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On the Flutter of Swept Taper Wing in Subsonic Compressible Flow Considering Effect of Fuel Sloshing in External Stores

Beheshtinia, Farshad | 2014

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 45608 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Department
  6. Advisor(s): Dehghani Firoozabadi, R
  7. Abstract:
  8. In the present work, the aeroelastic stability analysis for the swept taper wing and external fuel tank combination system in subsonic compressible flow are represented. The wing structure is modeled by using the Euler-Bernoulli beam theory. Fuel sloshing is modeled by using an equivalent mechanical mass-spring-damper model. Modal analysis technique is used to drive the structural equations of motion of the system. Aeorodynamic of wing is modeled by using index aerodynamic that has been dived by Marzocca and a slender body aerodynamic theory for the external fuel tank are used. For stability analysis, k-method redrived for a case that structural damping there is. The effects of the external fuel tanks attachment stiffness, the span location of the fuel tank, the fuel tank attachment damping, the fuel tank aerodynamic and the fuel sloshing on the aeroelastic stability are discussed. It is found that the flutter boundary is sensitive to the fuel tank span location, the fuel tank attachment stiffness and the fuel tank attachment damping. The fuel tank aerodynamic has a destabilizing effect and the fuel sloshing has a stabilizing effect on the flutter boundary of the system
  9. Keywords:
  10. Fuel Sloshing ; Aeroelastic Instability ; Swept Taper Wing ; Subsonic Compressible Flow ; Fuel Sloshing in Enternal Stores

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