抄録
This paper is on singularity avoidance on of the satellite using Control Moment Gyros as attitude control device. The Control Moment Gyros has very high ability for the space structures to control its attitude, but there remains the problem of singularity in the system. The singularity avoidance control law using state feedback is introduced and examined in this paper. The state feedback control law uses idea from optimal control theory and traditional laws to control the system. The control law shows ability to avoid the singularity with online feedback and keeps the designated constraint of the control.
