Adaptive Control of a Nonlinear Prototypical Wing Section with Reduced Order Observer

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Dynamics and Control



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This paper treats the question of control of an aeroelastic system with unknown parameters usingoutput feedback. The equations of motion of the chosen aeroelastic system describe the plunge and pitch motionof a wing. A single trailing edge flap is used for the purpose of control, and plunge displacement and pitchangle are measured for feedback. Using a canonical representation of the aeroelastic system, reduced order filtersare designed to obtain the unmeasured state variables. Then based on a backstepping design technique, adaptivecontrol laws for the trajectory control of the pitch angle and the plunge displacement are derived. In the closed-loopsystem, the state vector is shown to converge asymptotically to zero. Simulation results are presented which showthat regulation and trajectory following are accomplished in the closed-loop system in spite of large uncertaintiesin the structural and aerodynamic parameters of the model.


Adaptive control systems; Aeroelastic system; Aeroelasticity; Airplanes—Wings; Feedback control systems; Feedback linearization; Nonlinear systems; Stability of airplanes


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