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Nonlinear control design of an airfoil with active flutter suppression in the presence of disturbance

IET CONTROL THEORY AND APPLICATIONS 2007年第6期1卷 1638-1649页

作者： Afkhami, S. Alighanbari, H. Ryerson Univ Dept Aerosp Engn Toronto ON M5B 2K3 Canada

The nonlinear flutter suppression of a typical wing section is investigated. A structural nonlinearity is considered in the pitch direction. Integral-input-to-state stability (iISS) concept is utilised for the construction of a feedback controller. One of the advantages of this design is its simplicity and straightforwardness. A backstepping method is used to compare the results for the typical section, which is a multi-input system. The iISS controller has an outstanding performance in comparison to the backstepping method, especially with regards to the disturbance attenuation problem. A Lyapunov-based controller was also introduced for the system.

关键词： backstepping structural nonlinearity disturbance attenuation problem iISS concept nonlinear flutter suppression pitch direction Lyapunov-based controller airfoil iISS controller nonlinear systems integral-input-to-state stability feedback controller aerospace components nonlinear control design Lyapunov methods automotive components control system synthesis multiinput system active flutter suppression wing section

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active flutter suppression control using piezo-ceramic actuators

Active flutter suppression control using piezo-ceramic actua...

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6th World Congress on Intelligent Control and Automation

作者： Li, Lanjun Yu, Shouyi Kawai, Naoki Matsushita, Hiroshi Cent S Univ Coll Informat Sci & Engn Changsha 410083 Hunan Peoples R China Nanhua Univ Sch Elect Engn Hengyang 421001 Taiwan Michelin Res Asia Ohta Gumma Japan Univ Fukui Dept Engn Mech Fukui 910 Japan

ISBN: (纸本)1424403316

Single piezo ceramic element (PZT) was introduced to a wind tunnel wing model for active flutter suppression. The wing modeling process using FEM analysis for structures and Doublet Point Method for aerodynamics was described. As an extension to the previous experimental research with a proportional control, the LQG flutter suppression control law design based on the modeling equations was presented. The LQG control law was verified in wind tunnel tests in air and turned out to be able to successfully control the flutter.

关键词： active flutter suppression LQG control law PZT wind tunnel tests

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A comparison of full non-linear and reduced order aerodynamic models in control law design using a two-dimensional aerofoil model

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INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN ENGINEERING 2005年第12期64卷 1628-1648页

作者： Allen, CB Taylor, NV Fenwick, CL Gaitonde, AL Jones, DP Univ Bristol Dept Aerosp Engn Bristol BS8 1TR Avon England

The prediction of the flutter boundary of an aircraft is a necessary but time consuming process, particularly as for the most realistic results a time accurate simulation of the interaction between the non-linear aerodynamic and structural forces is required. Extension of the flight envelope by the design of active control laws to suppress flutter further increases the demands on computational time, to presently unrealistic levels. Use of a reduced order model (ROM) derived from, and in place of, the full non-linear aerodynamics greatly reduces the time required for calculation of aerodynamic forces. However, this is necessarily accompanied by some loss in accuracy, and hence the method must be verified by comparison with results obtained by the full aerodynamic model before it may be used with confidence. Such a comparison is presented here, using a two-dimensional aerofoil and control surface combination as a test case. active control of the deflectable surface is used to attempt to increase the flutter speed across the complete Mach range, feedback control being achieved by gains acting on heave and pitch proportional and differential signals, interpreted as a hinge moment demand. Full non-linear and reduced order aerodynamic models are then used to obtain optimum control law gain for flutter suppression. The results demonstrate that the ROM accurately predicts the open loop flutter boundary, gives a good approximation to the increase in flutter speed that may be produced by gain optimization, and produces a similar response given the identical gain values in each system for a significantly reduced cost. Copyright (c) 2005 John Wiley & Sons, Ltd.

关键词： reduced order modelling active flutter suppression aeroservoelastic modelling unsteady CFD unsteady aerodynamics transonic flows

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Two-dimensional transonic aeroservoelastic computations in the time domain

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INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN ENGINEERING 2001年第12期52卷 1355-1377页

作者： Djayapertapa, L Allen, CB Fiddes, SP Univ Bristol Dept Aerosp Engn Bristol BS8 1TR Avon England

A computational method to perform transonic aeroelastic and aeroservoelastic calculations in the time domain is presented, and used to predict stability (flutter) boundaries of 2-D wing sections. The aerodynamic model is a cell-centred finite-volume unsteady Euler solver, which uses an efficient implicit time-stepping scheme and structured moving grids. The aerodynamic equations are coupled with the structural equations of motion, which are derived from a typical wing section model. A control law is implemented within the aeroelastic solver to investigate active means of flutter suppression via control surface motion. Comparisons of open- and closed-loop calculations show that the control law can successfully suppress the flutter and results in an increase of up to 19 per cent in the allowable speed index. The effect of structural non-linearity, in the form of hinge axis backlash is also investigated. The effect is found to be strongly destabilizing, but the control law is shown to still alleviate the destabilizing effect. Copyright (C) 2001 John Wiley & Sons, Ltd.

