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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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control of a nonlinear wing section using leading- and trailing-edge surfaces

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JOURNAL OF GUIDANCE control AND DYNAMICS 2004年第1期27卷 52-58页

作者： Platanitis, G Strganac, TW Texas A&M Univ Dept Aerosp Engn College Stn TX 77843 USA

The control of nonlinear aeroelastic response of a wing section with a continuous stiffening-type structural nonlinearity is examined through analytical and experimental studies. Motivated by the limited effectiveness of using a single, trailing-edge control surface for the suppression of limit-cycle oscillations of a typical wing section, improvements in the control of limit-cycle oscillations are investigated through the use of multiple control surfaces, namely, an additional leading-edge control surface. The control methodology consists of a feedback linearization approach that transforms the system equations of motion via Lie algebraic methods and a model reference adaptive control strategy that augments the closed-loop system to account for inexact cancellation of nonlinear terms due to modeling uncertainty. Specifically, uncertainty in the nonlinear pitch stiffness is examined. It is shown through simulations and experiments that globally stabilizing control may be achieved by using two control surfaces.

关键词： Flexible Wings control Surfaces Aerodynamic Moments Model Reference Adaptive control Feedback Linearization Angle of Attack Low Speed Wind Tunnel Nonlinear Aeroelastic Systems benchmark active control technology Structural Response

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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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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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Modular adaptive control of a nonlinear aeroelastic system

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JOURNAL OF GUIDANCE control AND DYNAMICS 2003年第3期26卷 443-451页

作者： Singh, SN Brenner, M NASA Dryden Flight Res Ctr Aerostruct Branch Edwards AFB CA 93523 USA Univ Nevada Dept Elect & Comp Engn Las Vegas NV 89154 USA

The paper treats the question of adaptive control of prototypical aeroelastic wing sections with structural nonlinearity. The chosen dynamic model describes the nonlinear plunge and pitch motion of a wing. The model has both the plunge and pitch structural nonlinearities, and a single control surface is used for the purpose of control. It is assumed that only the sign of the coefficient of the control input and the lower bound on its absolute value are known, and the remaining parameters of the model are completely unknown. Modular adaptive control systems based on estimation-based design are derived for the control of the pitch angle and the plunge displacement. Unlike the direct adaptive controllers available in the literature, an input-to-state stabilizing control law is used herein. This control law accomplishes input-to-state stability with respect to parameter estimation error treated as a disturbance input. The control system includes a passive identifier (an observer and an adaptation law) for the parameter estimation. In the closed-loop system asymptotic stabilization of the plunge and pitch motion is accomplished. Simulation results are presented to show that the modular adaptive control systems accomplish flutter suppression in spite of the large uncertainties in the system. Simulation results also show that the closed-loop system without parameter adaptation fails to suppress flutter, but the input-to-state-stabilizing controller is effective in keeping the pitch and plunge responses bounded.

关键词： Closed Loop System Nonlinear Aeroelastic Systems benchmark active control technology Structural Nonlinearities Input to State Stability Output Feedback Freestream Velocity Nonlinear Systems Chaotic Vibrations Transonic Wind Tunnel

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Employing soft computing techniques to study stability and control in aircraft design

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JOURNAL OF GUIDANCE control AND DYNAMICS 2003年第1期26卷 169-173页

作者： Ali, N Behdinan, K Ryerson Univ Dept Mech Aerosp & Ind Engn Sch Aerosp Engn Toronto ON M5B 2K3 Canada

The effects of longitudinal static stability and control, laterial-directional static stability and control, and longitudinal motion of open-loop dynamic stability, specifically longitudinal and lateral flying qualities, on the aircraft conceptual design process were examined using a genetic algorithm (GA). The consideration of stability and control on the aircraft conceptual design proved to have an impact, resulting in a lower weight and feasible designs in most test runs. Accordingly, the GA was capable of varying design parameters in ways that other design tools cannot.

关键词： Aircraft Design Computing Techniques Commercial Aircraft Stability Derivatives benchmark active control technology Aircraft Conceptual Design Angle of Attack active control Fuselages Static Stability control

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Generalized predictive control for active flutter suppression

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JOURNAL OF GUIDANCE control AND DYNAMICS 2001年第1期24卷 154-159页

作者： Haley, P Soloway, D NASA Langley Res Ctr Dynam & Control Branch Airborne Syst Competency Hampton VA 23681 USA NASA Ames Res Ctr Nero Engn & Smart Syst Computat Sci Div Moffett Field CA 94035 USA

Experimental results of a transonic wind-tunnel test that demonstrate the use of generalized predictive control for flutter suppression in a subsonic wind-tunnel vying model are presented. The generalized predictive control algorithm is based on the minimization of a suitable cost function over finite costing and control horizons. The cost function minimizes not only the sum of the mean square output of the plant predictions, but also the weighted square rate of change of the control input with its input constraints. An additional term was added to the cost function to compensate for dynamics of the wing model that cause it to be invariant to low input frequencies. This characteristic results in a control surface that drifts within the specified input constraints. The augmentation to the cost function that penalizes this low-frequency drift is derived and demonstrated. The initial validation of the controller uses a linear plant predictor model for the computation of the control inputs. Simulation results of the closed-loop system that were used to determine nominal ranges for the tuning parameters are presented. The generalized predictive controller based on the linear predictor model successfully suppressed the flutter for all testable Mach numbers and dynamic pressures in the transonic region in both simulation and wind-tunnel testing. The results confirm that the generalized predictive controller is robust to modeling errors.

关键词： Transonic Wind Tunnel Closed Loop control Dynamic Pressure Iterative Algorithm Mach Numbers benchmark active control technology Accelerometer Neural Networks NASA Langley Research Center control Surfaces

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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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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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