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Aeroelastic Analysis of Aircraft Composite Wings in a Compressible Flow

Farsadi, Touraj | 2010

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 40437 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): haddadpour, Hassan
  7. Abstract:
  8. In this research, an anistropic thin-walled beam composite is used to consider the effects of fiber orientation and lay-up configuration on the aeroelastic stability and response of an aircraft wing. The circum ferentially asymmetric stiffness (CAS) model consists of a group of non-classical effects; such as transverse shear, material anisotropic, warping inhibition, etc. The aerodynamic load has been modeled based on the strip theory and compressible unsteady flow in the finite- state form. In addition, to form the mass, stiffness and damping matrices of non-conservative aeroelastic systems the extended Galerkin’s method (EGM) and the method of separation of variables has been used. After that by transferring matrices into the form of finite state, eigenvalue analysis has been accomplished. Therefore by solving the coupled linear system of equations, flutter and divergence speed for various laminate configurations and material properties was achieved. Then, by having equations of motion and solving them in the time domain, the aeroelastic response of the wing for different flight regimes has been obtained. At the end, some important consequences compared with existing results are presented
  9. Keywords:
  10. Thin Walled Beam ; Composite Materials ; Compressible Flow ; Incompressible Flow ; Unsteady Aerodynamic ; Aeroelasticity

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