Fault tolerant attitude controller for a class of additive faults via High-Order Sliding Modes

J. Dávila; J. Cieslak; D. Henry

doi:10.1016/j.ifacol.2016.07.122

Fault tolerant attitude controller for a class of additive faults via High-Order Sliding Modes

J. Dávila, J. Cieslak, D. Henry

Research output: Contribution to journal › Article › peer-review

Abstract

In this paper, an autopilot for attitude tracking is designed using disturbance compensation techniques. The proposed controller uses backstepping design procedure and combines the feedback linearization technique with high-order sliding-modes based identification for fault tolerant control. System faults and external disturbances are compensated by a differentiable term generated by means of the robust exact high-order sliding-modes differentiator. The control signal generated for the controller does not require filtration. Simulations illustrate the performance of the proposed controller in the rigid body model of an F-16 aircraft.

Original language	English
Pages (from-to)	254-259
Number of pages	6
Journal	IFAC-PapersOnLine
Volume	49
Issue number	5
DOIs	https://doi.org/10.1016/j.ifacol.2016.07.122
State	Published - 2016
Externally published	Yes

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10.1016/j.ifacol.2016.07.122

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abstract = "In this paper, an autopilot for attitude tracking is designed using disturbance compensation techniques. The proposed controller uses backstepping design procedure and combines the feedback linearization technique with high-order sliding-modes based identification for fault tolerant control. System faults and external disturbances are compensated by a differentiable term generated by means of the robust exact high-order sliding-modes differentiator. The control signal generated for the controller does not require filtration. Simulations illustrate the performance of the proposed controller in the rigid body model of an F-16 aircraft.",

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AB - In this paper, an autopilot for attitude tracking is designed using disturbance compensation techniques. The proposed controller uses backstepping design procedure and combines the feedback linearization technique with high-order sliding-modes based identification for fault tolerant control. System faults and external disturbances are compensated by a differentiable term generated by means of the robust exact high-order sliding-modes differentiator. The control signal generated for the controller does not require filtration. Simulations illustrate the performance of the proposed controller in the rigid body model of an F-16 aircraft.

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Fault tolerant attitude controller for a class of additive faults via High-Order Sliding Modes

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