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DESIGN OF A flutter suppression system FOR AN EXPERIMENTAL DRONE AIRCRAFT

JOURNAL OF AIRCRAFT 1985年第5期22卷 380-386页

作者： NEWSOM, JR POTOTZKY, AS ABEL, I NASA Langley Research Center Hampton Virginia Kentron International Inc. Hampton Virginia

This paper describes the design of a flutter suppression system for a remotely-piloted research vehicle. The modeling of the aeroelastic system, the methodology used to synthesize the control law, the analytical results used to evaluate the control law performance, and ground testing of the flutter suppression system onboard the aircraft are discussed. The major emphasis is on the use of optimal control techniques employed during the synthesis of the control law. © 1985 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： flutter suppression system Aeroplane Drone Linear Quadratic Gaussian Aeroelastic system Aerodynamic Force Coefficients Full State Feedback Gain Scheduled Control Finite Element Modeling Flight Testing

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STRUCTURE CONTROL DESIGN SYNTHESIS OF ACTIVE flutter suppression system BY GOAL PROGRAMMING

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1991年第6期14卷 1260-1266页

作者： SUZUKI, S MATSUDA, S University of Tokyo Bunkyo-ku Tokyo 113 Japan

The simultaneous design of the structure and control for a typical wing section with a trailing control surface is considered. Since the original structure usually has inadequate dynamic characteristics for active control, design parameters must be optimally modified. Full-state feedback control gains are designed using the linear quadratic Gaussian regulator theory at the design airspeed;this is the only control design parameter. A typical wing section with a trailing control surface is examined as a design example, and then both structure and control design parameters are optimized in accordance with the following prioritized design requirements: 1) the flutter speed of an initial open-loop system is maintained, 2) the stability characteristics of a closed-loop system are obtained over a wide range of flight speed, 3) the control surface deflection angle is restrained, and 4) the degree of structural design changes is minimized. The sequential goal programming method is successfully applied to optimize these multidisciplinary design requirements.

关键词： flutter suppression system Closed Loop system Full State Feedback Structural Design Airspeed Linear Quadratic Gaussian Sensitivity Analysis Aerodynamic Loads Numerical Optimization White Noise

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MULTIRATE flutter suppression system-DESIGN FOR A MODEL WING

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1994年第6期17卷 1267-1274页

作者： MASON, GS BERG, MC UNIV WASHINGTON SEATTLEWA 98195

A new methodology for multirate control system design is described. It accommodates a general multiple-input, multiple-output control law structure that allows the sampling rates for the plant sensor output signals, the update rates fur the processor states, and the update rates for the plant control input signals to be independently specified. It includes a capability to design for multiple plant conditions so as to achieve robustness to plant parameter variations. Its analysis components include a method for determining conventional gain and phase margins, a method for determining a bound on the smallest destabilizing uncertainty, and a method for determining the maximum root-mean-square (rms) gain of a multirate system. The methodology is demonstrated by application to the design of a multirate flutter suppression system for a model wing.

关键词： flutter suppression system Benchmark Active Control Technology Linear Time Invariant system Sensors Robotics Aeroplane Flight Control Boeing Accelerometer Dynamic Pressure

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DESIGN OF AN ACTIVE flutter suppression system

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1986年第1期9卷 64-71页

作者： LIEBST, BS GARRARD, WL ADAMS, WM NASA LANGLEY RES CTRDIV FLIGHT DYNAM & CONTROLHAMPTONVA 23665

An active control law is synthesized for the suppression of wing flutter for a mathematical model of a flight test vehicle. Eigenvalue placement is used to synthesize a full state controller that satisfies performance specifications on control surface activity and that exhibits excellent gain and phase margins. A simple frequency response matching technique is used to design a realizable compensator which approximates the feedback properties of the full state controller. The performance of the control system using this compensator is evaluated at various flight conditions and found to be satisfactory. In addition, eigenvector shaping is used to enhance the gust load alleviation capabilities of the flutter control system.

