NASA NTRS · 19770015867
Adaptive control laws for F-8 flight tests
Abstract
An 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.
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Stein, G., Hartmann, G. L., Hendrick, R. C.. 1975-01-01. Adaptive control laws for F-8 flight tests. https://ntrs.nasa.gov/citations/19770015867
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