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REVIEW ARTICLES

Characterization and analysis of delamination fracture in composites: An overview of developments from 1990 to 2001

[+] Author and Article Information
TE Tay

Department of Mechanical Engineering, National University of Singapore, 10 Kent Ridge Crescent, Singapore 119260, Singapore

Appl. Mech. Rev 56(1), 1-32 (Jan 15, 2003) (32 pages) doi:10.1115/1.1504848 History: Online January 15, 2003
Copyright © 2003 by ASME
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References

Figures

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Three general modes of fracture
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Double cantilever beam (DCB) specimen, after Martin 52
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End-notched flexure (ENF) specimen, after Martin 52
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End-loaded split (ELS) specimen, after Martin 52
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Four-point end-notched flexure (4ENF) specimen, after Schuecker and Davidson 17 (reprinted with permission of Elsevier Science)
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Mode I, Mode II, and mixed-mode fracture toughness for various composites, after Johnson and Mangalgiri 19 (reprinted with permission of ASTM International)
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Mixed-mode bend specimen, after Martin 52
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Scanning electron micrographs showing the formation of microcracks ahead of a delamination crack tip in AS4/3502, after Sjögren and Asp 36.
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Scanning electron micrographs showing the coalescence of microcracks into hackles in the wake of a delamination crack tip in AS4/3501-6, after Sjögren and Asp 36.
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Local crack opening displacement created under global shear loading, after Paris and Poursatip 37
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Crack opening displacements (COD) vs x (distance from the crack tip) for a unidirectional AS4/3501-6 specimen with a 19 mm pre-crack, under global pure Mode II loading (after Paris and Poursatip 37). Dashed lines show COD profiles for GIL that best fit the measurements.
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Edge-cracked torsion (ECT) specimen, after Li and Wang 39 (reprinted with permission of ASTM International)
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Comparison of fracture toughness for the three modes for G40-800/R6376 graphite-epoxy laminates, after Li et al. 43 (reprinted with permission of ASTM International)
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The split cantilever beam (SCB) specimen (a), and the crack rail shear (CRS) specimen (b), after Martin 48 (reprinted with permission of ASTM International)
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Formation of shear hackles and shear crevices, after Trakas and Kortschot 50 (reprinted with permission of ASTM International)
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Example of mixed-mode delamination fatigue data, after Kenane and Benzeggagh 57 (reprinted with permission of Elsevier Science)
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Mixed-mode fatigue data for IM7/5260, after Martin et al. 56 (reprinted with permission of ASTM International)
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Development of shear microcracks and displacements in Mode II delamination, after Dahlen and Springer 65
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Interface crack between two dissimilar materials
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Schematic of (a) 2D and (b) 3D crack fronts in the VCCT
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Comparison of computed SERRs from the resin layer and bare interface models, after Raju et al. 82. In Raju’s notation, Δ is the increment in crack length (reprinted with permission of Elsevier Science).
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Computed SERRs of a center cracked bimaterial plate subjected to tension, after Dattaguru et al. 81 (reprinted with permission of Elsevier Science)
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Plate element model of skin and stiffener, after Wang and Raju 84 (reprinted with permission of Elsevier Science)
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VCCT with four-noded plate elements, after Wang and Raju 84 (reprinted with permission of Elsevier Science)
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VCCT with nine-noded plate elements, after Wang and Raju 84 (reprinted with permission of Elsevier Science)
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Plate and 2D plane-strain finite element models of stiffener flange-skin strip, after Wang and Raju 84 (reprinted with permission of Elsevier Science)
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Comparison of SERRs obtained by Technique B, after Wang and Raju 84 (reprinted with permission of Elsevier Science)
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Comparison of SERRs obtained by Technique A, after Wang and Raju 84 (reprinted with permission of Elsevier Science)
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Crack tip element for plate theory, after Schapery and Davidson 86
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Beam model and loading for global partitioning of SERR, after Williams 103
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Crack jumping and delamination along different interfaces in a multidirectional ENF laminate, after Tao and Sun 114
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Mode II dominated critical SERR of 0/θ interfaces of AS4/3501-6 laminates, after Tao and Sun 114
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Finite element simulation of an embedded delamination under compression, with and without consideration of contact, after Rinderknecht and Kröplin 137; only a quarter of the plate was modeled (reprinted with permission of Taylor and Francis, Inc).
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Numerical simulation of deformed configurations of a [03 // 903 //453 //−45/−453 //453 //903 // 03 ] laminate containing six delaminations with an umbrella-shaped distribution as a function of the applied load, after Kutlu and Chang 144
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Continuum elements connected by line interface elements, after Schellekens and De Borst 166
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Traction (tn)-displacement (vn) diagram for discrete crack model, after Schellekens and De Borst 166
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Plate attached to a bed of elastic axial rods, after Shahwan and Waas 188. The length of rods is exaggerated for clarity. Theoretically, the number of rods is infinite, but for computational purposes, the number is finite and is equal to the number of integration points (reprinted with permission of The Royal Society).
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Sequence of pictures showing the progression of delamination (dark areas), after Shahwan and Waas 188 (reprinted with permission of The Royal Society)
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Application of shell/3D modeling technique to large built-up structures, after Krueger and O’Brien 202 (reprinted with permission of Elsevier Science)
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Comparison of total SERR, using a fracture mechanics (FM) approach, and a damage mechanics (DM) approach, after Rinderknecht and Kröplin 137. The model is shown in Fig. 33. The 3D FEM solution shown is Whitcomb’s 134 (reprinted with permission of Taylor and Francis, Inc).
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SERR components along the delamination front, after Rinderknecht and Kröplin 137. The model is shown in Fig. 33. The 3D FEM solutions shown are Whitcomb’s 134 (reprinted with permission of Taylor and Francis, Inc).
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Thin-film delamination model for a cross-ply [0/90/0]10T laminate, after Simitses 213
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Full 3D finite element model of an embedded delamination, after Tay and Shen 241
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Mode I SERR along delamination front (two-ply delamination), after Tay and Shen 241
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Mode II SERR along delamination front (two-ply delamination), after Tay and Shen 241
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C-scan image and directions of maximum SERRs for a two-ply delamination, after Tay and Shen 241
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C-scan image and directions of maximum SERRs for a three-ply delamination, after Tay and Shen 241
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C-scan image and directions of maximum SERRs for a four-ply delamination, after Tay and Shen 241
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Measured load vs out-of-plane displacement of lower u3L and upper u3Uside of panels of [(90/0)17/90] carbon fiber-epoxy with embedded delaminations, after Nilsson et al. 247. A3_10_2, A5_5_2 and A7_5_2 refer to laminates with delaminations embedded after the third, fifth, and seventh ply, respectively. Ref #2 and Ref #3 do not contain delaminations (reprinted with permission of Elsevier Science).
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Moving finite element mesh at 15 mm growth for a three-ply delamination, after Nilsson et al. 247. Shaded area denote contact and load direction is x1 (reprinted with permission of Elsevier Science).
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Angle-ply laminate double cantilever beam specimen with curved cross section, after Ozdil and Carlsson 164
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Molecular dynamics simulation of interfacial failure between epoxy and solid surface under tensile pull, after Stevens 269 (reprinted with permission of the American Chemical Society)

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