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Robust multivariable flutter suppression for benchmark active control technology wind-tunnel model

JOURNAL OF GUIDANCE control AND DYNAMICS 2001年第1期24卷 147-153页

作者： Waszak, MR NASA Langley Res Ctr Dynam & Control Branch Hampton VA 23681 USA

The benchmark active controls technology project is part of NASA Langley Research Center's benchmark Models Program for studying transonic aeroelastic phenomena. In January 1996, the benchmark active controls technology wind-tunnel model was used to successfully demonstrate the application of robust multivariable control design methods (H-infinity, and mu -synthesis) to flutter suppression. This paper addresses the design and experimental evaluation of robust multivariable flutter suppression control laws with particular attention paid to the degree to which stability and performance robustness was achieved.

关键词： benchmark active control technology Wind Tunnel Models Accelerometer Robust Multivariable control Digital control control Derivatives Dynamic Pressure Mathematical Models Langley Transonic Dynamics Tunnel Aeroelastic Models

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Comparison of two Navier-Stokes methods with benchmark active control technology experiments

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第6期23卷 1094-1099页

作者： Bartels, RE Schuster, DM NASA Langley Res Ctr Aeroelast Branch Hampton VA 23681 USA

Two commonly used three-dimensional compressible Navier-Stokes codes are applied to select test cases from an experimental data set on a model known as the benchmark active control technology (BACT) wing. The BACT test provides data for the validation of aerodynamic, aeroelastic, and active aeroelastic control simulation codes. An overview will be presented of the two Navier-stokes aeroelastic codes currently being used In an analysis of that data. A collection or results obtained by the two methods will be compared with the BACT experimental data for a wing with a statically deflected spoiler and statically and dynamically deflected aileron. Both methods employ structured computational fluid dynamics flow solvers and continuous surface modeling for the computation of complex moving control surface geometry. Motivation for this work is the development of an integrated computational aeroelasticity and active! control simulation capability for the transonic flight regime and validation of that capability using the BACT wing data.

关键词： benchmark active control technology control Surfaces Aerodynamic Simulation Angle of Attack Aeroelastic control active control Reynolds Averaged Navier Stokes Johnson King Model Courant Friedrichs Lewy Langley Transonic Dynamics Tunnel

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Output Regulation with Actuator Saturation for the benchmark active control technology Model

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JOURNAL OF GUIDANCE control AND DYNAMICS 2010年第6期33卷 1951-1966页

作者： Applebaum, Ellen Adin, Zvi J. Ben-Asher, Joseph Z. Technion Israel Inst Technol Fac Aerosp Engn IL-32000 Haifa Israel

A study was conducted to address the problem of output regulation of the continuous-time linear benchmark active control technology (BACT) model with control saturation and exogenous input additive disturbance. The BACT wind-tunnel aeroservoelastic (ASE) model was developed by NASA Langley Research Center that exhibited classical flutter instability at transonic speeds, with system dynamics that varied with the dynamic pressure. The study proposed an alternative strategy and methodology to that of sliding mode control for achieving output regulation of a linear system with actuator saturation and exogenous disturbances. The proposed method was also based upon the construction of invariant sets for maximizing domains of attraction and achieving continuous control action in small invariant neighborhoods of the equilibrium point.

关键词： benchmark active control technology Actuators Gain Scheduled control Feedback control Dynamic Pressure Numerical Simulation Algebraic Riccati Equation Resonance Frequencies Dynamic Response Hinge Moment

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Passivity-based robust control with application to benchmark active controls technology wing

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第5期23卷 938-947页

作者： Kelkar, AG Joshi, SM Kansas State Univ Manhattan KS 66506 USA NASA Langley Res Ctr Hampton VA 23666 USA

A passivity-based robust control design methodology is presented. A brief review of the stability results is given for passive linear and nonlinear systems followed by four different passification methods for rendering nonpassive systems passive. The robust control methodology via robust passification is demonstrated by application to the benchmark active controls technology subsonic wing. The controller design is shown to provide robust stability and satisfactory performance.

