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This paper discusses the common issues in vibration attenuation for large aerospace structures using PZT actuators. In addition, a case study is presented to illustrate the vibration attenuation for a rocket fairing system, where the traditional PPF controller is modified by employing multiple actuators instead of a single one for any particular vibration mode. Simulation results demonstrate the effectiveness of this improved PPF control design approach. Thus a more robust control system is obtained due to the actuator redundancy in the presence of actuator failures. Fault-tolerant control systems are being designed for aerospace applications.