Free Vibration and Aeroelastic Stability Analysis of Truncated Conical Panels in Supersonic Flows

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Javadi, Masoud | 2014

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 47135 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Dehghani Firoozabadi, Rouhollah
Abstract:
The current study is dedicated to free vibration and Aeroelastic Stability Analysis of Truncated Conical Panels in Supersonic Flows. Governing equations of motion and the corresponding boundary conditions are derived using Hamiltonian formulations. The aeroelastic stability problem is formulated based on first-order shear deformation theory as well as classical shell theory with the linearized first-order piston theory for aerodynamic loading and solved using Galerkin method. The flutter boundaries are obtained for truncated conical shells with different semi-vertex cone angles, different subtended angles, and different thickness
Keywords:
Stability ; Galerkin Method ; Natural Frequency ; Vibration ; Eigen Values ; Truncated Conical Thin Shell

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