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.
Positive position feedback based vibration attenuation for a flexible aerospace structure using multiple piezoelectric actuators
Digital Avionics Systems Conference, 2003. DASC '03. The 22nd ; 2 ; 7.C.1-71-10 vol.2
2003-01-01
602393 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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