Buckling of Compression Loaded Laminated Composite Cylindrical Panels
Buckling characteristics of anisotropic laminated cylindrical panels are presented using an isoparametric nine-noded rectangular element. Kinematic relations, extended to include the first order shear deformation theory through the thickness of the laminate, are utilized in the formulation. Numerical results are presented for laminated cylindrical panels under uniaxial and biaxial compression loadings to illustrate the influence of panel sizes, orientation of layers, material properties, and boundary conditions on the buckling loads. Results for plates are also presented as special cases and are compared with the available solutions.
K. Chandrashekhara, "Buckling of Compression Loaded Laminated Composite Cylindrical Panels," Composite Material Technology 1989; Houston, TX, American Society of Mechanical Engineers (ASME), Petroleum Division, Jan 1989.
Composite Material technology 1989
Mechanical and Aerospace Engineering
Keywords and Phrases
Cylinders-Composite; Kinematics; Laminated Products-Deformation; Stresses-Shear
Article - Conference proceedings
© 1989 American Society of Mechanical Engineers (ASME), Petroleum Division, All rights reserved.
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