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Adaptive fault-tolerant boundary control for a flexible aircraft wing with input constraints

机译：具有输入约束的柔性飞机机翼的自适应容错边界控制

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This paper discusses the boundary control problem of actuator input constraints for a flexible aircraft wing in the presence of unknown external disturbances and unknown actuator failure. Based on the application of smooth hyperbolic function and a projection algorithm, an innovative adaptive boundary controller with an external disturbance estimator is designed to suppress the bending and twist deformations of the flexible aircraft wing. The flexible aircraft wing is modeled as a coupled twist-bending system, the dynamics of which are described by several partial differential equations (PDEs) and ordinary differential equations (ODES). The proposed boundary control scheme is shown to satisfy the input restrictions and physical conditions. The elastic vibration and vibration rate of the flexible aircraft wing system is also eliminated successfully even after the actuator failure. Both theoretical analysis and numerical simulations are provided which demonstrate the effectiveness of the proposed scheme. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：本文讨论了在存在未知外部干扰和未知执行器故障的情况下，柔性飞机机翼执行器输入约束的边界控制问题。基于光滑双曲函数和投影算法的应用，设计了一种带有外部干扰估计器的创新型自适应边界控制器，以抑制柔性飞机机翼的弯曲和扭曲变形。柔性飞机机翼被建模为耦合的弯曲弯曲系统，其动力学由几个偏微分方程（PDE）和常微分方程（ODES）描述。所提出的边界控制方案表明满足输入限制和物理条件。即使执行器发生故障，柔性飞机机翼系统的弹性振动和振动率也可以成功消除。提供了理论分析和数值模拟，证明了该方案的有效性。 （C）2019 Elsevier Masson SAS。版权所有。

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