Abstract
This paper presents a new method for precise attitude control of a spinning satellite using CMG (Control Moment Gyro). CMG has been considered to be quite promising for precise attitude control of a satellite with long life. Nevertheless, its application to spin axis control has not been fully studied. The biggest trouble we meet in trying to apply CMG to a spinning satellite is the interaction of the spin of the satellite with that of the CMG rotor. In this paper we avoid this difficulty by considering the control law from the viewpoint of angular momentum. The torque exerted on the satellite under this control law is examined and is shown to be reasonable.
The control law for the desaturation of CMG gimbal angles using the earth's magnetic field is also discussed.
Assuming proper figures for the satellite and CMG dimensions, the procedure for designing system parameters is presented.
Digital simulation for the system is carried out and satisfactory results are obtained.
