Active Vibration Suppression in Flexible Spacecraft Attitude Tracking

Abstract

The active suppression of vibrations of spacecraft  exible appendages during attitude tracking or large-angle maneuvers is discussed.On thebasisof amodelobtainedusingtheLagrangianapproachand theunitaryquaternion parameterization, piezoelectric actuators are used to damp the vibration of  exible booms induced during the maneuvers. The results of simulation reveal the interest and the practical feasibility of such a control scheme. The control law requires only the measure of the attitude and the angular velocity. The absence of  exible displacement and velocity sensors is compensated for by the presence of appropriate dynamics in the controller.