Buckling analysis of stiffened cross-ply laminated conical shells under axial compression using GDQ method

Document Type : Research Article

Authors

1 Sharif University of Technology, Department of Aerospace Engineering, Tehran, Iran

2 دانشگاه صنعتی شریف- دانشکده مهندسی هوافضا

3 دانشکده مهندسی هوافضا

4 Iran Space Institute, Tehran, Iran

10.22060/ajme.2021.18820.5922

Abstract

The object of this study is to determine the global buckling load of stiffened composite conical shells under axial compression. The conical shells are stiffened by stringers in longitudinal and rings in circumferential directions. The boundary conditions are assumed to be simply supported at both ends. At the first, the equilibrium equations are obtained using the first order shear deformation theory (FSDT) and principle of minimum potential energy. Effects of stiffeners ((longitudinal and circumferential directions) are considered using smearing technique. The resulting equations are solved using generalized differential quadrature method (GDQM) to obtain the critical buckling load. The acquired results are compared with the results of finite element method (FEM) and other researcher's results available in the literature, and good agreement is observed. The influence of number of stiffeners and rings, length, radius and semi-vertex angle of the cone on buckling behavior of the shell are studied. Finally, optimum number of stiffeners (longitudinal and circumferential) to achieve the maximum global buckling load in composite conical shell for a specific weight and overall geometry is investigated.

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