衛星姿勢制御用コントロール?モーメント?ジャイロの初期ジンバル角最適化による特異点回避

摘要

Control Moment Gyroscopes (CMG) has been expected to apply to the control of a satellite in recent years because themission of a satellite becomes more complicated and requires more mobility. On the other hand, it is pointed out thatCMG itself has singularity conditions and major source of disturbance for the attitude control systems. Considering thisbackground, this paper proposes a new but simple CMG steering law using preferred initial gimbal angles and nullmotion for high accurate attitude control system on an agile satellite.