Global Robust Control of an Aeroelastic System Using Output Feedback

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The paper treats the question of global robust control of prototypical aeroelastic wing sections with structural nonlinearity using output feedback. The chosen dynamic model describes the nonlinear plunge and pitch motion of a wing. The model has pitch structural nonlinearity, and a single control surface is used for the purpose of control. It is assumed that the parameters of the model are unknown, but the bounds on uncertainties are given. For the purpose of design, the pitch angle is chosen as an output variable. Using Lyapunov stability theory, a control law for global robust output regulation is derived. For solving the regulation problem, a "chained" representation of the aeroelastic model by dynamic extension and coordinate transformation is derived, and then the backstepping technique is used to derive the controller. It is shown that in the closed-loop system, global asymptotic stabilization of the plunge and pitch motion is accomplished using only pitch angle feedback. Simulation results are presented to show that the control system accomplishes flutter suppression in spite of the uncertainties in the system. The derived control law is attractive from the viewpoint of implementation.


AIAA Guidance; Airplanes — Control systems; Airplanes—Wings; Control Conference and Exhibit; Navigation; Robust control; Stability of airplanes


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