Aircraft actuator fault detection and isolation using piecewise constant fault estimation scheme

Hanmin Lee, Steven Snyder, Andrew Patterson, Naira Hovakimyan

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper presents a model-based method for fault detection and isolation of actuator damage and failure on an aircraft. The proposed method is based on multiple linearized models that approximate the nonlinear dynamics of the aircraft and allow for uncertainty. In this paper, linearized actuator fault models are introduced and a Luenberger observer is modified with a piecewise constant update law for robust fault estimation. For the purposes of identifying actuator faults, a fault identification algorithm is suggested using the estimated fault information from the observer. Simulation results demonstrate the performance of the proposed method in models of a transport class aircraft.

Original languageEnglish (US)
Title of host publicationAIAA Guidance, Navigation, and Control Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103896
DOIs
StatePublished - Jan 1 2016
EventAIAA Guidance, Navigation, and Control Conference, 2016 - San Diego, United States
Duration: Jan 4 2016Jan 8 2016

Publication series

Name2016 AIAA Guidance, Navigation, and Control Conference

Other

OtherAIAA Guidance, Navigation, and Control Conference, 2016
CountryUnited States
CitySan Diego
Period1/4/161/8/16

ASJC Scopus subject areas

  • Aerospace Engineering
  • Electrical and Electronic Engineering
  • Control and Systems Engineering

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  • Cite this

    Lee, H., Snyder, S., Patterson, A., & Hovakimyan, N. (2016). Aircraft actuator fault detection and isolation using piecewise constant fault estimation scheme. In AIAA Guidance, Navigation, and Control Conference (2016 AIAA Guidance, Navigation, and Control Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2016-0373