关键词： Closed Loop System benchmark active control technology Mathematical Models Output Feedback Vibration Suppression Dynamic Pressure Accelerometer Aeroelastic System control Surfaces Frequency Domain

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Comparing linear parameter-varying gain-scheduled control techniques for active flutter suppression

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第5期23卷 948-955页

作者： Barker, JM Balas, GJ Univ Minnesota Dept Aerosp Engn & Mech Minneapolis MN 55455 USA

Two linear parameter-varying gain-scheduled controllers for active flutter suppression of the NASA Langley Research Center's benchmark active control technology (BACT) wing section are presented and compared to a previously presented gain-scheduled controller. The BACT wing section changes significantly as a function of Mach and dynamic pressure, The two linear parameter-varying (LPV) gain-scheduled controllers incorporate these changes as well as bounds on the rate of change of Mach and dynamic pressure The inclusion of rate bounds in the design process allows for improved performance over a larger range of operating conditions than previously achieved by a linear fractional transformation gain-scheduled controller. The LPV controllers differ in that one primarily reduces coupling between the trailing-edge flap and the pitch and plunge modes, whereas the second optimizes wind gust attenuation. Closed-loop stability and improved performance are demonstrated via time simulations in which both Math and dynamic pressure are allowed to vary in the presence of a Dryden wind-gust disturbance.

关键词： Closed Loop Transfer Function Aircraft Wings benchmark active control technology Dynamic Pressure NASA Langley Research Center Aerodynamic Instability Unsteady Aerodynamics Linear Interpolation Small Gain Theorem control Algorithm

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

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JOURNAL OF GUIDANCE control AND DYNAMICS 2010年第5期33卷 1451-1460页

作者： Lee, Keum W. Singh, Sahjendra N. Univ Nevada Dept Elect & Comp Engn Las Vegas NV 89154 USA Kwandong Univ Gangwon 210701 South Korea

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.

关键词： Nonlinear Aeroelastic Systems Closed Loop control benchmark active control technology Trailing Edges control Surfaces Freestream Velocity Feedback control System Damping Coefficient Low Speed Wind Tunnel Mathematical Models

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Comparison of μ- and H₂-synthesis controllers on an experimental typical section

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JOURNAL OF GUIDANCE control AND DYNAMICS 1999年第2期22卷 278-285页

作者： Vipperman, JS Barker, JM Clark, RL Balas, GJ Univ Maine Dept Mech Engn Orono ME 04469 USA Univ Minnesota Dept Aerosp Engn & Mech Minneapolis MN 55455 USA Duke Univ Dept Mech Engn & Mat Sci Durham NC 27708 USA

An experimental comparison of H-2- and mu-synthesized flutter suppression control systems was performed. A simple parametric uncertainty can be used to track changes in system dynamics as a function of dynamic pressure. The control system was implemented experimentally on a NACA 0012 test model of a typical section mounted in a low-speed wind tunnel. The pitching angle, flap angle, and plunge deflection of the airfoil were measured with sensors and fed back through the control compensator to generate a single control signal commanding the trailing-edge flap of the airfoil. The model of the aeroelastic system, including the dynamics of the sensors and actuators in the bandwidth of interest, was obtained using system identification techniques. For comparison purposes, an H-2 control system with standard linear quadratic Gaussian weightings also was designed and implemented. When compared to the H-2 control system, the mu-synthesis controller provided better disturbance rejection in the bandwidth of the unsteady aeroelastic dynamics. In addition, the mu controller required less control energy than the H-2 control system. The final advantage of mu-synthesis is the ability to design an aggressive mu control system that is stabilizing across the range of operating dynamic pressures.

