ACTIVE VIBRATION SUPPRESSION IN FLEXIBLE SPACECRAFT DURING ATTITUDE MANEUVER

A novel method using the optical measurement to measure the dynamic behaviors of the spacecraft flexible appendages such as solar panels and solar arrays which are not allowed to be settled with piezoelectric actuators and sensors is proposed. Active vibrations suppression for these spacecraft flexible appendages during spacecraft large-angle maneuvers is discussed. The vibration information of the flexible appendages is obtained by the measured displacement; a finite convergence observer is designed to estimate the vibration velocity. The active vibration suppression algorithm is designed, based on the back-stepping control and Lyapunov method. The stabilization of the controller and the observer is proved. The actuator that used to the complete the active vibration control is collocating at the spacecraft body.