Abstract
In this article, a finite element model of multi-layer composite laminates with delamination based on higher order zig-zag theory is studied for the progressive delamination analysis. The degrees of freedom are simplified by the continuity conditions of shear stress between layers and the free-surface conditions at the bottom and top of laminates. The numbers of degrees of freedom are not reduced with this method while the model can take the initiation of delamination into consideration in return. Static loading analysis is implemented to simulate the performance in delamination resistance with two different plies and under two different boundary conditions. The present model can present good performance in the prediction of delamination phenomenon.
Highlights
Nowadays, composite materials have been applied extensively in many industrial fields such as aerospace, chemistry, automobile, sport apparatus, and medical instruments, attributing their high specific strength and stiffness, good fatigue and corrosion resistance, and property designability
The failure mode of composite laminate is usually classified into three types: fiber failure, matrix failure, and delamination
Load-open displacement curves obtained from double cantilever beam (DCB) model built in section ‘‘Double cantilever beam’’ is illustrated in Figure 8, and results from experiment[39] and from other models[38] are presented in Figure 8 for comparison
Summary
Composite materials have been applied extensively in many industrial fields such as aerospace, chemistry, automobile, sport apparatus, and medical instruments, attributing their high specific strength and stiffness, good fatigue and corrosion resistance, and property designability. Keywords Higher order zig-zag plate theory, composite laminate, progressive damage analysis, delamination The traditional Kirchhoff thin plate model neglect of transverse shear strain (stress) and normal stress along thickness, which have important contributions to delamination damage of composite laminates.
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