Cohesive zone length in numerical simulations of composite delamination

By Paul W. Harper, S. Hallett. 2008

556 citations recorded by the source corpus.

Subfields: Civil and Structural Engineering, Mechanics of Materials

View Paper: https://www.semanticscholar.org/paper/cb120074e55f0f658b9c32294bfe9ece12cda0d4

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In Civil and Structural Engineering

In Mechanics of Materials

Citations in the corpus

A new generalized finite element method for two‐scale simulations of propagating cohesive fractures in 3‐D (2015, unknown): “, [107].”
On cohesive element parameters and delamination modelling (2019, background): “The relationship between cohesive strength and mesh size has been widely researched in the literature [18-22].”
An experimental and numerical investigation into the damage mechanisms in notched composites (2009, background): “This is necessary in order to preserve a sufficient number of interface elements in the process zone ahead of a predicted crack tip, see [28] for further details.”
A fatigue degradation law for cohesive interface elements – Development and application to composite materials (2010, methodology): “However, this requires a significantly finer mesh than that required purely to obtain an accurate load-displacement analysis, where only 2-3 interface elements are needed within the fully developed cohesive zone [28,38].”
Compressive failure of laminates containing an embedded wrinkle; experimental and numerical study (2015, background): “8(a)) were related to the corresponding traction components by high stiffness values I K and II K [24].”
A crack tip tracking algorithm for cohesive interface element analysis of fatigue delamination propagation in composite materials (2012, background): “Because the cohesive zone length is a load and geometry-dependent parameter (Turon et al., 2008; Harper and Hallett, 2008), the present work aimed at developing a formulation which is independent of this value and of any assumptions required for its estimation.”
Barely visible impact damage in scaled composite laminates: Experiments and numerical simulations (2017, unknown): “According to the calculation presented in Harper and Hallett [37] for accurate interface element performance, finer meshes were required in the interlaminar cohesive layers than in the plies.”
Progressive damage modeling of open-hole composite laminates under compression (2015, methodology): “The expressions of EII and E 0 II;slender can be found in [31].”
Computational modeling of complex failure mechanisms in laminates (2012, background): “For the interface elements, the strength is reduced with a factor 2 as suggested by Turon et al.65 and examined by Harper and Hallett.60 .”