Hybrid fault-tolerant flight control against actuator faults and input saturation: a set-invariance approach

2012 ◽  
Author(s):  
Jinhua Fan ◽  
Youmin Zhang ◽  
Zhiqiang Zheng
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Input Saturation ◽  
Actuator Faults ◽  
Set Invariance

Robust fault-tolerant control design for hypersonic vehicle with input saturation and actuator faults

2021 ◽  
pp. 095441002110412
Author(s):  
Zhong-Zhe Yue ◽  
Jing-Guang Sun
Keyword(s):  
Feedback Linearization ◽  
Fault Tolerant ◽  
Input Saturation ◽  
Lyapunov Stability Theory ◽  
Hypersonic Vehicle ◽  
Actuator Faults ◽  
Closed Loop System ◽  
External Disturbances ◽  
Longitudinal Tracking ◽  
Tangent Function

This study investigates the flight longitudinal tracking control problem of hypersonic vehicle in presence of the input saturation, external disturbances, model parametric uncertainties, and actuator faults. First, the velocity and altitude subsystem are established with disturbances based on the feedback linearization model. Second, two robust anti-saturation fault-tolerant controllers are designed for the velocity subsystem and altitude subsystem by the utilization of the tangent function, Nussbaum function, and adaptive nonlinear filter. Finally, Lyapunov stability theory is used to prove that the states of the closed-loop system are bounded. And, the effectiveness and robustness of the control strategy are proved by numerical simulations.

Fixed-time three-dimensional guidance law with input constraint and actuator faults

2020 ◽  
pp. 095441002097197
Author(s):  
Peng Li ◽  
Qi Liu ◽  
Chen-Yu He ◽  
Xiao-Qing Liu
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Impact Angle ◽  
Actuator Faults ◽  
Input Constraint ◽  
Guidance Law ◽  
The Impact ◽  
Impact Angle Constraint

This paper investigates the three-dimensional guidance with the impact angle constraint, actuator faults and input constraint. Firstly, an adaptive three-dimensional guidance law with impact angle constraint is designed by using the terminal sliding mode control and nonhomogeneous disturbance observer. Then, in order to solve the problem of the input saturation and actuator faults, an adaptive anti-saturation fault-tolerant three-dimensional law is proposed by using the hyperbolic tangent function based on the passive fault-tolerant control. Finally, the effectiveness of the designed guidance laws is verified by using the Lyapunov function and simulation.

scholarly journals Robust Fault Tolerant Control for a Class of Time-Delay Systems with Multiple Disturbances

2013 ◽  
Vol 2013 ◽  
pp. 1-8
Author(s):  
Songyin Cao ◽  
Jianzhong Qiao
Keyword(s):  
Time Delay ◽  
Flight Control ◽  
Disturbance Rejection ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Delay Systems ◽  
Actuator Faults ◽  
Flight Control System ◽  
Multiple Disturbances ◽  
Fault Accommodation

A robust fault tolerant control (FTC) approach is addressed for a class of nonlinear systems with time delay, actuator faults, and multiple disturbances. The first part of the multiple disturbances is supposed to be an uncertain modeled disturbance and the second one represents a norm-bounded variable. First, a composite observer is designed to estimate the uncertain modeled disturbance and actuator fault simultaneously. Then, an FTC strategy consisting of disturbance observer based control (DOBC), fault accommodation, and a mixedH2/H∞controller is constructed to reconfigure the considered systems with disturbance rejection and attenuation performance. Finally, simulations for a flight control system are given to show the efficiency of the proposed approach.

Distributed fault-tolerant formation control for multiple unmanned aerial vehicles under actuator fault and intermittent communication interrupt

2021 ◽  
pp. 095965182097908
Author(s):  
Bing Han ◽  
Ju Jiang ◽  
Chaojun Yu
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Formation Control ◽  
Fault Tolerant ◽  
Input Saturation ◽  
Actuator Faults ◽  
Aerial Vehicles ◽  
Multiple Unmanned Aerial Vehicles ◽  
The Stability ◽  
Intermittent Communication ◽  
Formation System

This article develops a distributed adaptive fault-tolerant formation control scheme for the multiple unmanned aerial vehicles to counteract actuator faults and intermittent communication interrupt, where the issues on control input saturation and mismatched uncertainties are also addressed. The discontinuous communication protocol technique is exploited to achieve the stability of the formation system, if the conditions of dwell time and the rate of communication are satisfied. On the basis of the local information of neighboring unmanned aerial vehicles, a novel distributed adaptive mechanism is designed to estimate the bounds of actuator faults and uncertainties, where the input saturation is explicitly taken into consideration. The stability of the whole formation system under the designed fault-tolerant formation control strategy is analyzed using the Lyapunov approach. Finally, simulation results are presented to illustrate the effectiveness of the proposed scheme.