关键词： aeroelasticity aeroservoelasticity transonic flow active flutter suppression backlash free-play

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A design of active flutter suppression control systems using mu synthesis and controller reduction

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PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 1997年第G3期211卷 183-192页

作者： Fujimori, A Nikiforuk, PN UNIV SASKATCHEWAN DEPT MECH ENGNSASKATOONSK S7N 0W0CANADA

This paper presents a control synthesis of a two-dimensional aerofoil active flutter suppression (2D-AFS) using mu synthesis and the extended coprime factorization (weighted) (ECFW) controller reduction method in numerical simulation. A multiplicative uncertainty representation is chosen as a structured uncertainty model of the 2D-AFS system because H-infinity norm of the uncertainty due to changes in the flight velocity is calculated small by using the multiplicative uncertainty representation. Controllers are designed by mu synthesis in the frame of the robust stability and the robust control performance problems. Furthermore, using the ECFW controller reduction method, a seventh-order controller whose performances are almost the same as those of the original controller is obtained.

关键词： active flutter suppression mu synthesis controller reduction uncertainty

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APPLICATION OF H-INFINITY CONTROL AND LQG WITH FREQUENCY-DEPENDENT WEIGHT SYNTHESES TO A MULTIVARIABLE active flutter suppression SYSTEM

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PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 1995年第3期209卷 233-243页

作者： FUJIMORI, A NIKIFORUK, PN UNIV SASKATCHEWAN DEPT MECH ENGNSASKATOONSK S7N 0W0CANADA

This paper describes the effectiveness of three robust control synthesis techniques applied to a multivariable active flutter suppression system using numerical simulations. These techniques are the mixed-sensitivity reduction in H-infinity (H-infinity-mix), the normalized left coprime factorization robust stabilization in H-infinity (H-infinity-normalized), and LQG with frequency-dependent weights (FWLQG), which are proposed in this paper. Although the plant is an unstable multi-input and multi-output system with large parameter variation, the FWLQG technique is superior to both H(i)nfinity synthesis techniques from the viewpoint of the increment of the flutter velocity, the time response and the solubility of control problems.

关键词： ROBUST CONTROL FREQUENCY-DEPENDENT WEIGHT H-INFINITY CONTROL active flutter suppression

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Multivariable active flutter suppression Tems using H ∞ Control and LQG with Frequency Dependent Weight Syntheses

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IFAC Proceedings Volumes 1994年第13期27卷 243-248页

作者： A. Fujimori P.N. Nikiforuk M.M. Gupta University of Saskatchewan Department of Mechanical Engineering Saskatoon Saskatchewan S7N 0W0 Canada

This paper describes the effectiveness of three robust control synthesis techniques applied to a multivariable active flutter suppression system using numerical simulations. These techniques are the mixed-sensitivity reduction in H ∞ ( H ∞ -mix), the normalized left coprirne factorization robust stabilization in H ∞ ( H ∞ -normalized), and LQG with frequency-dependent weights (FWLQG), which is proposed in this paper. Although the plant is an unstable multi-input and multi-output system with large parameter variation, the FWLQG technique is superior to both H ∞ synthesis techniques from viewpoints of the increment of the flutter velocity, the time response and the solubility of control problems.

关键词： active flutter suppression robust control H ∞ control LQG frequency-dependent weight

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A Synthesis of Reduced-order H ∞ Controllers for active flutter suppression Systems

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IFAC Proceedings Volumes 1993年第2期26卷 805-808页

作者： A. Fujimori H. Ohta Department of Energy and Mechanical Engineering Shizuoka University 3.5.1 Johoku Hamamatsu 432 Japan Department of Aeronautical Engineering Nagoya University Furo-cho Chikusa-ku Nagoya 464 Japan

The objective of this paper is to present a synthesis method of reduced-order active flutter suppression (AFS) systems. AFS systems of a two-dimensional airfoil (2D-AFS) are first designed by mixed sensitivity reduction problem in H ∞ control theory (H ∞ -mix). Secondary to reduce the order of the H ∞ controller, the coprime factorization (weighted) controller reduction method (CFW) is then extended lo apply the controllers that are designed by using other than the LQG control theory. It is shown in the numerical example that H ∞ -mix controllers give more increase of the flutter velocity than the LQG and H 2 -mix ones, and the extended CFW method is useful to reduce the order of Hie H ∞ -mix controllers

关键词： active flutter suppression H ∞ control controller reduction stability robustness coprime factorization

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A SYNTHESIS OF REDUCED-ORDER COMPENSATORS FOR active flutter suppression SYSTEMS BASED ON THE OPTIMAL PROJECTION METHOD

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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 1991年第103期34卷 12-26页

作者： FUJIMORI, A Shizuoka Univ Hamamatsu Japan

A synthesis of reduced-order compensators for the active flutter suppression of a two-dimensional airfoil is presented using the optimal projection method. The condition which minimizes a quadratic performance cost is taken into consideration for a compensator whose order is less than that of the controlled plant. A reduced-order compensator is then constructed satisfying this condition. In this paper, two modified Riccati and two modified Lyapunov equations are derived for the conditions stated. Since these equations are coupled, iterative calculation methods are employed, therefore, to solve them and an algorithm which overcomes some of the defects of the conventional method is proposed. Numerical simulations, carried out using a thirteenth-order active flutter suppression system for a two-dimensional airfoil, show that the optimal projection method can yield the second-order compensators in all cases. Compensators whose order is six or more display approximately the same control performance as that using the optimal observer, that is, a Kalman filter.

关键词： active flutter suppression OPTIMAL PROJECTION METHOD REDUCED-ORDER COMPENSATOR

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