Abstract
Impact analysis of an advanced laminated composite comprising aerospace 2024-T3 aluminum alloy and resin impregnated E-glass fiber layers with different stacking sequences is presented in the paper. The panel under study is subjected to load-time history equivalent to the low velocity crash using FEM software ANSYS 12. Stress values in the laminate are found to be discontinuous at the interfaces whereas the displacements are continuous across the interfaces. The maximum stress and displacement values in the laminate are comparable with those in monolithic aluminum alloy panel of same thickness.
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