Please use this identifier to cite or link to this item: http://dlib.scu.ac.ir/handle/Hannan/183847
Title: Spacecraft fault-tolerant control using adaptive non-singular fast terminal sliding mode
Authors: Zhiguo Han;Ke Zhang;Tianshe Yang;Minghuan Zhang
subject: external disturbances|closed-loop system|saturation magnitude|spacecraft attitude tracking|inertia uncertainties|spacecraft fault-tolerant control|actuator output torque saturation amplitude requirements|Lyapunov stability analysis|finite-time convergence control strategies|finite-time fault-tolerant attitude tracking controller|actuator faults|adaptive parameters|adaptive nonsingular fast terminal sliding mode control law
Year: 2016
Publisher: IEEE
Abstract: Finite-time convergence control strategies based on adaptive non-singular fast terminal sliding mode are proposed for spacecraft attitude tracking subject to actuator faults, actuator saturations, external disturbances and inertia uncertainties. The designed non-singular fast terminal sliding mode control law can converge in a finite time and avoid singularity, hence it can be used to develop a finite-time fault-tolerant attitude tracking controller that meets multiple constraints. It is demonstrated that the controller is independent of inertia uncertainties and external disturbances with adaptive parameters. The controller designed considers the actuator output torque saturation amplitude requirements and makes the spacecraft accomplish certain operations within the saturation magnitude and without the need for on-line fault estimate. The Lyapunov stability analysis shows that the controller can guarantee the fast convergence of a closed-loop system and has a good fault-tolerant performance on actuator faults and saturations under the multiple constraints on actuator faults, actuator saturations, external disturbances and inertia uncertainties. Numerical simulation verified the good performance of the controller in the attitude tracking control.
URI: http://localhost/handle/Hannan/183847
ISSN: 1751-8644
1751-8652
volume: 10
issue: 16
More Information: 1991
1999
Appears in Collections:2016

Files in This Item:
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Title: Spacecraft fault-tolerant control using adaptive non-singular fast terminal sliding mode
Authors: Zhiguo Han;Ke Zhang;Tianshe Yang;Minghuan Zhang
subject: external disturbances|closed-loop system|saturation magnitude|spacecraft attitude tracking|inertia uncertainties|spacecraft fault-tolerant control|actuator output torque saturation amplitude requirements|Lyapunov stability analysis|finite-time convergence control strategies|finite-time fault-tolerant attitude tracking controller|actuator faults|adaptive parameters|adaptive nonsingular fast terminal sliding mode control law
Year: 2016
Publisher: IEEE
Abstract: Finite-time convergence control strategies based on adaptive non-singular fast terminal sliding mode are proposed for spacecraft attitude tracking subject to actuator faults, actuator saturations, external disturbances and inertia uncertainties. The designed non-singular fast terminal sliding mode control law can converge in a finite time and avoid singularity, hence it can be used to develop a finite-time fault-tolerant attitude tracking controller that meets multiple constraints. It is demonstrated that the controller is independent of inertia uncertainties and external disturbances with adaptive parameters. The controller designed considers the actuator output torque saturation amplitude requirements and makes the spacecraft accomplish certain operations within the saturation magnitude and without the need for on-line fault estimate. The Lyapunov stability analysis shows that the controller can guarantee the fast convergence of a closed-loop system and has a good fault-tolerant performance on actuator faults and saturations under the multiple constraints on actuator faults, actuator saturations, external disturbances and inertia uncertainties. Numerical simulation verified the good performance of the controller in the attitude tracking control.
URI: http://localhost/handle/Hannan/183847
ISSN: 1751-8644
1751-8652
volume: 10
issue: 16
More Information: 1991
1999
Appears in Collections:2016

Files in This Item:
File Description SizeFormat 
7725835.pdf1.7 MBAdobe PDFThumbnail
Preview File
Title: Spacecraft fault-tolerant control using adaptive non-singular fast terminal sliding mode
Authors: Zhiguo Han;Ke Zhang;Tianshe Yang;Minghuan Zhang
subject: external disturbances|closed-loop system|saturation magnitude|spacecraft attitude tracking|inertia uncertainties|spacecraft fault-tolerant control|actuator output torque saturation amplitude requirements|Lyapunov stability analysis|finite-time convergence control strategies|finite-time fault-tolerant attitude tracking controller|actuator faults|adaptive parameters|adaptive nonsingular fast terminal sliding mode control law
Year: 2016
Publisher: IEEE
Abstract: Finite-time convergence control strategies based on adaptive non-singular fast terminal sliding mode are proposed for spacecraft attitude tracking subject to actuator faults, actuator saturations, external disturbances and inertia uncertainties. The designed non-singular fast terminal sliding mode control law can converge in a finite time and avoid singularity, hence it can be used to develop a finite-time fault-tolerant attitude tracking controller that meets multiple constraints. It is demonstrated that the controller is independent of inertia uncertainties and external disturbances with adaptive parameters. The controller designed considers the actuator output torque saturation amplitude requirements and makes the spacecraft accomplish certain operations within the saturation magnitude and without the need for on-line fault estimate. The Lyapunov stability analysis shows that the controller can guarantee the fast convergence of a closed-loop system and has a good fault-tolerant performance on actuator faults and saturations under the multiple constraints on actuator faults, actuator saturations, external disturbances and inertia uncertainties. Numerical simulation verified the good performance of the controller in the attitude tracking control.
URI: http://localhost/handle/Hannan/183847
ISSN: 1751-8644
1751-8652
volume: 10
issue: 16
More Information: 1991
1999
Appears in Collections:2016

Files in This Item:
File Description SizeFormat 
7725835.pdf1.7 MBAdobe PDFThumbnail
Preview File