关键词： benchmark active control technology Linear Actuator Low Speed Wind Tunnel Sensor Systems Thin Airfoil Aeroelastic control Stagnation Pressure Closed Loop Transfer Function Linear Quadratic Gaussian Frequency Response Functions

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Transonic flutter suppression control law design and wind-tunnel test results

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JOURNAL OF GUIDANCE control AND DYNAMICS 2000年第5期23卷 930-937页

作者： Mukhopadhyay, V NASA Langley Res Ctr Hampton VA 23681 USA

Flutter suppression control law design and wind-tunnel test results in transonic flow for a NACA 0012 wing model, under the benchmark active control technology program at NASA Langley Research Center, will be presented. Two control law design processes using classical and minimax techniques are described. Design considerations fur improving the multivariable system robustness are outlined. The classical control law was digitally implemented and tested in the NASA Langley Transonic Dynamics Tunnel. In wind-tunnel tests in air and heavy gas medium, the closed-loop Butter dynamic pressure was increased by over 50% up to the wind-tunnel upper limit. The active Butter suppression system also provided significant robustness, relative to gain and phase perturbations, even in the presence of transonic shocks and Row separation.

关键词： Wind Tunnel Models Linear Quadratic Regulator Dynamic Pressure Aerodynamic Loads benchmark active control technology Accelerometer Feedback control Linear Quadratic Gaussian Langley Transonic Dynamics Tunnel Numerical Simulation

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Historical perspective on analysis and control of aeroelastic responses

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JOURNAL OF GUIDANCE control AND DYNAMICS 2003年第5期26卷 673-684页

作者： Mukhopadhyay, V NASA Langley Res Ctr Hampton VA 23681 USA

Brief glimpses of history of aeroelastic analysis and control of aeroelastic responses and their mathematical foundation are presented. This is a continuing story, and many excellent research works in this multidisciplinary field remain to be reviewed in the future. In addition, the history and recent advances in aeroelastic analysis and control of rotorcraft, turbines, jet engines, launch vehicles, missiles, spacecraft, large space structures, and non-aerospace structures were omitted. However, most unclassified publications are available through the Web-based *** search engine. (Author)

关键词： Nonlinear Aeroelastic Systems Linear Quadratic Gaussian Nyquist Stability Criterion Aerodynamic Flutter Langley Transonic Dynamics Tunnel Theory of Elasticity control Surfaces active Aeroelastic Wing benchmark active control technology Feedback control System

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Experimental Nonlinear control for Flutter Suppression in a Nonlinear Aeroelastic System

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第8期40卷 1925-1938页

作者： Jiffri, Shakir Fichera, Sebastiano Mottershead, John E. Da Ronch, Andrea Univ Liverpool Dept Mech Mat & Aerosp Engn Sch Engn Brownlow Hill Liverpool L69 3GH Merseyside England Univ Liverpool Appl Mech Brownlow Hill Liverpool L69 3GH Merseyside England Univ Liverpool Inst Risk & Uncertainty Brownlow Hill Liverpool L69 3GH Merseyside England Univ Southampton Fac Engn & Environm Univ Rd Southampton SO17 1BJ Hants England

Experimental implementation of input-output feedback linearization in controlling the dynamics of a nonlinear pitch-plunge aeroelastic system is presented. The control objective is to linearize the system dynamics and assign the poles of the pitch mode of the resulting linear system. The implementation 1)addresses experimentally the general case where feedback linearization-based control is applied using as the output a degree of freedom other than that where the physical nonlinearity is located, using a single trailing-edge control surface, to stabilize the entire system;2)includes the unsteady effects of the airfoil's aerodynamic behavior;3)includes the embedding of a tuned numerical model of the aeroelastic system into the control scheme in real time;and 4)uses pole placement as the linear control objective, providing the user with flexibility in determining the nature of the controlled response. When implemented experimentally, the controller is capable of not only delaying the onset of limit-cycle oscillation but also successfully eliminating a previously established limit-cycle oscillation. The assignment of higher levels of damping results in notable reductions in limit-cycle oscillation decay times in the closed-loop response, indicating good controllability of the aeroelastic system and effectiveness of the pole-placement objective. The closed-loop response is further improved by incorporating adaptation so that assumed system parameters are updated with time. The use of an optimum adaptation parameter results in reduced response decay times.

关键词： Nonlinear Aeroelastic Systems Nonlinear control Numerical Integration Linear Time Invariant System Feedback Linearization Flap Deflection Aerodynamic Loads Airspeed benchmark active control technology Damping Coefficient

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