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Design and flight experience with a digital fly-by-wire control system using Apollo guidance system hardware on an F-8 aircraft.This paper discusses the design and initial flight tests of the first digital fly-by-wire system to be flown in an aircraft. The system, which used components from the Apollo guidance system, was installed in an F-8 aircraft. A lunar module guidance computer is the central element in the three-axis, single-channel, multimode, digital, primary control system. An electrohydraulic triplex system providing unaugmented control of the F-8 aircraft is the only backup to the digital system. Emphasis is placed on the digital system in its role as a control augmentor, a logic processor, and a failure detector. A sampled-data design synthesis example is included to demonstrate the role of various analytical and simulation methods. The use of a digital system to implement conventional control laws was shown to be practical for flight. Logic functions coded as an integral part of the control laws were found to be advantageous. Verification of software required an extensive effort, but confidence in the software was achieved. Initial flight results showed highly successful system operation, although quantization of pilot's stick and trim were areas of minor concern from the piloting standpoint.
Document ID
19720056394
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Deets, D. A.
Szalai, K. J.
(NASA Flight Research Center Systems Analysis Branch, Edwards, Calif., United States)
Date Acquired
August 6, 2013
Publication Date
August 1, 1972
Subject Category
Aircraft
Report/Patent Number
AIAA PAPER 72-881
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Guidance and Control Conference
Location: Stanford, CA
Start Date: August 14, 1972
End Date: August 16, 1972
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
72A40060
Distribution Limits
Public
Copyright
Other

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