DocumentCode
416859
Title
Nonlinear mathematical modeling of aircraft transonic flutter and its closed loop bifurcation characteristics
Author
Miyata, Takafumi ; Matsushita, Hiroshi
Author_Institution
Fukui Univ., Japan
Volume
3
fYear
2003
fDate
4-6 Aug. 2003
Firstpage
3335
Abstract
The authors have developed a nonlinear mathematical model, by the nonlinear dynamics approach, which can explain qualitatively the fundamental bifurcation phenomena observed in the series of wind tunnel tests. The linear control law was designed, and it was shown that bifurcation diagram analysis was able to be made also in the nonlinear closed loop system.
Keywords
aircraft control; bifurcation; closed loop systems; mathematical analysis; nonlinear control systems; nonlinear dynamical systems; aircraft transonic flutter; bifurcation diagram analysis; closed loop bifurcation characteristics; fundamental bifurcation phenomena; linear control law; nonlinear closed loop system; nonlinear dynamics; nonlinear mathematical modeling; wind tunnel tests;
fLanguage
English
Publisher
ieee
Conference_Titel
SICE 2003 Annual Conference
Conference_Location
Fukui, Japan
Print_ISBN
0-7803-8352-4
Type
conf
Filename
1323924
Link To Document