Active control techniques of structural modes using piezoelectric actuators

New vibration control technology featuring integrated piezo actuators and sensors can reduce and actively control undesired structural flexing and vibrations. The objectives of this research are to design, implement, and test active vibration controls consisting of integrated piezo actuators and sensors on unmanned model aircraft. Finite element modeling was used to design and analyze the composite structure prior to actuator integration. Piezo actuators and strain gages were bonded to the structure and controlled through integrated hardware and software to damp structural oscillation. Combined with finite element analysis and computer simulation, the resulting capability will allow prediction of sensor and actuator location performance and impact on structural dynamics. This will ultimately aid in understanding the predicted stability and flight handling qualities of unmanned air vehicles in flight, thus increasing both their efficiency and safety.