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application of a bank of kalman filters for aircraft engine fault diagnosticsIn this paper, a bank of Kalman filters is applied to aircraft gas turbine engine sensor and actuator fault detection and isolation (FDI) in conjunction with the detection of component faults. This approach uses multiple Kalman filters, each of which is designed for detecting a specific sensor or actuator fault. In the event that a fault does occur, all filters except the one using the correct hypothesis will produce large estimation errors, thereby isolating the specific fault. In the meantime, a set of parameters that indicate engine component performance is estimated for the detection of abrupt degradation. The proposed FDI approach is applied to a nonlinear engine simulation at nominal and aged conditions, and the evaluation results for various engine faults at cruise operating conditions are given. The ability of the proposed approach to reliably detect and isolate sensor and actuator faults is demonstrated.
Document ID
Document Type
Technical Memorandum (TM)
Kobayashi, Takahisa
(QSS Group, Inc. Cleveland, OH, United States)
Simon, Donald L.
(Army Research Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2003
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NAS 1.15:212526
Meeting Information
Turbo Expo 2003(Atlanta, GA)
Funding Number(s)
PROJECT: DA Proj. 1L1-61102-AF-20
WBS: WBS 22-728-30-20
Distribution Limits
Work of the US Gov. Public Use Permitted.

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NameType 20030067984.pdf STI