Gimbal Actuator Modeling For A Spin-StabilizedSpacecraft Equipped With A 1dof Gimbaled-ThrusterAnd Two Reaction Wheels

Attitude control of spacecraft during an impulsive orbital maneuver is a vital task. many spacecraft andlaunchers use the gimbaled thrust vector control (tvc) in their attitude control system during an orbitalmaneuver. mathematical modeling of the gimbal actuator is an important task because we should show theapplicability of the gimbaled-tvc in a spacecraft. in this paper, a spin-stabilized spacecraft equipped withone degree of freedom (dof) gimbaled-thruster and two reaction wheels (rws) is considered. the controlgoals are disturbance rejection and thrust vector (spin-axis) stabilization based on one dof gimbal actuatorand two rws. the gimbal is assumed to be equipped with a gearbox and a dc electric motor. this actuatormust supply the gimbal torque to rotate the spacecraft nozzle. the mathematical model of the mentionedspacecraft is extended with respect to the dc motor equations. in order to investigate the applicability of theproposed method, an industrial dc electric motor is considered for the gimbal actuator. the simulationresults prove that an industrial dc electric motor is able to be used for attitude control of the mentionedspacecraft. the simulation results indicate the applicability of the proposed control method in an impulsiveorbital maneuver.