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Adaptive Positive Position Feedback Control of Flexible Aircraft Structures Using Piezoelectric Actuators
AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
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Buffet Adaptively Managed Fin BAMF focused on vibrations due to the interaction of aerodynamic forces with aircraft structure. Past failures of F-16 ventral ns due to vibrations provided grounds for control research. The n used had piezoelectric patches as collocated sensorsactuators. A custom ampli er and transformer were restructured into a system that could safely and reliably run, and adaptive software was created to address issues of system plant changes. Generating a PSD from the n sensors, the highest peaks were assumed to represent the low damped vibration modes. A PPF controller for each mode was designed and control signals were sent to the n actuators. Limited data were collected in a wind tunnel behind a custom system that caused bu et by varying vortex strengthshedding frequencies from pods upstream of the n. While minimal testing was accomplished to optimize gains, the system showed signi cant PSD peak reductions for the rst three modes of the n up to -14.9, -15.3, and -16.4 dB, respectively. The system maintained stability and e ective control even when both sensor input and controller output were saturated.
APPROVED FOR PUBLIC RELEASE