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This threshold is due to the absence of an easy path for oxygen ingress when matrix cracks are not present.
Near-tip matrix cracks are found to initiate and propagate intralaminarly before the onset of planar growth.
Matrix cracks are modelled through the eXtended Finite Element Method and delaminations through a cohesive zone model.
The finite elements analysis is also show that the matrix cracks are initiated in the first skin layer for most of the cases.
With increasing the applied load the matrix cracks are propagated through the thickness to reach the next layer and causes delamination between the two layers.
Based on the Schapery's 3-D constitutive relationship and the Von Karman's plate theory, the constitutive equations and the nonlinear dynamic governing equations for viscoelastic symmetric cross-ply laminated plates with transverse matrix cracks are derived.
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The propagation mechanism of matrix cracks is also discussed.
No matrix cracks were observed prior to fatigue loading.
The effect of matrix cracks is included in an analytical model of composite box-beam.
An analytical, closed form solution for [0m/90n/±θr]s laminated composites with transverse matrix cracks is presented.
These matrix cracks were found to have initiated preferentially in the weak 90° plies near the 90°/0° ply boundaries.
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