Cumulative Damage Model for Advanced Composite Materials.

Miller, H R; Reifsnider, K.L.; Stinchcomb, WW; Ulman, D. A.; Bruner, R D

doi:10.21236/ada144840

Cited by 8 publications

(4 citation statements)

References 9 publications

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“…This is done by comparing to published experimental results. The size of the crack spacing in 90°plies as a function of applied laminate stress for [0 n /90 m ]s and [±25/90 n ]s laminates for different values of n and m and for different materials is compared to test results from 2,[19][20][21][22] in Figure 2.…”

Section: Matrix Crack Formationmentioning

confidence: 99%

“…For a symmetric laminate, E x c and g xy c can be calculated using the A matrix. The results can then be differentiated with respect to 1/D with the use of equations (19) and (20) to get the strain energy release rate G c for the laminate with cracked plies. An example of how the value of G c changes with crack spacing for different thickness of cracked plies in various laminates under tension is shown in Figure 3.…”

Section: Delamination Onsetdelaminations Emanating From Matrix Cracksmentioning

confidence: 99%

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Damage history in composite laminates: Matrix cracks leading to delaminations

Romarís Villanueva,

Kassapoglou

2024

Journal of Composite Materials

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Strain energy release rate calculations for various cases of delaminations emanating from matrix cracks are developed and used to predict the onset of delaminations and their growth size as a function of applied tension and shear loads in composite laminates. The method determines the matrix crack spacing, the delamination onset load, the delamination size at onset and, through the use of a newly proposed delamination resistance curve, the size of delaminations as they grow under load. The method can be applied to any symmetric laminate. Comparisons to test results in the literature for a variety of layups and materials shows very good agreement with the exception of cases where significant edge delaminations appear before delaminations caused by matrix cracks.

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Section: Matrix Crack Formationmentioning

confidence: 99%

Section: Delamination Onsetdelaminations Emanating From Matrix Cracksmentioning

confidence: 99%

Damage history in composite laminates: Matrix cracks leading to delaminations

Romarís Villanueva,

Kassapoglou

2024

Journal of Composite Materials

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“…Hashin [13] provided a statistical cumulative damage theory of fatigue based on his deterministic cumulative damage theory [9] by making the assumption of normal distribution of experimental data. Yang and Jones [14] and Chou [15] assumed a twoparameter Weibull distribution of ultimate tensile strength for the prediction of fatigue life. Bengtsson and Rychik [16] and Rychlik and Gupta [17] studied fatigue damage by Gaussian loads.…”

Section: Introduction and Historical Reviewmentioning

confidence: 99%

Cumulative Damage Theory in Fatigue of Graphite/Epoxy [±45]_sComposites

An¹

2015

Composites Research

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ABSTRACT:The phenomenological evolution laws of damage can be defined either based on residual life or residual strength. The failure of a specimen can be defined immediately after or before fracture. The former is called in this paper by "failure defined by approach I" and the latter "failure defined by approach II. " Usually at failure there is a discontinuity of loading variables and, because of this, damage at failure is discontinuous. Therefore the values of damage at failure by two different approaches are not the same. Based on this idea the sequence effects of the phenomenological evolution law of damage given by dD/dN = g(D)f(Φ) were studied. Thin-walled graphite/epoxy tubes consisting of four of [±45] s laminates were used for the experimental study of sequence effects and the effects of mean stress on fatigue life. It was found that the sequence effects in two step uniaxial fatigue for [±45] s graphite/epoxy tubular specimen showed that a high-low block loading sequence was less damaging than a low-high one.

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“…Wang (1983) contributed significantly by numerically solving the matrix crack problem. Chou et al (1982) used a statistical approach along with finite element method (FEM) and energy fracture criterion for solving this problem. Tan (1982, 1988), Tan (1983), and Tan and Nuismer (1989) have studied the progressive failure of composite laminate using a plane strain assumption and generalized plane strain assumption.…”

Section: Introductionmentioning

confidence: 99%

Matrix Crack Detection in Thin-walled Composite Beam using Genetic Fuzzy System

Pawar

Ganguli

2005

Journal of Intelligent Material Systems and Structures

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Since thin-walled composite structures are widely used in structural engineering, damage in such structures is an important issue of research. Matrix cracking is a principal cause of failure in composites. In the present study, a composite matrix cracking model is implemented in a thin-walled hollow circular cantilever beam using an effective stiffness approach. Such structures are used to model connecting shafts and helicopter tail boom, for example, because of their high stiffness-to-weight ratios and excellent crashworthiness characteristics. The effect of variation in crack density on the fundamental frequency, for various combinations of ½AE m =90 n s composite is studied. Using these change in frequencies due to matrix cracking, a genetic fuzzy system for crack density and crack location detection is generated. The genetic fuzzy system combines the uncertainty representation characteristics of fuzzy logic with the learning ability of genetic algorithm. It is observed that the success rate of the genetic fuzzy system in the presence of noise is dependent on crack density (level of damage), number of 90 plies, angle of constraining layer (), and noise level. It is found that the genetic fuzzy system shows excellent damage detection and isolation performance, and is robust to presence of noise in data.

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Cumulative Damage Model for Advanced Composite Materials.

Cited by 8 publications

References 9 publications

Damage history in composite laminates: Matrix cracks leading to delaminations

Damage history in composite laminates: Matrix cracks leading to delaminations

Cumulative Damage Theory in Fatigue of Graphite/Epoxy [±45]_sComposites

Matrix Crack Detection in Thin-walled Composite Beam using Genetic Fuzzy System

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Cumulative Damage Model for Advanced Composite Materials.

Cited by 8 publications

References 9 publications

Damage history in composite laminates: Matrix cracks leading to delaminations

Damage history in composite laminates: Matrix cracks leading to delaminations

Cumulative Damage Theory in Fatigue of Graphite/Epoxy [±45]sComposites

Matrix Crack Detection in Thin-walled Composite Beam using Genetic Fuzzy System

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Product

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Cumulative Damage Theory in Fatigue of Graphite/Epoxy [±45]_sComposites