Distributed passive and active vibration control for spacecraft with large flexible appendage

To realize rapid attitude maneuvers and stabilization for a spacecraft with flexible appendages, a distributed passive and active vibration control strategy is presented. A dynamical model of the spacecraft with control moment gyroscopes (CMGs), a passive vibration isolation system, and flexible appendages is constructed using the Newton-Euler method and the Kane equations. This integrated dynamical model is used to determine the effect of the spacecraft's angular velocities on the performance of the passive vibration isolation system for an attitude maneuver mission. To reduce the vibrations caused by the flexible appendages, multiple mode input shapers using the modal information are designed and used as a type of feed forward controller in the attitude control system. The attitude maneuver control simulation results validate the use of the developed vibration control method for the effective attenuation of vibrations of flexible appendages and improving attitude stability.