Disturbance observer design and vibration control for a flexible aircraft wing

Zhang, Yuanyuan; Liu, Jinkun; He, Wei

doi:10.1177/0142331217730887

Cited by 11 publications

(5 citation statements)

References 37 publications

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“…e boundary disturbance observer-based control problem of a vibrating single-link flexible manipulator system with external disturbances was studied in [43]. In [44], considering the influence of extraneous disturbance acting on the wing, a new observer was proposed for controller design. A new disturbance observer was proposed to deal with the distributed disturbance and boundary disturbance of a flexible-link manipulator in [45].…”

Section: Introductionmentioning

confidence: 99%

Vibration Suppression of a Coupled Aircraft Wing with Finite‐Time Convergence

et al. 2022

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A nonlinear coupled wing model subject to unknown external disturbances is proposed in this paper. Since the model is modeled by partial differential equations, the traditional control design scheme based on the ordinary differential equation model is not applicable, and the control law design becomes very complex. In this paper, a new antidisturbance boundary control scheme based on a finite time convergent disturbance observer is proposed. The control laws are designed based on the new disturbance observers to make the external disturbance errors converge to zero in a finite time and ensure the uniformly bounded stability of the controlled system. Finally, the effectiveness of the controllers and the finite-time convergence of disturbance errors are verified by the simulation and comparison.

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Section: Introductionmentioning

confidence: 99%

Vibration Suppression of a Coupled Aircraft Wing with Finite‐Time Convergence

et al. 2022

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“…During flight, the wings and fuselage of the aircraft with flexible materials are affected by unknown external disturbances, which are mainly caused by wind, aircraft acceleration, and gravity (Zhang et al, 2018). In this study, slow time-varying boundary disturbances were considered during controller design.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fault-tolerant boundary vibration control for a flexible aircraft wing against actuator and sensor faults

Gao

Liu

2021

Journal of Vibration and Control

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The vibration control problem was investigated in this study in the presence of unknown loss of actuator effectiveness fault and loss of sensor effectiveness fault in a flexible aircraft wing system. A series of partial differential equations was used as the mathematical model of the wing with unknown boundary disturbances. An adaptive fault-tolerant boundary controller was designed accordingly. All signals of the closed-loop control system are globally uniformly bounded and the controlled state asymptotically converges. Numerical simulations were conducted to validate the proposed control scheme.

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“…Many researchers have studied the Euler‐Bernoulli beam because it has practical applications, such as flexible robotic manipulator, flexible satellite, flexible aircraft wing, and nonuniform gantry crane . In the work of Liu et al, a finite‐dimensional backstepping method is adopted to design a boundary controller with a disturbance observer to suppress the vibration of an axially moving belt system.…”

Section: Introductionmentioning

confidence: 99%

Adaptive neural network control for a nonlinear Euler‐Bernoulli beam in three‐dimensional space with unknown control direction

Liu

2019

Intl J Robust & Nonlinear

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Summary In this paper, an adaptive neural network control system is developed for a nonlinear three‐dimensional Euler‐Bernoulli beam with unknown control direction. The Euler‐Bernoulli beam is modeled as a combination of partial differential equations (PDEs) and ordinary differential equations (ODEs). Adaptive radial basis function–based neural network control laws are designed to determine approximation of disturbances. A projection mapping operator is adopted to realize bounded approximation of disturbances. A Nussbaum function is introduced to compensate for the unknown control direction. The goal of this study is to suppress the vibrations of the Euler‐Bernoulli beam in three‐dimensional space. In addition, unknown control direction problem and bounded disturbances are considered to guarantee that the signals of the system are uniformly bounded. Numerical simulations demonstrate the effectiveness of the proposed method.

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Disturbance observer design and vibration control for a flexible aircraft wing

Cited by 11 publications

References 37 publications

Vibration Suppression of a Coupled Aircraft Wing with Finite‐Time Convergence

Vibration Suppression of a Coupled Aircraft Wing with Finite‐Time Convergence

Adaptive fault-tolerant boundary vibration control for a flexible aircraft wing against actuator and sensor faults

Adaptive neural network control for a nonlinear Euler‐Bernoulli beam in three‐dimensional space with unknown control direction

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