This paper describes an adaptive flight control system design for NASA's F-8 digital fly-by-wire research aircraft. 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.
Adaptive control laws for F-8 flight test
1977-10-01
Miscellaneous
No indication
English
Adaptive control laws for F-8 flight test
Tema Archive | 1977
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NTRS | 1977
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