Multi-Input Noncertainty-Equivalent Adaptive Control of an Aeroelastic System

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This paper treats the question of noncertainty-equivalent adaptive control of a nonlinear aeroelastic system with leading- and trailing-edge control surfaces. The model describes the plunge and pitch dynamics of a prototypical wing section. It is assumed that all the system parameters, except the signs of principal minors of the input matrix, are unknown. The objective is to asymptotically regulate the pitch angle and plunge displacement to the origin using two control surfaces. The derivation of the control system is based on the attractive manifold design procedure, which retains interesting features of the immersion and invariance approach, and on the matrix decomposition. The control system has a modular structure consisting of a control module and an identifier and is well defined for arbitrary perturbations in the parameters. Based on the Lyapunov analysis, it is shown that in the closed-loop system, the pitch angle and plunge displacement converge to zero, and the trajectories are ultimately confined to a manifold on which the controller recovers the performance of a deterministic control system. Simulation results are presented that show suppression of oscillatory responses for large parameter uncertainties.


Adaptive control systems; Airplanes—Wings; Pitching (Aerodynamics); Stability of airplanes


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