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Robust fault-tolerant control for wing flutter under actuator failure

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Chinese Journal of Aeronautics 2016年第4期29卷 1007-1017页

作者： Gao Mingzhou Cai Guoping Department of Engineering Mechanics State Key Laboratory of Ocean Engineering Shanghai Jiaotong University

Many control laws, such as optimal controller and classical controller, have seen their applications to suppressing the aeroelastic vibrations of the aeroelastic system. However, those control laws may not work effectively if the aeroelastic system involves actuator faults. In the current study for wing flutter of reentry vehicle, the effect of actuator faults on wing flutter system is rarely considered and few of the fault-tolerant control problems are taken into account. In this paper, we use the radial basis function neural network and the finite-time H-infinity adaptive fault-tolerant control technique to deal with the flutter problem of wings, which is affected by actuator faults, actuator saturation, parameter uncertainties and external disturbances. The theory of this article includes the modeling of wing flutter and fault-tolerant controller design. The stability of the finite-time adaptive fault-tolerant controller is theoretically proved. Simulation results indicate that the designed fault-tolerant flutter controller can effectively deal with the faults in the flutter system and can promptly suppress the wing flutter as well. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license.

关键词： Actuator fault Actuator saturation aeroservoelasticity Fault-tolerant control Flutter Observer

Study on gust alleviation control and wind tunnel test

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Science China Technological Sciences 2013年第3期56卷 762-771页

作者： WU ZhiGang CHEN Lei YANG Chao School of Aeronautic Science and Engineering Beijing University of Aeronautics and Astronautics Division of Structural Strength Shanghai Aircraft Design and Research Institute

Aircraft are inevitably affected by gust during flight,which disturbs the regular operations of pilots and worsens the ride *** more grievous cases,flight mission cannot be completed and the flight safety may be *** order to improve the ride quality and the fatigue life of the plane structure under the affect of gust,it is necessary to explore and validate the gust alleviation *** the low-speed wind tunnel test,the gust alleviation active control technology applied to elastic aircraft is *** a large-type passenger plane configuration with high aspect ratio wing,a test system was designed and three gust alleviation control schemes with PID controllers were *** the gust alleviation control low-speed wind tunnel test was carried out in the FD-09 wind *** results showed that at certain speed and gust frequency,all of the 3 control schemes can alleviate the acceleration at fuselage and wing-tip to a certain extent,as well as the bending moment of *** gust alleviation control scheme,which uses aileron,elevator and canard as control surfaces synthetically,gives the most satisfying gust alleviation effect.

关键词： aeroelasticity aeroservoelasticity gust response gust alleviation active control wind tunnel test

Aeroservoelastic stability analysis for flexible aircraft based on a nonlinear coupled dynamic model

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Chinese Journal of Aeronautics 2018年第12期31卷 2185-2198页

作者： Yi LIU Changchuan XIE Beijing Institute of Electrical and Mechanical Engineering Beijing 100074China School of Aeronautic Science and Engineering Beihang UniversityBeijing 100083China

A unified theoretical aeroservoelastic stability analysis framework for flexible aircraft is established in this paper. This linearized state space model for stability analysis is based on nonlinear coupled dynamic equations, in which rigid and elastic motions of aircraft are both *** common body coordinate system is utilized as the reference frame in the deduction of dynamic equations, and significant deformations of flexible aircraft are also fully concerned without any excessive assumptions. Therefore, the obtained nonlinear coupled dynamic models can well reflect the special dynamic coupling mechanics of flexible aircraft. For aeroservoelastic stability analysis,the coupled dynamic equations are linearized around the nonlinear equilibrium state and together with a control system model to establish a state space model in the time domain. The methodology in this paper can be easily integrated into the industrial design process and complex *** results for a complex flexible aircraft indicate the necessity to consider the nonlinear coupled dynamics and large deformation when dealing with aeroservoelastic stability for flexible aircraft.

关键词： aeroservoelasticity Flexible aircraft Geometric nonlinearity Nonlinear coupled dynamics Stability control

Parameterized Analysis of Aeroservoelastic Stability for Closed-Loop Aircraft

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Journal of Beijing Institute of Technology 2024年第5期33卷 450-464页

作者： Jihang Lyu Fei Yang Rong Yang Beijing ZhongHangZhi Technology Co. Ltd.Beijing 100176China Shanghai Aircraft Design and Research Institute Shanghai 201210China AVIC General Huanan Aircraft Industry Co.Ltd.Zhuhai 519040 China

The closed-loop flight control system of fly by wire is generally adopted in modern *** on the frequency-domain stability analysis,the aeroservoelastic model of closedloop aircraft is established,and aeroservoelastic stability parameterized calculation of design improvement is conducted after the preliminary *** design variables are mounted location of integrated sensors and damping coefficientsζ_(1),ζ_(2) of notch filter,with stability margin of the system as design *** indicate that aeroservoelastic margin of the aircraft in certain states is *** the mounted location of integrated sensors is adjusted,the system stability can be improved to certain ***’s more appropriate to mount the integrated sensors in the overlapping field between the nodal lines of vertical and lateral bending for the *** system stability is also significantly improved by adding notch filter,both gain margin and phase margin increase when the real number pairζ_(1)-ζ_(2) is located in the zone above the 45°diagonal ofζ_(1),ζ_(2) con-struction plane,and the farther theζ_(1)-ζ_(2) is from the 45°diagonal,the stronger the system *** the decrease in the gain peak of frequency response and the enhancement of relative stability of the system are achieved by the appropriateζ_(1)-ζ_(2) of notch filter.

关键词： aeroservoelasticity mounted location of sensors notch filter stability margin response peak