Study of Nonsingular Fast Terminal Sliding-Mode Fault-Tolerant Control

• Published in: IEEE transactions on industrial electronics (1982) Vol. 62; no. 6; pp. 3906 - 3913
• Main Authors: Xu, Sendren Sheng-Dong, Chih-Chiang Chen, Zheng-Lun Wu
• Format: Journal Article
• Language: English
• Published: New York IEEE 01.06.2015; The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
• Subjects: Actuators; Closed loop systems; Control systems; Convergence; Design engineering; Fault detection; Fault tolerance; Fault tolerant systems; fault-tolerant control (FTC); Mathematical analysis; nonlinear systems; nonsingular fast terminal sliding-mode control (NFTSMC); nonsingular terminal sliding-mode control (NTSMC); Robustness; Sliding mode control; sliding mode control (SMC); Space vehicles; Terminals; nonlinear systems; nonsingular terminal sliding-mode control (NTSMC); Fault detection; fault-tolerant control (FTC); sliding-mode control (SMC); nonsingular fast terminal sliding-mode control (NFTSMC)
• ISSN: 0278-0046; 1557-9948
• DOI: 10.1109/TIE.2015.2399397

This paper studies fault-tolerant control (FTC) designs based on nonsingular terminal sliding-mode control and nonsingular fast terminal sliding-mode control (NFTSMC). The proposed active FTC laws are shown to be able to achieve fault-tolerant objectives and maintain stabilization performance even when some of the actuators fail to operate. In comparison to existing sliding-mode control (SMC) fault-tolerant designs, the proposed schemes not only can retain the advantages of traditional SMC, including fast response, easy implementation, and robustness to disturbances/uncertainties, but also make the system states reach the control objective point in a finite amount of time. Moreover, they also resolve the potential singularity phenomena in traditional terminal and faster terminal SMC designs; meanwhile, the proposed NFTSMC fault-tolerant scheme also possesses the benefit of faster state convergence speed of NFTSMC. Finally, the proposed analytical results are also applied to the attitude control of a spacecraft. Simulation results demonstrate the benefits of the proposed schemes.