关键词： flutter suppression system Loop Transfer Function Aerodynamic Coefficients Control systems Flight Test Vehicle Mathematical Models Frequency Response Control Surfaces Accelerometer Dynamic Pressure

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DESIGN AND MULTIFUNCTION TESTS OF A FREQUENCY DOMAIN-BASED ACTIVE flutter suppression system

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JOURNAL OF AIRCRAFT 1995年第1期32卷 52-60页

作者： ADAMS, WM CHRISTHILF, DM NASA Langley Research Center Hampton Virginia 23681 Lockheed Engineering and Sciences Company Inc. Hampton Virginia 23666

This article describes the process of analysis, design, digital implementation, and subsonic testing of an active controls nutter suppression system for a full-span, free-to-roll, wind-tunnel model of an advanced fighter concept. A frequency domain representation of the plant was employed, and a robust multiinput/multioutput controller was generated by using optimization techniques to maximize singular value robustness criteria and insensitivity to uncertainty in the nutter frequency. During testing in a fixed-in-roll configuration, simultaneous suppression of both symmetric and antisymmetric nutter was successfully demonstrated. For a free-to-roll configuration, symmetric nutter was suppressed to the limit of the tunnel test envelope. During aggressive rolling maneuvers above the open-loop nutter boundary, simultaneous nutter suppression and maneuver load control were demonstrated. Finally, the nutter suppression controller was reoptimized during the test using combined experimental and analytical frequency domain data, resulting in improved stability robustness. The reoptimization, accomplished overnight, shows the potential, with a much faster computer, to apply the design procedure to a tuning-type adaptive active nutter suppression controller.

关键词： flutter suppression system Power Spectral Density State Space Representation Wind Tunnel Models Maneuver Load Control Dynamic Pressure Accelerometer Control Surfaces Aerodynamic Force Langley Transonic Dynamics Tunnel

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ROBUSTNESS ANALYSIS OF A MULTIRATE flutter suppression system

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1993年第5期16卷 922-926页

作者： MASON, GS BERG, MC University of Washington Seattle Washington 98195

A unified approach for analyzing the robustness and performance of multirate systems is presented. The approach is a compilation of existing multirate performance and robustness analysis results, along with some new results, all presented in a consistent state-space formulation. The approach is used to analyze the robustness of a multirate flutter suppression system designed for a model wing. The example highlights some of the practical considerations in multirate performance and robustness analysis.

关键词： flutter suppression system Nyquist Stability Criterion Multiple Input, Multiple Output NASA Langley Research Center Numerical Simulation Composite Structures Mathematical Models Frequency Domain Feedback Loop Accelerometer

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ACCELEROMETER PLACEMENT IN ACTIVE flutter suppression systemS

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1987年第5期10卷 441-446页

作者： LIEBST, BS University of Minnesota Minneapolis Minnesota

An elementary study of the placement of accelerometers when used as sensors in active flutter suppression systems is presented. The model analyzed is a two-dimensional typical section with various combinations of leading- and trailing-edge controllers. The relationship between the control surface placement and accelerometer placement is examined. The results for the numerical examples presented show that accelerometers must be on the same side of the center of gravity as the control surface or right half-plane transmission zeros will arise. The detrimental effects of the right half-plane zeros are discussed in the context of linear-quadratic-regulator plus loop-transfer-recovered observer designs.

关键词： flutter suppression system Accelerometer Trailing Edges Linear Quadratic Regulator Sensors Feedback Control system Control Surfaces Aerodynamic Damping Angle of Attack Kalman Filter

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LOW-FREQUENCY RESPONSE OF ACCELEROMETERS FOR OBSERVER DESIGN IN A GRAVITY ENVIRONMENT

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1990年第4期13卷 732-737页

作者： NORRIS, MA THOMPSON, RC DAS, A PENN STATE UNIV DEPT AEROSP ENGNUNIVERSITY PKPA 16802 USAF ASTRONAUT LABEDWARDS AFBEDWARDS AFBCA 93523

