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.

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 Fault Diagnosis and Fault-Tolerant Control Scheme for Quadcopter UAVs with a Total Loss of Actuator

Energies ◽  
2019 ◽  
Vol 12 (6) ◽  
pp. 1139 ◽  
Author(s):  
Ngoc Nguyen ◽  
Sung Hong
Keyword(s):  
Fault Diagnosis ◽  
Active Fault ◽  
Control Method ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Fault Tolerant Control ◽  
Total Loss ◽  
Actuator Faults ◽  
Control Scheme ◽  
Robust Adaptive

Fault-tolerant control has drawn attention in recent years owning to its reliability and safe flight during missions. In this article, an active fault-tolerant control method is proposed to control a quadcopter in the presence of actuator faults and disturbances. Firstly, the dynamics of the quadcopter are presented. Secondly, a robust adaptive sliding mode Thau observer is presented to estimate the time-varying magnitudes of actuator faults. Thirdly, a fault-tolerant control scheme based on sliding mode control and reconfiguration technique is designed to maintain the quadcopter at the desired position despite the presence of faults. Unlike previous studies, the proposed method aims to integrate the fault diagnosis and a fault-tolerant control scheme into a single unit with total loss of actuator. Simulation results illustrate the efficiency of the suggested algorithm.

scholarly journals Fault-tolerant Control of Quadcopter UAVs Using Robust Adaptive Sliding Mode Approach

Energies ◽  
2018 ◽  
Vol 12 (1) ◽  
pp. 95 ◽  
Author(s):  
Ngoc Phi Nguyen ◽  
Sung Kyung Hong
Keyword(s):  
Control Method ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Fault Tolerant Control ◽  
Lyapunov Theory ◽  
Adaptive Sliding Mode Control ◽  
Actuator Faults ◽  
Adaptive Sliding Mode ◽  
System Uncertainties ◽  
Robust Adaptive

In this paper, a fault-tolerant control method is proposed for quadcopter unmanned aerial vehicles (UAV) to account for system uncertainties and actuator faults. A mathematical model of the quadcopter UAV is first introduced when faults occur in actuators. A normal adaptive sliding mode control (NASMC) approach is proposed as a baseline controller to handle the chattering problem and system uncertainties, which does not require information of the upper bound. To improve the performance of the NASMC scheme, radial basis function neural networks are combined with an adaptive scheme to make a quick compensation in presence of system uncertainties and actuator faults. The Lyapunov theory is applied to verify the stability of the proposed methods. The effectiveness of modified ASMC algorithm is compared with that of NASMC using numerical examples under different faulty conditions.

scholarly journals A new fault diagnosis and fault-tolerant control method for mechanical and aeronautical systems with neural estimators

2019 ◽  
Vol 11 (11) ◽  
pp. 168781401989165 ◽  
Author(s):  
Haiying Qi ◽  
Yiran Shi ◽  
Yantao Tian ◽  
Clifford Mayhew ◽  
Ding-Li Yu ◽  
...  
Keyword(s):  
Control Method ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Design Procedure ◽  
Fault Tolerant Control ◽  
System Stability ◽  
Time Varying ◽  
Neural Network Learning ◽  
Control Loops ◽  
The Impact

A new method of fault detection and fault-tolerant control is proposed in this article for mechanical systems and aeronautical systems. The faults to be estimated and diagnosed are malfunctions that occurred within the control loops of the systems, rather than some static faults, such as gearbox fault, component cracks, and so on. In the proposed method, two neural networks are used as online estimators, the fault will be accurately estimated when the estimators are adapted online with the post-fault dynamic information. Furthermore, the estimated values of faults are used to compensate for the impact of the faults, so that the stability and performance of the system with the faults are maintained until the faulty components to be repaired. The sliding mode control is used to maintain system stability under the post-fault dynamics. The control law and the neural network learning algorithms are derived using the Lyapunov method, so that the neural estimators are guaranteed to converge to the fault to be diagnosed, while the entire closed-loop system stability is guaranteed with all variables bounded. The main contribution of this article to the knowledge in this field is that the proposed method can not only diagnose and tolerant with constant fault but also diagnose and tolerant with the time-varying faults. This is very important because most faults occurred in industrial systems are time varying in nature. A simulation example is used to demonstrate the design procedure and the effectiveness of the method. The simulation results are compared with the two existing methods that can cope with constant faults only, and the superiority is demonstrated.

