effects of nonlinear damping on post-flutter behavior using geometrically nonlinear reduced order modelingThe

The effects of this nonlinear damping mechanism on the post-flutter response is next analyzed on the Goland wing through time-marching of the aeroelastic equations comprising a rational fraction approximation of the linear aerodynamic forces. It is indeed found that the nonlinearity in the damping can stabilize the unstable aerodynamics and lead to finite amplitude limit cycle oscillations even when the stiffness related nonlinear geometric effects are neglected. The incorporation of these latter effects in the model is found to further decrease the amplitude of LCO even though the dominant bending motions do not seem to stiffen as the level of displacements is increased in static analyses.]]>autSong, PengchaothsMignolet, Marc PdgcChattopadhyay, AditidgcOswald, JaypblArizona State UniversityengPartial requirement for: M.S., Arizona State University, 2015Includes bibliographical references (pages 69-71)Field of study: Mechanical engineeringby Pengchao Songhttps://hdl.handle.net/2286/R.I.2975900Masters ThesisAcademic thesesxi, 71 pages : illustrations (some color)114331640021630348182153495adminIn CopyrightAll Rights Reserved2015TextMechanical EngineeringAerospace EngineeringGeometrically NonlinearLimit Cycle OscillationMechanical EngineeringReduced Order ModelStructural DynamicsFlutter (Aerodynamics)Damping (Mechanics)Nonlinear oscillationsStructural dynamics--Vibration.Structural Dynamics