Agile Attitude Control and Vibration Suppression of Flexible Spacecraft Using Control Moment Gyros

Because control moment gyroscopes (CMGs) are capable of generating a much larger control torque for attitude maneuvers than can reaction wheels (RWs), vibration becomes a significant issue for flexible structures such as solar paddles. It is important to address this issue for the agile attitude maneuver control of flexible spacecraft using CMGs. This paper presents an integrated feedback/feedforward control system for reducing the vibration of flexible structures, as well as for completing a rapid, large-angle attitude maneuver of the spacecraft. The proposed Lyapunov control integrated with the Nil-Mode-Exciting profiler and an extended Input Shaping technique effectively improved the transient vibration of the modal response.