Decoupling of the longitudinal modes of advanced aircraft

 
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1996 (EN)
Decoupling of the longitudinal modes of advanced aircraft (EN)

Koumboulis, FN (EN)
Skarpetis, MG (EN)

N/A (EN)

In this study, the pitch and flight-path angle of a multimode aircraft have been independently controlled, via static state feedback, using the input-output decoupling with simultaneous arbitrary pole assignment technique. The satisfactory closed-loop performance is illustrated by simulation for an AFTI F-16 aircraft. However, the present technique basically differs from that of eigenstructure assignment on the starting point. Based on this difference several results have been obtained which enabled the desirable damping and settling time to be achieved. (EN)

journalArticle

Damping (EN)
Nonlinear equations (EN)
Computer simulation (EN)
Flight path angle (EN)
Advanced aircraft (EN)
Transfer functions (EN)
Longitudinal modes (EN)
Feedback control (EN)
Flight dynamics (EN)
Mechanical variables control (EN)
Decoupling (EN)
Mathematical models (EN)
Eigenstructure assignment (EN)
Closed loop control systems (EN)
Control theory (EN)
Aircraft (EN)

Εθνικό Μετσόβιο Πολυτεχνείο (EL)
National Technical University of Athens (EN)

Journal of Guidance, Control, and Dynamics (EN)

1996


AIAA, Washington, DC, United States (EN)



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