Aeroelastic Analysis of Sandwich wing With Fractional Viscoelastic Core

Ebrahimi, Hossein | 2016

590 Viewed
  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 51099 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Haddadpour, Hassan
  7. Abstract:
  8. In this research, the effect of application of viscoelastic material with fractional derivatives pattern in aeroelastic stability analysis for a sandwich wing, has been examined. In order to study the wing’s aeroelastic behavior and the effect of inner layer on aeroelastic instability boundaries (fluttering), the wing is modeled as a cantilever sandwich beam with a fractional viscoelastic core. The Wagner approximation is used for applying the unstable aeroelastic loads. To obtain the characteristics and behaviors of the structure some assumptions including non-classical effects, are considered. These non-classical effects are the inner layer shear stress, the axial movements, the wing’s twisting and the layers warping. For deriving the mass matrix, stiffness matrix and damping matrix the separation of variables and Galerkin approaches are adopted. To validate the used method, samples of simply-supported and cantilever sandwich beams with different cross sections are analyzed by the written code. During free vibration analysis the natural frequencies and the mode shapes are achieved. There is a good agreement between obtained results and analytical solution results provided through pervious works. Finally, the effects of inner layer’s different parameters on wing’s aeroelastic stability are studied. This dissertation novelty is modeling and aeroelastic analyzing of a sandwich wing with fractional viscoelastic core
  9. Keywords:
  10. Flutter ; Aeroelasticity ; Viscoelasticity ; Sandwich Beam ; Fractional Derivative ; Aeroelastic Behavior

 Digital Object List