DocumentCode
3496898
Title
Design of a nonlinear flight controller based on dynamic inversion
Author
Baba, Yoriaki ; Takano, Hiroyuki ; Sano, Masaki
Author_Institution
Dept. of Aerosp. Eng., Nat. Defense Acad., Yokosuka, Japan
fYear
1995
fDate
26-28 Jul 1995
Firstpage
1487
Lastpage
1492
Abstract
This paper deals with a synthesis for a nonlinear flight controller using a nonlinear state feedback. This method is called a dynamic inversion theory and is widely used to design a nonlinear flight controller. We show how to choose the control gains for the controller designed by a dynamic inversion theory when inversion is not exact due to the actuator lags
Keywords
aircraft control; control system synthesis; nonlinear control systems; state feedback; control gains; dynamic inversion; nonlinear flight controller design; nonlinear state feedback; Actuators; Aerodynamics; Aerospace engineering; Aircraft; Ear; Nonlinear equations; Proportional control; Robustness; State estimation; State feedback;
fLanguage
English
Publisher
ieee
Conference_Titel
SICE '95. Proceedings of the 34th SICE Annual Conference. International Session Papers
Conference_Location
Hokkaido
Print_ISBN
0-7803-2781-0
Type
conf
DOI
10.1109/SICE.1995.526734
Filename
526734
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