A fault-tolerant control design against major actuator failures: application to a three-tank system

Author(s):  
V. Dardinier-Maron ◽  
F. Hamelin ◽  
H. Noura
2000 ◽  
Vol 31 (9) ◽  
pp. 1143-1155 ◽  
Author(s):  
Hassan Noura ◽  
Didier Theilliol ◽  
Dominique Sauter

Author(s):  
Didier Theilliol ◽  
Cédric Join ◽  
Youmin Zhang

Actuator Fault Tolerant Control Design Based on a Reconfigurable Reference InputThe prospective work reported in this paper explores a new approach to enhance the performance of an active fault tolerant control system. The proposed technique is based on a modified recovery/trajectory control system in which a reconfigurable reference input is considered when performance degradation occurs in the system due to faults in actuator dynamics. An added value of this work is to reduce the energy spent to achieve the desired closed-loop performance. This work is justified by the need of maintaining a reliable system in a dynamical way in order to achieve a mission by an autonomous system, e.g., a launcher, a satellite, a submarine, etc. The effectiveness is illustrated using a three-tank system for slowly varying reference inputs corrupted by actuators faults.


Sensors ◽  
2019 ◽  
Vol 19 (3) ◽  
pp. 643 ◽  
Author(s):  
Juan Tan ◽  
Yonghua Fan ◽  
Pengpeng Yan ◽  
Chun Wang ◽  
Hao Feng

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.


2014 ◽  
Vol 24 (14) ◽  
pp. 1969-1988 ◽  
Author(s):  
Saúl Montes de Oca ◽  
Sebastian Tornil-Sin ◽  
Vicenç Puig ◽  
Didier Theilliol

2020 ◽  
Vol 50 (9) ◽  
pp. 3401-3411 ◽  
Author(s):  
Alireza Abbaspour ◽  
Kang K. Yen ◽  
Parisa Forouzannezhad ◽  
Arman Sargolzaei

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