Active Vibration Suppression of Flexible Spacecraft During Attitude Maneuver With Actuator Dynamics

A novel active vibration suppression approach based on a flywheel actuator for flexible spacecraft during attitude maneuvering is proposed in this paper. The flywheel is regarded as the only actuator. The rotation of the flywheel, the motion of the rigid body, and the vibration of the modes are coupled in this paper. The system model is obtained using the Euler-Lagrange methodology and the Assumedmode Method, in which the dynamics of the flywheel is considered. The stability of the flywheel transfer function from input voltage to output torque is analyzed using the Lyapunov method. Effects on system caused by flywheel are analyzed. Based on component synthesis vibration suppression theory, a typical vibration suppress law during attitude maneuver is derived. The input voltage of the flywheel actuator is designed according to this law. The presented novel approach is easily applied and practical without changing the spacecraft's structure properties. The simulation results and experiments on an air bearing spacecraft simulator are presented to verify the efficacy of the proposed approach.