Abstract
The use of composite laminates is increasing in these days due to desired directional properties and low densities in comparison of metals. Delamination is a major source of failure in composite laminates where a crack like entity can initiate and propagate between different layers of composite laminates under given loading conditions. Damage mechanics based theories are employed to simulate the delamination phenomena between composite laminates. These damage models are inherently local and can cause the concentration of stresses around the crack tip. In the present study integral type non-local damage formulation is proposed to avoid the localization problem associated to damage formulation. A comprehensive study is carried out for the selection of different non-local variables. Finite element simulations based on proposed non-local damage models and classical local damage model are performed and results are compared with available experimental data for UD IMS/924 Carbon/fiber epoxy composite laminate.
Highlights
Composite laminates are used as a major load bearing structural parts in different industries like avionic and automobile
The interface is a two-dimensional surface entity that ensures the transfer of stress and displacement between two adjacent plies [4,8]. This model coupled with the damage mechanics theory can take into account the phenomena of delamination that may occur during mechanical loading of structural parts
In order to satisfy the energy balance principle of linear elastic fracture mechanics (LEFM), the area under the curve of stress-displacement curve for the whole debonding process (DP) obtained through Damage Mechanics formulation is set equal to critical energy release rate GiC, and the following relations for the modes I, II and III critical energy release rates can be written: GIC = σ33 dU3, GIIC = σ13 dU1, GIIIC = σ23 dU2
Summary
Composite laminates are used as a major load bearing structural parts in different industries like avionic and automobile. The composite laminates consist of different layers of fibers/fabric stacked together and cured with thermosetting resin [1]. In recent times much attention is made to integral type non-local damage modeling in order to reduce the localization effects This type of modeling is effectively discussed and employed to study the delamination crack growth in composite laminates [13, 14]. Finite element simulations on delamination crack growth with different types of non-local variables are performed and compared with each other and with classical local damage model in the present study.
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