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gust load alleviation wind tunnel tests of a large-aspect-ratio flexible wing with piezoelectric control

Chinese Journal of Aeronautics 2017年第1期30卷 292-309页

作者： Bi Ying Xie Changchuan An Chao Yang Chao School of Aeronautic Science and Engineering Beihang University

An active control technique utilizing piezoelectric actuators to alleviate gust-response loads of a large-aspect-ratio flexible wing is investigated. Piezoelectric materials have been extensively used for active vibration control of engineering structures. In this paper, piezoelectric materials further attempt to suppress the vibration of the aeroelastic wing caused by gust. The motion equation of the flexible wing with piezoelectric patches is obtained by Hamilton＇s principle with the modal approach, and then numerical gust responses are analyzed, based on which a gust load alleviation（GLA） control system is proposed. The gust load alleviation system employs classic propor tional-integral-derivative（PID） controllers which treat piezoelectric patches as control actuators and acceleration as the feedback signal. By a numerical method, the control mechanism that piezoelectric actuators can be used to alleviate gust-response loads is also analyzed qualitatively. Furthermore, through low-speed wind tunnel tests, the effectiveness of the gust load alleviation active control technology is validated. The test results agree well with the numerical results. Test results show that at a certain frequency range, the control scheme can effectively alleviate the z and x wingtip accelerations and the root bending moment of the wing to a certain extent. The control system gives satisfying gust load alleviation efficacy with the reduction rate being generally over 20%.

关键词： Active control Aeroelastic wing gust load alleviation gust response Piezoelectric actuators Wind tunnel test

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Mixed H_2/H_∞ Control Using a Fuzzy Singularly Perturbed Model with Multiple Perturbation Parameters for gust load alleviation

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Tsinghua Science and Technology 2011年第4期16卷 344-351页

作者：袁源胡叶楠孙富春 Department of Computer Science and Technology Tsinghua University Beijing Institute of Astronautical System Engineering

This paper presents a mixed H21H∞ control using fuzzy singularly perturbed model （FSPM） with multiple perturbation parameters. Since FSPM with multiple perturbation parameters is an extension of models with a single perturbation parameter, the theoretical results are applicable to a larger class of systems described by multiple time scale nonlinear models, such as flying aircraft and flexible space robots. The parameter-independent solution of the mixed H21H∞ controller was obtained in the form of linear matrix inequalities （LMIs）. The application of this approach to gust load alleviation of a flying vehicle verifies its effectiveness and flexibility.

关键词： fuzzy singularly perturbed model (FSPM) mixed H21∞Hcontrol multiple perturbation parameters gust load alleviation flying vehicle

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Improved LQG Method for Active gust load alleviation

Improved LQG Method for Active Gust Load Alleviation

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2016年航空科学与技术全国博士生学术论坛

作者： Xiang Liu Qin Sun School of Aeronautics Northwestern Polytechnical University

Against a background of various techniques for gust load alleviation(GLA), this paper aims at proposing an improved linear quadratic Gaussian(LQG) method, which is robust to variations of flight parameters, structural parameters and modeling errors, and suitable for application in the structure/control design optimization. This new technique differs from the traditional LQG methodology by the introduction of properly constructed fictitious high frequency noise. Furthermore, to accurately measure the stability margins of the multi-input multi-output(MIMO) controllers, a variable-structure μ analysis method is proposed. The parameters of Dryden continuous gust model is adjusted according to the structural natural frequencies to meet the design requirements and model reduction combined with input signal scaling is applied to reduce the controller order. Using a general transport aircraft(GTA) model, the robust performance and robust stability of the improved LQG method are compared with those of the modern robust controllers, including the H controller and the μ-synthesis controller. The numerical results demonstrate the successful application of this new technique.

关键词： gust load alleviation active control linear quadratic Gaussian fictitious noise stability margin

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