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A Fault Tolerant Direct Control Allocation Scheme with Integral Sliding Modes

  • Mirza Tariq HamayunEmail author
  • Christopher Edwards
  • Halim Alwi
Chapter
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Part of the Studies in Systems, Decision and Control book series (SSDC, volume 61)

Abstract

The FTC scheme described in this chapter looks at the possibility of introducing fault tolerance without having information about actuator effectiveness levels . Here the idea of direct control allocation is incorporated within the ISM/FTC framework. Achieving performance close to the nominal and maintaining overall closed-loop stability in the face of actuator faults/failures and in the presence of aerodynamic disturbances  (i.e. wind gusts) and sensor noise is the main objective. An LMI based procedure is described to synthesise the controller parameters, and a rigorous closed-loop stability analysis is carried out in the presence of unmatched uncertainty for a suitable set of actuator faults/failures . The FTC scheme is compared in simulation with the one from Chap.  3 by considering the same manoeuvre on the RECOVER benchmark model in the presence of wind gusts and sensor noise.

Keywords

Feedback Gain Sensor Noise Full Column Rank Virtual Control Control Allocation 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

References

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    Edwards, C., Lombaerts, T., Smaili, H.: Fault Tolerant Flight Control: A Benchmark Challenge, vol. 399. Springer, Berlin (2010)Google Scholar
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    Alwi, H., Edwards, C., Stroosma, O., Mulder, J.A.: Evaluation of a sliding mode fault-tolerant controller for the EL AL incident. AIAA J. Guid. Control Dyn. 33(3), 677–694 (2010)CrossRefGoogle Scholar
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    Shtessel, Y., Buffington, J., Banda, S.: Tailless aircraft flight control using multiple time scale re-configurable sliding modes. IEEE Trans. Control Syst. Technol. 10, 288–296 (2002)CrossRefGoogle Scholar
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    Wells, S.R., Hess, R.A.: Multi-input/multi-output sliding mode control for a tailless fighter aircraft. J. Guid. Control Dyn. 26(3), 463–473 (2003)CrossRefGoogle Scholar

Copyright information

© Springer International Publishing Switzerland 2016

Authors and Affiliations

  • Mirza Tariq Hamayun
    • 1
    Email author
  • Christopher Edwards
    • 2
  • Halim Alwi
    • 2
  1. 1.Department of Electrical EngineeringCOMSATS Institute of Information TechnologyLahorePakistan
  2. 2.College of Engineering Mathematics and Physical SciencesUniversity of ExeterExeterUK

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