A FEM-BEM Model for Investigation of Fuel SlushingEffect on the Supersonic Wing Aeroelasticity

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Zanjanizadeh Esfahani, Mohammad Javad | 2013

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 45077 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Haddadpour, Hassan
Abstract:
In the present work the stability analysis for the coupled aeroelasticity and fuel sloshing in supersonic wings is represented. The wing and store structure is modeled using the finite element method. The supersonic wing aerodynamic is modeled by the linear piston theory and store aerodynamic is modeled by the semi-stable slender body piston theory. Fuel sloshing in the store with desired geometry is modeled by the boundary element method. The coupled structure, aerodynamic and sloshing governing equations are drawn by using the Galerkin method and reduce order modeling teqnique for them and an effective numerical model was developed that is capable to analyze the stability for aeroelasticity and fuel sloshing of the supersonic wing with any desired geometry. And the interaction effects of these two dynamics are investigated by using this model. The fuel sloshing effect and also store attachment stiffness and damping on the stability of the system are discussed. The obtained results are compared with the case in which store fuel is modeled by the lumped mass and added to the store mass
Keywords:
Finite Element Method ; Boundary Element Method ; Aeroelasticity ; Fuel Sloshing ; Supersonic Wing

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