Experimental Investigation of Passive Fault Tolerant Control for Induction Machine Using Sliding Mode Approach

2018 ◽  
Vol 21 (1) ◽  
pp. 520-532 ◽  
Author(s):  
Amal Guezmil ◽  
Hanen Berriri ◽  
Remus Pusca ◽  
Anis Sakly ◽  
Raphael Romary ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Induction Machine ◽  
Fault Tolerant Control

Fault-Tolerant Control Based on Sliding Mode Controller for Double-Star Induction Machine

2019 ◽  
Vol 45 (3) ◽  
pp. 1615-1627
Author(s):  
Noureddine Layadi ◽  
Ali Djerioui ◽  
Samir Zeghlache ◽  
Hemza Mekki ◽  
Azeddine Houari ◽  
...  
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
Induction Machine ◽  
Fault Tolerant Control ◽  
Double Star ◽  
Sliding Mode Controller

Sliding Mode-Based Active Fault-Tolerant Control for Induction Machine

2019 ◽  
Vol 45 (3) ◽  
pp. 1447-1455
Author(s):  
Amal Guezmil ◽  
Hanen Berriri ◽  
Anis Sakly ◽  
Mohamed Faouzi Mimouni
Keyword(s):  
Active Fault ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Induction Machine ◽  
Fault Tolerant Control ◽  
Active Fault Tolerant Control

scholarly journals Fault-tolerant control for a class of n-order systems based on fast terminal sliding mode and extended state observer

2021 ◽  
pp. 002029402110286
Author(s):  
Pu Yang ◽  
Peng Liu ◽  
ChenWan Wen ◽  
Huilin Geng
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
Singular Control ◽  
Fault Tolerant Control ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Terminal Sliding Mode ◽  
Fast Terminal Sliding Mode ◽  
Terminal Sliding Surface

This paper focuses on fast terminal sliding mode fault-tolerant control for a class of n-order nonlinear systems. Firstly, when the actuator fault occurs, the extended state observer (ESO) is used to estimate the lumped uncertainty and its derivative of the system, so that the fault boundary is not needed to know. The convergence of ESO is proved theoretically. Secondly, a new type of fast terminal sliding surface is designed to achieve global fast convergence, non-singular control law and chattering reduction, and the Lyapunov stability criterion is used to prove that the system states converge to the origin of the sliding mode surface in finite time, which ensures the stability of the closed-loop system. Finally, the effectiveness and superiority of the proposed algorithm are verified by two simulation experiments of different order systems.

scholarly journals Sliding Mode Fault Tolerant Control for Unmanned Aerial Vehicle with Sensor and Actuator Faults

Sensors ◽  
2019 ◽  
Vol 19 (3) ◽  
pp. 643 ◽  
Author(s):  
Juan Tan ◽  
Yonghua Fan ◽  
Pengpeng Yan ◽  
Chun Wang ◽  
Hao Feng
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Health Management ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Control Process ◽  
Fault Tolerant Control ◽  
Accelerometer Sensor ◽  
Actuator Failures ◽  
Aerial Vehicle ◽  
Gyroscope Sensor

The unmanned aerial vehicle (UAV) has been developing rapidly recently, and the safety and the reliability of the UAV are significant to the mission execution and the life of UAV. Sensor and actuator failures of a UAV are one of the most common malfunctions, threating the safety and life of the UAV. Fault-tolerant control technology is an effective method to improve the reliability and safety of UAV, which also contributes to vehicle health management (VHM). This paper deals with the sliding mode fault-tolerant control of the UAV, considering the failures of sensor and actuator. Firstly, a terminal sliding surface is designed to ensure the state of the system on the sliding mode surface throughout the control process based on the simplified coupling dynamic model. Then, the sliding mode control (SMC) method combined with the RBF neural network algorithm is used to design the parameters of the sliding mode controller, and with this, the efficiency of the design process is improved and system chattering is minimized. Finally, the Simulink simulations are carried out using a fault tolerance controller under the conditions where accelerometer sensor, gyroscope sensor or actuator failures is assumed. The results show that the proposed control strategy is quite an effective method for the control of UAVs with accelerometer sensor, gyroscope sensor or actuator failures.

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