Gimbal Actuator Modeling for a Spin-Stabilized Spacecraft Equipped with a 1DoF Gimbaled-Thruster and two Reaction Wheels
کد مقاله : 1030-ISME
حامد کوهی *1، فاطمه قربانی2، منصور کبگانیان3، فرهاد فانی صابری4
1استادیار-دانشکده مهندسی مکانیک-دانشگاه گیلان
2فارغ التحصیل کارشناسی ارشد از دانشگاه خواجه نصیر الدین ظوسی
3عضو هیات علمی دانشکده مهندسی مکانیک دانشگاه گیلان
4عضو هیات علمی پژوهشکده فضایی دانشگاه صنعتی امیرکبیر
چکیده مقاله:
Attitude control of spacecraft during an impulsive orbital maneuver is an important 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 is considered which is equipped with a one degree of freedom (1DoF) gimbaled-thruster and two reaction wheels (RWs). The control goals are disturbance rejection and thrust vector (spin-axis) stabilization based on a 1DoF 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 by considering 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. In the simulation results it is shown that an industrial DC electric motor can be used for attitude control of the mentioned spacecraft. The simulation results show the applicability of the proposed control method in an impulsive orbital maneuver.
کلیدواژه ها:
Thrust Vector Control, Gimbaled-Thruster, Actuator Modeling, DC Electric Motor
وضعیت : مقاله به صورت مشروط برای ارائه شفاهی پذیرفته شده است