Nonlinear dynamics approach of modeling the bifurcation for aircraft wing flutter in transonic speed 

Abstract  The procedure of obtaining the twodegreesoffreedom, finite dimensional. nonlinear mathematical model. which models the nonlinear features of aircraft flutter in transonic speed is reported. The model enables to explain every feature of the transonic flutter data of the wind tunnel tests conducted at National Aerospace Laboratory in Japan for a high aspect ratio wing. It explains the nonlinear features of the transonic flutter such as the subcritical Hopf bifurcation of a limit cycle oscillation (LCO), a saddlenode bifurcation, and an unstable limit cycle as well as a normal (linear) flutter condition with its linear pan. At a final procedure of improve a quantitative matching with the test data. the continuation method for analyzing the bifurcation is extensively used 
Type  Conference paper [With referee] 
Conference  Proceedings of the 41st SICE Annual Conference 
Year  2002 Vol. 2 pp. 695700 
Publisher  Soc. Instrument & Control Eng. (SICE) 
ISBN / ISSN  0780376315 
BibTeX data  [bibtex] 
IMM Group(s)  Intelligent Signal Processing 