Fault-tolerant control of hypersonic vehicles based on fast fault observer under actuator gain loss fault or stuck fault

2020 ◽  
Vol 124 (1278) ◽  
pp. 1190-1207
Author(s):  
P. Zhu ◽  
J. Jiang ◽  
C. Yu
Keyword(s):  
Simulation Experiment ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Input Saturation ◽  
Fault Tolerant Control ◽  
Fault Estimation ◽  
Hypersonic Vehicles ◽  
Control Input ◽  
Actuator Faults ◽  
Gain Loss

ABSTRACTThis paper proposes a fault-tolerant control (FTC) method based on fast fault observer (FFO) to solve the problem of actuator gain loss fault and stuck fault for hypersonic vehicles. Firstly, an input-output feedback linearisation model is presented that considers parametric uncertainties, control input saturation, disturbances and actuator faults. Secondly, the above factors are defined as an integrated fault item, and an improved fast fault observer is designed to estimate the integrated fault in real time. Finally, the fault-tolerant controller is constructed based on the sliding mode and fault estimation. In case of unknown faults, the effects of gain loss fault or stuck fault happen on elevators and the engine can be quickly processed, Also, the asymptotically stable tracking of the flight output reference command is completed to achieve fault-tolerant control. The final simulation experiment verifies the effectiveness of the proposed method.

scholarly journals Hybrid Robust H2/H∞ Fault-Tolerant Control with Random Delay NCS

2020 ◽  
Vol 2020 ◽  
pp. 1-13
Author(s):  
Jun Wang ◽  
Miaomiao Ling
Keyword(s):  
Closed Loop ◽  
Control Method ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Finite Energy ◽  
Actuator Faults ◽  
Matlab Simulation ◽  
Random Delay ◽  
The Impact ◽  
Line Design

In this paper, a hybrid fault-tolerant control method with off-line design and online scheduling is proposed for NCS with actuator faults, random delay, and external finite energy disturbance. The problem of less conservatism of robust generalized H2/H∞ hybrid fault-tolerant control is studied. Firstly, a closed-loop fault model of the system with random delay parameters was established according to the Bernoulli 0-1 distribution; all possible prior faults are divided into a few intervals according to certain rules, and then an interval fault-tolerant controller is designed off-line according to the prior faults of each interval. Secondly, when the fault is estimated online, the corresponding interval fault-tolerant controller is called through the scheduling mechanism to achieve rapid fault tolerance of prior faults within the interval and mitigate the impact of other faults within the interval, which provides a guarantee for subsequent safe reconstruction control. Finally, the effectiveness of the proposed method is verified by Matlab simulation.

scholarly journals Actuator Fault Detection and Fault-Tolerant Control for Hexacopter

Sensors ◽  
2019 ◽  
Vol 19 (21) ◽  
pp. 4721 ◽  
Author(s):  
Nguyen ◽  
Mung ◽  
Hong
Keyword(s):  
Fault Detection ◽  
Control Method ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Detection System ◽  
Control Strategies ◽  
Fault Tolerant Control ◽  
Actuator Faults ◽  
Actuator Failures ◽  
The One

In this paper, fault detection and fault-tolerant control strategies are proposed to handle the issues of both actuator faults and disturbances in a hexacopter. A dynamic model of a hexacopter is first derived to develop a model-based fault detection system. Secondly, the altitude control based on a sliding mode and disturbance observer is presented to tackle the disturbance issue. Then, a nonlinear Thau observer is applied to estimate the states of a hexacopter and to generate the residuals. Using a fault detection unit, the motor failure is isolated to address the one or two actuator faults. Finally, experimental results are tested on a DJI F550 hexacopter platform and Pixhawk2 flight controller to verify the effectiveness of the proposed approach. Unlike previous studies, this work can integrate fault detection and fault-tolerant control design as a single unit. Moreover, the developed fault detection and fault-tolerant control method can handle up to two actuator failures in presence of disturbances.

scholarly journals Adaptive Finite-Time Control for a Flexible Hypersonic Vehicle with Actuator Fault

2013 ◽  
Vol 2013 ◽  
pp. 1-10 ◽  
Author(s):  
Jie Wang ◽  
Qun Zong ◽  
Xiao He ◽  
Hamid Reza Karimi
Keyword(s):  
Control Strategy ◽  
Finite Time ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Hypersonic Vehicle ◽  
Actuator Faults ◽  
Partial Loss ◽  
Time Control ◽  
Mode Method ◽  
Loss Of Actuator Effectiveness

The problem of robust fault-tolerant tracking control is investigated. Simulation on the longitudinal model of a flexible air-breathing hypersonic vehicle (FAHV) with actuator faults and uncertainties is conducted. In order to guarantee that the velocity and altitude track their desired commands in finite time with the partial loss of actuator effectiveness, an adaptive fault-tolerant control strategy is presented based on practical finite-time sliding mode method. The adaptive update laws are used to estimate the upper bound of uncertainties and the minimum value of actuator efficiency factor. Finally, simulation results show that the proposed control strategy is effective in rejecting uncertainties even in the presence of actuator faults.

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