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Dual redundant sensor FDI techniques applied to the NASA F8C DFBW aircraftAn onboard failure detection and identification (FDI) technique for dual redundant sensors on the NASA F8C digital fly-by-wire (DFBW) aircraft is presented. The failure of one of a pair of sensors of the same type is detected by a direct redundancy trigger which observes the difference between the outputs of these two sensors. Identification of the failed sensor is accomplished utilizing the analytic redundancy that exists as kinematic and functional relationships among the variables being measured by dissimilar instruments. In addition, identification of generic failures, common to both instruments of a given type, is accomplished by using a time trigger to periodically initiate analytic redundancy failure identification tests for individual sensors. The basic form of these tests is the comparison of the measurement of a variable using the suspect instrument with another measurement of the same variable obtained using other instrument types.
Document ID
19760058516
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Desai, M. N.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Deckert, J. C.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Deyst, J. J.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Willsky, A. S.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Chow, E. Y.
(Charles Stark Draper Laboratory, Inc. Cambridge, Mass., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 76-1976
Meeting Information
Meeting: Guidance and Control Conference
Location: San Diego, CA
Start Date: August 16, 1976
End Date: August 18, 1976
Accession Number
76A41482
Funding Number(s)
CONTRACT_GRANT: NAS1-13914
Distribution Limits
Public
Copyright
Other

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