Analytical and experimental results demonstrate that the dynamic effect of gravity degrades low-frequency accelerometer measurements. The attitude of an accelerometer in motion in a constant uniform gravity field can cause the output signal to indicate an incorrect amplitude (magnitude and phase) relative to the actual acceleration of the point on the structure at which the sensor is mounted. The effect of gravity is to attenuate the accelerometer signals to the extent that a 180-deg phase shift between signals at different locations may occur in the lower modes of vibration. The positions on the structure where the phase shift occurs are called accelerometer nodal locations, because the output of accelerometers located at these positions are theoretically zero. The effect is demonstrated analytically and experimentally when results from a pendulum and a two-dimensional grid structure are used. An observer is designed for the grid structure in which accelerometer measurements are used as input. The observer performance, including the dynamic effect of gravity on the accelerometer, is compared to the performance of an observer using the output signal from the accelerometers without compensating for the signal errors induced by the gravity field. The results show that the dynamic effect of gravity must be included in the observer design for low-frequency response estimates in a gravity environment. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Frequency Response Accelerometer Proximity Sensors Kalman Filter Transverse Vibrations Flexible Structures Newton's Second Law Active Vibration suppression Mathematical Models flutter suppression system

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Active flutter suppression: Quantification of Performance Loss Due to Actuator Saturation

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2024年第11期47卷 2333-2350页

作者： Micheli, Boris German Aerosp Ctr DLR Inst Aeroelast Dept Aeroelast Simulat Bunsenstr 10 D-37073 Gottingen Germany

Active flutter suppression technologies have the potential to lead to major weight savings while keeping the envisaged flight envelope for the future generation of commercial aircraft. Since the stabilization of aeroelastic systems undergoing flutter instabilities is strongly affected by actuators' characteristics and delays in the closed loop, the degradation of closed-loop performance due to actuators' nonlinearities must be thoroughly understood. Comparisons between the region of attraction and the controllable region can support the quantification of performance loss due to common actuators' nonlinearities, such as amplitude and rate limits. At first, this paper illustrates a numerically robust algorithm for the full characterization of the controllable region of a generic unstable system under input amplitude and rate constraints. Secondly, the concept of region of attraction is expanded to assess the boundedness of the closed-loop response in the presence of input saturation and atmospheric disturbances. These concepts are here employed to define two nonlinear performance measures that quantify the performance loss due to actuators' saturation in an unstable aeroelastic system stabilized by a flutter suppression controller. The approach is demonstrated on a realistic aeroelastic system for which different H2 and H infinity output feedback controllers are synthesized to augment the damping of the critical flutter mode.

关键词： Electro Hydraulic Actuator Linear Time Invariant Aeroservoelastic systems Full State Feedback Commercial Aircraft Dynamic Pressure Benchmark Active Control Technology Aeroservoelasticity flutter suppression system Robust Control

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DESIGN AND EXAMINATION OF H-INFINITY ROBUST CONTROLLER FOR GROUND EFFECT PROBLEM

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1995年第4期18卷 740-747页

作者： NITTA, K Nagoya Univ. Aichi Japan

An aeroelastic problem in the ground effect is treated. The H(i)nfinity control theory based on the loop-shaping design procedure is applied to designing controllers for flutter suppression and attenuation of the aerodynamic disturbance caused by the ground irregulation. A two-dimensional Bat-plate airfoil with three degrees of freedom, plunging, pitching, and control surface deflection is treated. The aeroelastic characteristics vary according to the altitude at which the airfoil is flying. Stability analysis and controller design are performed with the models with aerodynamic data obtained by the doubler-lattice method aerodynamic calculations and Pade approximation with two lag terms. Examination of robustness of the designed controllers are performed with numerical experiments using the finite difference method.

关键词： Open Loop Transfer Function Airfoil Finite Difference Method Three Degrees of Freedom Aerodynamic Characteristics flutter suppression system Wind Tunnel Tests Linear Quadratic Gaussian Ground Effect Vehicle Navier Stokes Equations

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