Ganapathy, S and Rao, KP (1998) Failure analysis of laminated composite cylindrical/spherical shell panels subjected to low-velocity impact. In: Computers and Structures, 68 (6). pp. 627-641.
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A 4-noded, 48 d.o.f. doubly curved quadrilateral shell finite element based on Kirchhoff-Love shell theory, is used in the nonlinear finite element analysis to predict the damage of laminated composite cylindrical/spherical shell panels subjected to low-velocity impact. The large displacement stiffness matrix is formed using Green's strain tensor based on total Lagrangian approach. An incremental/iterative scheme is used for solving resulting nonlinear algebraic equations by Newton-Raphson method. The damage analysis is performed by applying Tsai-Wu quadratic failure criterion at all Gauss points and the mode of failure is identified using maximum stress criteria. The modes of failure considered are fiber breakage and matrix cracking. The progressive failure analysis is carried out y degrading the stiffness of the material suitably at all ailed Gauss points. The load due to low-velocity impact is treated as an equivalent quasi-static load and Hertzian law of contact is used for finding the maximum contact force. After evaluating the nonlinear finite element analysis thoroughly for typical problems, damage analysis was arried out for cross-ply and quasi-isotropic cylindrical/spherical shell panels.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to Elsevier.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||03 Jan 2007|
|Last Modified:||19 Sep 2010 04:33|
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