Research on Adaptive Prescribed Performance Control Method Based on Online Aerodynamics Identification

An, Shuaibin; Zang, Jianwen; Yan, Mi; Zhu, Baiyang; Li, Jun

doi:10.3390/drones7010050

Cited by 3 publications

(2 citation statements)

References 25 publications

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“…为了利用飞行数据进行空气动力学建模 [26] , 首先将空气动力学中无量纲的力和力矩系数作为建模问题的因变量, 由于不能在飞行中直接测量无量纲空气动力和力矩系数的值, 所以必须使用以下等式从测量的和已知的量中计算得出, 本文主要对纵向俯仰力矩相关的参数进行辨识, 纵向俯仰力矩的计算公式:…”

Section: 基于自适应重构控制的主动容错控制方法unclassified

“…其中, m z0 是当其余参数为 0 时的俯仰力矩系数, m α z 时静稳定系数, m δz z 是舵效参数, m ωz z 是俯仰阻尼力矩系数, δ z 是升降舵偏转大小, m φ th 是燃油当量比引起的俯仰力矩变化参数. 接着利用递归最小二乘的方法得到所需要的辨识参数, 下面简单按照文献 [26] 介绍递归最小二乘方法(RLS), 首先将动力学模型与气动参数写成线型参数模型.…”

Section: 基于自适应重构控制的主动容错控制方法unclassified

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高超声速飞行器主被动复合一体化容错控制方法研究

Zhou,

Fu,

Yang

2024

Sci. Sin.-Inf.

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Airbreathing hypersonic vehicles (AHVs) feature a severe force and thermal loads flight environment, which leads to a high risk of elevator failures such as embrittlement, thermal damage, chipping, furthermore to affect the attitude control accuracy degradation and even destabilization. Accordingly, this paper proposes a faulttolerant control strategy via the active-passive composite approach, which employs a sliding mode control (SMC) to guarantee the robustness of the system when aerodynamic parameters change abruptly at the initial stage of an elevator failure. Simultaneously, sensor data and the online aerodynamic identification approach are utilized to calculate aerodynamic force damages. After meeting the transient stabilization requirements, it will switch to the adaptive integrated-flight-propulsion control, thereby performing control reconfiguration and enhancing the flight control quality after the failure occurs. Finally, the simulation results verify the effectiveness and robustness of the strategy and also show a robustness and better control effect compared with a single fault-tolerant control strategy.

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Section: 基于自适应重构控制的主动容错控制方法unclassified

高超声速飞行器主被动复合一体化容错控制方法研究

Zhou,

Fu,

Yang

2024

Sci. Sin.-Inf.

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Adaptive fault‐tolerant control for aircraft against control surface failure diagnosed by set‐membership estimation

Liu,

An,

Tang

et al. 2024

Asian Journal of Control

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This paper focuses on the fault diagnosis method and the fault‐tolerant control method of the aircraft with control surface damage. The fault diagnosis method is based on the set‐membership estimation. To diagnose the fault of control surface under the condition of data containing noise and uncertainty, a multi‐index optimized fault residual observer based on sensitivity and robustness is designed for the observation of aircraft fault information. Based on the observed fault residual information, the set‐membership estimation theory is used to determine whether the aircraft control surface fault occurs. The fault‐tolerant control method is based on dynamic inverse control via aerodynamic parameter identification. Furthermore, to reduce the nonlinear effects of unmodeled dynamics and aerodynamic identification errors after a fault, an adaptive disturbance rejection observer is designed for control compensation. The proposed methods are evaluated by numerical simulation. Results demonstrate that the fault diagnosis method can effectively diagnose under the influence of uncertain noise and the attitude control has the robustness of different faults.

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Analysis of Dynamic Systems Through Artificial Neural Networks

Hamad,

Khalf,

Abdoon

et al. 2024

Tikrit j. eng. sci.

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Parameter identification techniques for linear and nonlinear dynamic systems currently show a clear orientation toward black box models, with Artificial Neural Networks occupying a prominent place there. This paper presents a procedure for identifying linear dynamic systems parameters in two stages: in the first, a regressive model is fitted from the excitation and response time records, and in the second, its parameters are identified (matrixes of stiffness and damping) and dynamic characteristics (vibration frequencies and modes) based on the previous model. Artificial Neural Networks of the Adaline type and multilayer Perceptions are used for the first stage. The second stage is fully formulated through matrix algebra, which facilitates its systematic implementation and makes it independent of the complexity or dimension of the studied system. The proposed procedure is intended to operate from experimental records, so special attention is paid to the sensitivity of the results to the data interval and noise in the input signals. For the latter, various noise levels were incorporated into the correct responses obtained under ideal conditions, which respond to Gaussian distribution functions with a null mean and specified standard deviation. The proposed procedure justification, the results with the regressive models, and a study of the sensitivity of the results to the variation in the available data quality are presented.

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Research on Adaptive Prescribed Performance Control Method Based on Online Aerodynamics Identification

Cited by 3 publications

References 25 publications

高超声速飞行器主被动复合一体化容错控制方法研究

高超声速飞行器主被动复合一体化容错控制方法研究

Adaptive fault‐tolerant control for aircraft against control surface failure diagnosed by set‐membership estimation

Analysis of Dynamic Systems Through Artificial Neural Networks

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