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A finite element model for progressive in-plane damage and interfacial delamination was presented for cross-ply composite laminates. The commercial finite element software ABAQUS/STANDARD was used for this study. Each composite lamina was modeled as layers of shell elements based on Mindlin's plate theory. Displacement continuity was established across the layers of shell elements. Interlaminar stresses were recovered at the interface with the use of multi-point constraints. Several material constitutive relations were developed to simulate in-plane damage, such as fiber breakage, matrix cracking and in-plane shear failure. Delamination was simulated by removing the displacement constraints. Cross-ply composite laminates were subjected to impact loading. The results from the finite element analysis compared well with the experimental results.

A finite element model for hybrid III dummy's lower torso is presented. All details of the dummy's knee structure are carefully considered. In order to justify the finite element model, numerical results are made to compare with the experimental results from both knee impact test and knee slider impact test. It is found that the finite element results agree very well with their experimental counterparts.

Foamed materials and rubbery materials have been commonly used as energy absorbers in automotive safety designs. The present study investigates the response of polyurethane, vinyl, and their laminations with aluminum panels under low-velocity impact. In addition to force history and force-deflection relation, impact parameters such as peak force, contact duration, maximum deflection, and energy absorption capability are of primary concerns. Experimental results reveal that the lamination sequence affects the impact parameters significantly, LS-DYNA3D is also used to verify the experimental findings.