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A reliable dual-redundant sensor FDI system for the NASA F8C-DFBW aircraftIn this paper we outline the structure of a sensor failure detection and identification (FDI) system designed for the NASA F8C DFBW aircraft. The system is for use in a dual-redundant environment, and it takes maximal advantage of all functional and kinematic relationships among the sensed variables. The technique is reliable in that we have designed the system to account for a variety of unmodeled effects and have introduced a new concept - the quality sequential probability ratio (QSPR) - that provides a useful measure of our confidence in each test. The methodology used for determining detector parameters and the 'outer loop logic' for combining the various sources of information are described.
Document ID
19770045955
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Deckert, J. C.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Desai, M. N.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Deyst, J. J., Jr.
(Charles Stark Draper Laboratory, Inc. Cambridge, Mass., United States)
Willsky, A. S.
(MIT Cambridge, Mass., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aircraft Stability And Control
Meeting Information
Meeting: Conference on Decision and Control
Location: Clearwater, FL
Country: US
Start Date: December 1, 1976
End Date: December 3, 1976
Accession Number
77A28807
Funding Number(s)
CONTRACT_GRANT: NAS1-13914
Distribution Limits
Public
Copyright
Other

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