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active flutter suppression of nonlinear fin-actuator system via inverse system and immersion and invariance method

Chinese Journal of Aeronautics 2024年第4期37卷 343-362页

作者： Jin LU Zhigang WU Chao YANG Chinese Aeronautical Establishment Beijing 100029China School of Aeronautic Science and Engineering Beihang UniversityBeijing 100191China

Structural nonlinearities such as freeplay will affect the stability and even flight safety of the fin-actuator *** is a lack of a practical method for designing active flutter suppression (AFS) control laws for nonlinear fin-actuator systems.A design method for the AFS controller of the nonlinear all-movable fin-electromechanical actuator system is established by combining the inverse system and the Immersion and Invariance (I&I) ***,the composite control law combining the inverse system principle and internal model control is used to offset the nonlinearity and dynamics of the actuator,so that its driving torque can follow the ideal ***,the ideal torque of the actuator is designed employing the I&I *** unfavorable oscillation of the fin is suppressed by making the output torque of the actuator track the ideal *** simulation results reveal that the proposed AFS method can increase the flutter speed of the nonlinear finactuator system with freeplay,and a set of controller parameters is also applicable for wider freeplay within a certain *** power required for the actuator does not exceed the power that can be provided by the commonly used aviation *** method can also resist a certain level of noise and external disturbance.

关键词： Aeroelasticity active flutter suppression Fin-actuator system Freeplay Inverse system Immersion and invariance

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

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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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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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Synthesis of an active flutter suppression system in the transonic domain using a computational model

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AERONAUTICAL JOURNAL 2021年第1293期125卷 2002-2020页

作者： Vepa, R. Kwon, J. R. Queen Mary Univ London Sch Engn & Mat Sci London E1 4NS England Agcy Def Dev Aerosp Technol Res Inst Daejeon 34186 South Korea

Control laws for implementing active flutter suppression are generally derived from linear aeroelastic models. In this paper, families of control laws for implementing an active flutter suppression system were initially designed using linearised aeroelastic models based on the doublet lattice method after ignoring the aerodynamic loads associated with relatively faster time scales. Using these preliminary sets of control laws and the nonlinear transonic small disturbance theory, near-optimum control laws were chosen in the transonic domain to maximally increase the flutter speed of a typical aircraft wing by at least 16% or more. Thus it is shown that it is feasible to systematically design near-optimal control laws for active flutter suppression using computational models in transonic flow. The doublet lattice method coupled with the zeroth-order matrix Pade approximant provided the fastest method for synthesising a large number of preliminary control laws. The methodology was successfully demonstrated by applying it to two benchmarking examples.

关键词： Unsteady transonic flow Potential flow Transonic small disturbance Doublet lattice method flutter analysis active flutter suppression Control law synthesis

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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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Research on model-free adaptive active flutter suppression based on ridge regression

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AERONAUTICAL JOURNAL 2024年第1323期128卷 950-965页

作者： Yu, J. Qi, H. Du, J. Wang, K. Guo, J. Harbin Engn Univ Coll Aerosp & Civil Engn Harbin 150001 Peoples R China Harbin Engn Univ Key Lab Vehicle Transmedia Technol Harbin 150001 Peoples R China

Traditional active flutter suppression controllers are designed based on model. However, as the aircraft becomes more and more powerful, the modeling of aeroelastic system becomes difficult and the model-free requirement of controller design becomes more and more urgent. The complexity of industrial processes has brought about massive operational data generated online. Aviation industry development has entered the era of big data. Breaking through the traditional theoretical framework, mining the correlation, evolution and dynamic characteristics of the system from the data is the inevitable choice to meet this demand. In this paper, a data-driven model-free controller is designed, which relies on ridge regression of the input and output variation at each operating point of the closed-loop controlled system to recursively derive the iterative format of the control signals and ensure the numerical stability of the signals. The controller can only use the real-time measurement of the system's online input and output data for continuous correction, to achieve the purpose of flutter suppression. Then flutter suppression of a three-degree-of-freedom binary wing with a control surface is studied, and the superiority of model-free controller is demonstrated by comparing it with the optimal controller.

关键词： ridge regression active flutter suppression data drive

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active flutter suppression of a Two-Dimensional Wing Using Linear Quadratic Gaussian Optimal Control

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INTERNATIONAL JOURNAL OF STRUCTURAL STABILITY AND DYNAMICS 2022年第14期22卷 2250157-2250157页

作者： Darabseh, T. T. Tarabulsi, A. M. Mourad, A-H, I Jordan Univ Sci & Technol Aeronaut Engn Dept POB 3030 Irbid 22110 Jordan United Arab Emirates Univ Mech & Aerosp Engn Dept POB 15551 Abu Dhabi U Arab Emirates

This paper aims to utilize the modern control theory in designing an active flutter suppression controller for a two-dimensional wing with a flap. In this study, the wing's pitch-plunge linear aeroelastic response, in addition to the control flap motion, was modeled using Lagrange's energy method, and Theodorsen's classic unsteady aerodynamic theory. The derived mathematical model was represented in state-spare so the modern control techniques can be implemented. The open-loop system was analyzed, and the flutter speed for a selected experimental-wing model was calculated. For model verification purposes, the open-loop simulation results were compared to an experimental study from the literature. Next, a linear quadratic Gaussian (LQG) compensator with integral action was designed and timed using MATLAB (R) simulation environment to reach the best possible performance at a selected speed in the flutter region, where the results have proven excellent performance for this kind of controller in flutter suppression, as the stable flight region has successfully been extended by 29%.

关键词： active flutter suppression optimal control linear quadratic controller (LQR) state estimator (Kalman filter) linear quadratic Gaussian (LQG) Integral action

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active flutter suppression of wing with morphing flap

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AEROSPACE SCIENCE AND TECHNOLOGY 2021年 110卷 106457-106457页

作者： Ouyang, Yan Gu, Yingsong Kou, Xiping Yang, Zhichun Northwestern Polytech Univ Sch Aeronaut Inst Struct Dynam & Control Xian 710072 Peoples R China

The flutter characteristics of a wing with morphing flap are analyzed based on computational fluid dynamics (CFD) method. The unsteady aerodynamic reduced order model (ROM) is constructed to model the morphing flap with high accuracy, and the effect of flap camber on the wing flutter boundary is investigated. active suppression of aeroelastic response by controlling the flap deflection is validated through numerical simulations. A Linear Quadratic Gaussian (LQG) compensator is designed to explore the potential of suppressing wing flutter by deflecting the flap actively. The simulation results show that the order of morphing flap camber may change the critical flutter speed and flutter frequency of the wing. Compared with the conventional plain flap, the morphing flap shows higher control efficiency with fewer deflection demands. (C) 2020 Elsevier Masson SAS. All rights reserved.

关键词： Morphing flap active flutter suppression Reduced order model LQG controller

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