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Advanced flight control system studyA fly by wire flight control system architecture designed for high reliability includes spare sensor and computer elements to permit safe dispatch with failed elements, thereby reducing unscheduled maintenance. A methodology capable of demonstrating that the architecture does achieve the predicted performance characteristics consists of a hierarchy of activities ranging from analytical calculations of system reliability and formal methods of software verification to iron bird testing followed by flight evaluation. Interfacing this architecture to the Lockheed S-3A aircraft for flight test is discussed. This testbed vehicle can be expanded to support flight experiments in advanced aerodynamics, electromechanical actuators, secondary power systems, flight management, new displays, and air traffic control concepts.
Document ID
19830004843
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hartmann, G. L.
(Lockheed-California Co. Burbank, CA, United States)
Wall, J. E., Jr.
(Lockheed-California Co. Burbank, CA, United States)
Rang, E. R.
(Lockheed-California Co. Burbank, CA, United States)
Lee, H. P.
(Lockheed-California Co. Burbank, CA, United States)
Schulte, R. W.
(Lockheed-California Co. Burbank, CA, United States)
Ng, W. K.
(Lockheed-California Co. Burbank, CA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1982
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.26:163117
HONEYWELL-82SRC5
NASA-CR-163117
Accession Number
83N13113
Funding Number(s)
PROJECT: RTOP 512-54-14
CONTRACT_GRANT: NAS4-2876
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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