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Ground and flight test experience with a triple redundant digital fly by wire control systemA triplex digital fly by wire flight control system was developed and installed in an F-8C aircraft to provide fail operative, full authority control. Hardware and software redundancy management techniques were designed to detect and identify failures in the system. Control functions typical of those projected for future actively controlled vehicles were implemented.
Document ID
19810010480
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jarvis, C. R. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Szalai, K. J. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 11, 2013
Publication Date
February 1, 1981
Publication Information
Publication: NASA. Langley Research Center Advan. Aerodyn. and Active Controls
Subject Category
Aircraft Stability And Control
Accession Number
81N19006
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19810010475Collected WorksAdvanced aerodynamics and active controls. Selected NASA research
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