed to be
equipped with a gearbox and a DC electric motor. This actuator must supply the
gimbal torque to rotate the spacecraft nozzle. The mathematical model of the
mentioned spacecraft is extended with respect to the DC motor equations. In
order to investigate the applicability of the proposed method, an industrial DC
electric motor is considered for the gimbal actuator. The simulation results
prove that an industrial DC electric motor is able to be used for attitude
control of the mentioned spacecraft. The simulation results indicate the
applicability of the proposed control method in an impulsive orbital maneuver.
