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

AbstractThe procedure of obtaining the two-degrees-of-freedom, 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 saddle-node 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
TypeConference paper [With referee]
ConferenceProceedings of the 41st SICE Annual Conference
Year2002    Vol. 2    pp. 695-700
PublisherSoc. Instrument & Control Eng. (SICE)
ISBN / ISSN0780376315
BibTeX data [bibtex]
IMM Group(s)Intelligent Signal Processing