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

Hanmin Lee; Steven Snyder; Andrew Patterson; Naira Hovakimyan

doi:10.2514/6.2016-0373

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 proceeding › Conference 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 language	English (US)
Title of host publication	AIAA Guidance, Navigation, and Control Conference
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624103896
DOIs	https://doi.org/10.2514/6.2016-0373
State	Published - Jan 1 2016
Event	AIAA Guidance, Navigation, and Control Conference, 2016 - San Diego, United States Duration: Jan 4 2016 → Jan 8 2016

Publication series

Name	2016 AIAA Guidance, Navigation, and Control Conference

Other

Other	AIAA Guidance, Navigation, and Control Conference, 2016
Country	United States
City	San Diego
Period	1/4/16 → 1/8/16

ASJC Scopus subject areas

Aerospace Engineering
Electrical and Electronic Engineering
Control and Systems Engineering

Access to Document

10.2514/6.2016-0373

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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

Aircraft actuator fault detection and isolation using piecewise constant fault estimation scheme. / Lee, Hanmin; Snyder, Steven; Patterson, Andrew; Hovakimyan, Naira.

AIAA Guidance, Navigation, and Control Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (2016 AIAA Guidance, Navigation, and Control Conference).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

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, AIAA Guidance, Navigation, and Control Conference, 2016, San Diego, United States, 1/4/16. https://doi.org/10.2514/6.2016-0373

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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.",

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AB - 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.

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