Recent studies of the occurrence of post-flutter limit cycle oscillations (LCO) of the F-16 have provided good support to the long-standing hypothesis that this phenomenon involves a nonlinear structural damping. A potential mechanism for the appearance of nonlinearity in the damping are the nonlinear geometric effects that arise when the deformations become large enough to exceed the linear regime.
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- Partial requirement for: M.S., Arizona State University, 2015Note typethesis
- Includes bibliographical references (pages 69-71)Note typebibliography
- Field of study: Mechanical engineering