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Fault-tolerant control for commercial aircraft with actuator faults and constraints

Research output: Contribution to journalArticle

Original languageEnglish
Pages (from-to)3849-3868
Number of pages20
JournalJournal of the Franklin Institute
Volume356
Issue number7
Early online date5 Mar 2019
DOIs
DateAccepted/In press - 3 Nov 2018
DateE-pub ahead of print - 5 Mar 2019
DatePublished (current) - 1 May 2019

Abstract

In this paper, a constrained control scheme based on model reference adaptive control is investigated for the longitudinal motion of a commercial aircraft with actuator faults and saturation nonlinearities. Actuator faults and constraints are both important factors adversely affecting the stability and performance of flight control systems. An adaptive adjustment law based on Lyapunov function is utilized to adjust the fault-tolerant control law. Both additive and multiplicative faults are considered in the designed controller to deal with the three types of actuator faults: locked in place, loss of effectiveness, and bias. Moreover, different techniques are implemented in the basic and fault-tolerant controller to anti-windup. Proofs for the stability of the two modified controllers which improve the performance of control system operating in the presence of actuator faults and saturations are proposed. Finally, a numerical example of the anti-windup fault-tolerant controller for a commercial aircraft is demonstrated. The stability and performance improvements can be accrued with the presented fault-tolerant control scheme.

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  • Full-text PDF (accepted author manuscript)

    Rights statement: This is the author accepted manuscript (AAM). The final published version (version of record) is available online via Elsevier at https://www.sciencedirect.com/science/article/pii/S001600321930184X?via%3Dihub. Please refer to any applicable terms of use of the publisher.

    Accepted author manuscript, 654 KB, PDF document

    Embargo ends: 5/03/20

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    Licence: CC BY-NC-ND

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