Adaptive anti-saturation fault-tolerant control of hypersonic vehicle with actuator faults

2018 ◽  
Vol 233 (6) ◽  
pp. 2066-2083
Author(s):  
Jing-guang Sun ◽  
Shen-Min Song ◽  
Peng-Li ◽  
Guan-qun Wu
Keyword(s):  
Finite Time ◽  
Control Method ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Input Saturation ◽  
Reference Signal ◽  
Fault Tolerant Control ◽  
Hypersonic Vehicle ◽  
Actuator Faults ◽  
The Impact

In this paper, related researches and analyses are conducted for the tracking problem of the hypersonic vehicle subject to external disturbances, actuator faults, and input saturation. Firstly, to achieve automatic adjustment of control gains and deal with the impact of dynamic failures of system without requiring prior knowledge of the fault, a new modified fast nonsingular terminal sliding manifold is proposed, and a fast adaptive finite time fault-tolerant controller is provided combining the adaptive control method and terminal sliding mode. Then, a fast adaptive finite time anti-saturation fault-tolerant controller is presented to further solve the problem of input saturation, under which both of the velocity and altitude can track respective reference signal with the actuator input constraint. Finally, the closed-loop stability under the proposed two adaptive fault-tolerant control schemes is analyzed, and numerical simulations of longitudinal model of the hypersonic vehicle are demonstrated to further confirm the effectiveness of the proposed approach.

Robust constrained fault-tolerant attitude control for flexible spacecraft

2017 ◽  
Vol 232 (16) ◽  
pp. 3011-3023 ◽  
Author(s):  
Haihui Long ◽  
Jiankang Zhao
Keyword(s):  
Attitude Control ◽  
Fault Tolerant ◽  
External Disturbance ◽  
Input Saturation ◽  
Flexible Spacecraft ◽  
Disturbance Attenuation ◽  
Actuator Faults ◽  
Partial Loss ◽  
Unknown Parameters ◽  
Disturbance Model

In this paper, robust constrained fault-tolerant attitude controllers are proposed for flexible spacecraft subjected to external disturbance, model uncertainty, input saturation, and actuator faults. Three types of actuator faults of spacecraft, i.e. partial loss of effectiveness, stuck fault, and outage fault, are modeled explicitly. To handle these actuator faults, a significant lemma is proposed and rigorous proof is conducted at length. By introducing two e-modification parameter update laws to online estimate the unknown parameters caused by actuator faults, constrained fault-tolerant attitude controllers of flexible spacecraft are designed to accommodate these faults without the need of any prior information about these faults. The proposed controllers can achieve the disturbance attenuation in the sense of [Formula: see text] gain. The effectiveness of the proposed algorithms is assessed through numerical simulations.

Integrated sensor/actuator FDI and reconfigurable control for fault-tolerant flight control system design

2001 ◽  
Vol 105 (1051) ◽  
pp. 525-533 ◽  
Author(s):  
Ch. M. Hajiyevt ◽  
F. Caliskan
Keyword(s):  
Control System ◽  
Flight Control ◽  
Fault Tolerant ◽  
Control System Design ◽  
Actuator Faults ◽  
Flight Control System ◽  
Aircraft Control ◽  
Reconfigurable Control ◽  
Sensor Actuator ◽  
Control Reconfiguration

AbstractIn this paper an approach to fault-tolerant flight control system design based on the integration of sensor/actuator fault detection and isolation (FDI) and reconfigurable control is presented. The effects of the sensor and actuator faults in the innovation process of the Kalman filter are investigated, and a decision approach to isolate the sensor and actuator faults is proposed.The reconfigurable control algorithm based on the Extended Kalman Filter (EKF) is presented. The control reconfiguration procedure is executed by considering the identified control distribution matrix. In the simulations, the longitudinal dynamics of an aircraft control system are considered, and control reconfiguration is examined. In the paper, the principal block diagram of a fault tolerant aircraft control system is offered.

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