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Digital adaptive control laws for the F-8NASA is conducting a flight control research program in digital fly-by-wire technology using a modified F-8C aircraft. The first phase of this program used Apollo hardware to demonstrate the practicality of digital fly-by-wire in an actual test vehicle. For the second phase, conventional aircraft sensors and a large floating point digital computer are being utilized to test advanced control laws and redundancy concepts. As part of NASA's research in digital fly-by-wire technology, Honeywell developed digital adaptive flight control laws for flight test in the F-8C. Adaptation of the control laws was to be based on information sensed from conventional aircraft sensors excluding air data. The control laws were constrained to use only existing elevator, rudder, and ailerons as control effectors, each powered by existing actuators. Three adaptive control laws were successfully designed using maximum likelihood estimation, a Liapunov stable model tracker and a self-excited limit cycle concept. The maximum likelihood estimation design was selected as the most promising because of its capability to identify more than surface effectiveness parameters. The adaptive concepts, the control laws and comparisons of predicted performance are described.
Document ID
19760058497
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Hartmann, G. L.
(Honeywell, Inc. Minneapolis, MN, United States)
Harvey, C. A.
(Honeywell, Inc. Minneapolis, Minn., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 76-1952
Meeting Information
Meeting: Guidance and Control Conference
Location: San Diego, CA
Start Date: August 16, 1976
End Date: August 18, 1976
Accession Number
76A41463
Funding Number(s)
CONTRACT_GRANT: NAS1-13383
Distribution Limits
Public
Copyright
Other

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