Stabilization of a Spacecraft with Control Moment Gyros
Takahiro Sasaki, Takashi Shimomura, Sayaka Kanata
This paper considers stabilization of a spacecraft with CMGs (Control Moment Gyros) via LPV (Linear Parameter-Varying) control theory, in which we obtain a GS (Gain-Scheduled) controller by using LMIs (Linear Matrix Inequalities). However, due to excess of the number of scheduling parameters, it is difficult to design a GS controller. In most cases, LMIs are infeasible. To reduce the number of scheduling parameters, in this study, we redefine the steering law of a spacecraft with CMGs. By using two types of steering laws, we attain stabilization of a spacecraft. In comparison of some designed results, we consider how to select the coefficient matrices of the performance output.