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Robust output regulation of uncertain chaotic systems with input magnitude and rate constraints

Velosa C. M. N., Bousson K.

Acta Mechanica et Automatica

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2015

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Vol. 9, no. 4

252--258

EN

The problem of output regulation deserves a special attention particularly when it comes to the regulation of nonlinear systems. It is well-known that the problem is not always solvable even for linear systems and the fact that some demanding applications require not only magnitude but also rate actuator constraints makes the problem even more challenging. In addition, real physical systems might have parameters whose values can be known only with a specified accuracy and these uncertainties must also be considered to ensure robustness and on the other hand because they can be crucial for the type of behaviour exhibited by the system as it happens with the celebrated chaotic systems. The present paper proposes a robust control method for output regulation of chaotic systems with parameter uncertainties and subjected to magnitude and rate actuator constraints. The method is an extension of a work recently addressed by the same authors and consists in decomposing the nonlinear system into a stabilizable linear part plus a nonlinear part and in finding a control law based on the small-gain principle. Numerical simulations are performed to validate the effectiveness and robustness of the method using an aeronautical application. The output regulation is successfully achieved without exceeding the input constraints and stability is assured when the parameters are within the specified intervals. Furthermore, the proposed method does not require much computational effort because all the control parameters are computed offline.

2

Variable structure flutter control of a prototypical wing section with unsteady aerodynamics

Chemplavil S. C., Singh S. N., Wells W. R.

Systems Science

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2004

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Vol. 30, no 2

109-118

EN

This paper presents a variable structure control system for the realization of an aeroelastic system with unsteady aerodynamics. The aeroelastic model describes the plunge and pitch motion of a wing. Based on the sliding mode design technique, a control law for the trajectory control of the pitch angle is derived. For the synthesis of the controller, only the plunge displacement, pitch angle, control surface deflection and their derivatives are measured, and the states associated with Theodorsen's function are treated as unknown signals. In the closed-loop system, the state vector asymptotically convergers to the origin.

3

Sterowanie układem aeroelastycznym wymuszanym okresowo

Miller M., Narkiewicz J.

Zeszyty Naukowe Politechniki Rzeszowskiej. Mechanika

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2001

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z. 56[186], t.1

87-94

PL

W referacie przedstawiono wykorzystanie algorytmów "uczących się" do sterowania układu aeroelastycznego wymuszanego okresowo. Obiektem sterowania był cienki, słabo wysklepiony profil z klapką na krawędzi spływu znajdujący się w nielepkim, nieściśliwym opływie dwuwymiarowym. Badania numeryczne miały na celu określenie skuteczności różnych algorytmów sterowania w dziedzinie czasu i stanowią wstęp do ich wykorzystania na stanowisku doświadczalnym.

EN

In the paper deterministic learning control algorithms were applied to simple aeroealstic system to investigate of the influence of various assumptions on their effectiveness. As a controlled system, a typical cross section model of rotor blade with trailing edge fIap is The fIap deflection angle is both a degree of freedom and a control variable. In this study the efficiency of learning controI algorithms is evaluated by numerical simulations. As a result three control algorithms were fulfilIed the requirements, the three others, although effective, were not efficient. The further investigation will concern the embedding into system an electromechanical model of sensing/actuating piezoelectric element for investigation the properties of complete aeroservoelastic system.