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Adaptive control laws for F-8 flight testsAn adaptive flight-control-system design for NASA's F-8 Digital Fly-by-Wire research aircraft is described. This design implements an explicit parallel maximum likelihood identification algorithm to estimate key aircraft parameters. The estimates are used to compute gains in simplified quadratic-optimal command augmentation control laws. Design details for the control laws and identifier are presented, and performance evaluation results from NASA Langley's F-8 simulator are summarized.
Document ID
19770015867
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stein, G. (Honeywell, Inc. Minneapolis, MN, United States)
Hartmann, G. L. (Honeywell, Inc. Minneapolis, MN, United States)
Hendrick, R. C. (Honeywell, Inc. Minneapolis, MN, United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Publication Information
Publication: NASA. Ames Res. Center Systems Reliability Issues for Future Aircraft
Subject Category
Aircraft Stability And Control
Accession Number
77N22811
Funding Number(s)
CONTRACT_GRANT: NAS1-12680
CONTRACT_GRANT: NAS1-13383
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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