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Dynamic Behavior and Impact Induced First Ply Failure of Multiple Delaminated Composite Shells

Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur-721302, India

P. K. Sinha

Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur-721302, India. pksinhagaero.iitkgp.ernet.in

S. K. Bhattacharyya

Department of Civil Engineering, Indian Institute of Technology, Kharagpur-721302, India

This analytical study is concerned with the free vibration, forced vibration, low velocity impact response as well as impact induced first ply failure of delaminated composite shells. It is based on a simple multiple delamination modeling which can take care of any arbitrary number and size of delaminations placed at any location of the laminate. Sander's shallow shell theory is applied for the shell analysis. First order shear deformation theory in conjunction with an eight noded isoparametric quadratic delaminated shell element with five degrees of freedom per node are used to develop the finite element formulation. Newmark's time integration algorithm is employed for solving the time dependent multiple equations of the plate and the impactor. Tsai-Wu failure criterion is used to predict the first ply failure of a laminate due to impact at every time step. Numerical results are generated for different cases by varying the size and location of delaminations as well as the stacking sequences. It is observed that the delaminations reduce the natural frequencies and increase the dynamic displacements. Critical impactor velocity to cause the first ply failure in a laminate is also reduced in the presence of a delamination.

Key Words: composites • composite shells • displacement • shear deformation • finite element analysis • isoparametric • multiple delaminations • stacking sequence • impact • ply failure

Journal of Reinforced Plastics and Composites, Vol. 20, No. 14-15, 1276-1300 (2001)
DOI: 10.1106/YQ8E-3GEL-8JA3-AXWM


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