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

• Autorzy: Chemplavil S. C. , Singh S. N. , Wells W. R.
• Języki publikacji: EN

Abstrakty

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.

Słowa kluczowe

EN

aerodynamics; variable structure flutter control; aeroelastic system; displacement control; motion control; closed loop system; Theodorsen function

• Wydawca: Oficyna Wydawnicza Politechniki Wrocławskiej
• Czasopismo: Systems Science
• Rocznik: 2004
• Tom: Vol. 30, no 2
• Strony: 109--118
• Opis fizyczny: Bibliogr. 11 poz., wykr.

Twórcy

autor

Chemplavil S. C.

• HRH College of Engineering, University of Nevada, Las Vegas, NV 89154-4026

autor

Singh S. N.

• HRH College of Engineering, University of Nevada, Las Vegas, NV 89154-4026

autor

Wells W. R.

• HRH College of Engineering, University of Nevada, Las Vegas, NV 89154-4026

Bibliografia

• [1] Bhoir N., Singh S. N., Control of Unsteady Aeroelastic System via State-Dependent Riccati Equation Method, J. Guidance, Control and Dynamics, 27, 2004.
• [2] Bhoir N., Singh S. N., Output Feedback Nonlinear Control of an Aeroelastic System with Unsteady Aerodynamics, Aerospace Science and Technology, 8, 2004, 195-205.
• [3] Block J., Strganac T. M., Applied Active Control for a Nonlinear Aeroelastic Structure, J. Guidance, Control and Dynamics, 21, 1998, 838-845.
• [4] Dowell E. H. (ed.), A Modern Course in Aeroelasticity, Chap. 1, Kluwer Academic Publishers, MA, 1995.
• [5] Fung Y. C., An Introduction to the Theory of Aeroelasticity, Willey, New York 1955.
• [6] Ko J., Kurdila A. J., Strganac T. W., Nonlinear Control of a Prototypical Wing Section with Torsional Nonlinearity, J. Guidance, Control and Dynamics, 20, 1997, 1181-1189.
• [7] Ko J., Strganac T. W., Kurdila A. J., Adaptive Feedback Linearization for the Control of a Typical Wing Section with Structural Nonlinearity, Nonlinear Dynamics, 18, 1999, 289-301.
• [8] Mukhopadhyay V., Transonic Flutter Suppression Control Law Design and Wind-Tunnel Test Results, J. Guidance, Control and Dynamics, 23, 2000, 930-937.[9] Singh S. N., Wang L, Output Feedback Form and Adaptive Stabilization of a Nonlinear Aeroelas-tic System, J. Guidance, Control and Dynamics, 25, 2002, 725-732.
• [10] Slotine J. J., Li W., Applied Nonlinear Control, Prentice-Hall, Englewood Cliffs, N. J., 1991.
• [11] Theodorsen T., General theory of aerodynamic instability and mechanism of flutter, NACA report 496, National Advisory Committee for Aeronautics, Hampton, VA, 1935.