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Nonlinear Tracking Control of an Elastically Supported Flapping Thin Airfoil

Space Research Institute, King Abdulaziz City for Science and Technology, PO Box 6086, Riyadh 11442, Saudi Arabia

Khalid A. Alsaif

Department of Mechanical Engineering, King Saud University, PO Box 800, Riyadh 111421, Saudi Arabia

A control law for a self-excited system using state feedback linearization and coordinate transformation is developed. The system consists of an elastically supported hinged thin airfoil, which is subjected to a uniform steady airflow A nonlinear aerodynamic model is used to account for the fluid-solid interaction mnechanism. A chaotic behavior of the open-loop system at certain control parameters is observed experimentally and checked numerically. It is shown that the controllability of the system is guaranteed using a torque source at the leading edge of the airfoil. Furthennore, good tracl4rg of time-varying desired angle of attack is achieved using the developed controller. Finally, a SIMULINK%N model is developed to facilitate time-domain analysis, control design and future real-time control implementations.

Key Words: Self-excited • fluid-solid interaction • feedback linearization • chaos

Journal of Vibration and Control, Vol. 10, No. 6, 779-794 (2004)
DOI: 10.1177/1077546304039430


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