A cumulative damage model to predict the fatigue life of composite laminates including the effect of a fibre-matrix interphase

Subramanian, S.; Reifsnider, KL; Stinchcomb, WW

doi:10.1016/0142-1123(95)99735-s

Cited by 113 publications

(63 citation statements)

References 13 publications

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“…The trends found with increasing r max at fixed R, and with increasing R at fixed r max , are both as expected. The roughly linear increase in damage as a function of the logarithmic cycle number implies that fibre breaks accumulate rapidly during the first few cycles, after which the damage accumulation rate decreases gradually, as found in prior investigations of fatigue damage in heterogeneous materials [25,26].…”

Section: Discussionmentioning

confidence: 61%

Damage accumulation during cyclic loading of a continuous alumina fibre reinforced aluminium composite

2005

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Section: Discussionmentioning

confidence: 61%

Damage accumulation during cyclic loading of a continuous alumina fibre reinforced aluminium composite

2005

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“…Based on these experimental results, empirical S-N curves have been derived between stress (S) and fatigue life (N). A nonlinear curve between strain and fatigue life is also used to predict the fatigue life of composite materials [24][25][26]. Both linear and nonlinear S-N curves have been proposed based on the experimental results [21][22][23].…”

Section: Fatigue Limit State: Materials Modelingmentioning

confidence: 99%

Reliability Analysis of Composite Structures and Materials

Mahadevan¹

2004

Engineering Design Reliability Handbook

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From the perspective of strength limit states, composite laminate failure may be considered in two major stages, first-ply failure (FPF) and last-ply failure (LPF). The first-ply failure usually corresponds to the commencement of matrix cracking failure; structural ultimate failure or last-ply failure consists of a series of the ply-level component failures, such as matrix cracking, delamination, and fiber breakage, from the first one to the last one. Well-known methods such as the first-order reliability method (FORM), second-order reliability method (SORM), or Monte Carlo simulation can be combined with finite element analysis to compute the component failure probability. The branch-and-bound method can then be employed to search for the significant system failure sequences. When each component failure occurs, the structural stiffness is modified to account for this damage, and the damaged structure is reanalyzed. This proceeds until system failure occurs. Based on the identified significant failure sequences, the system failure probability is determined by means of bounding techniques. In the composite structure, multiple sequences are found to be highly correlated, leading to efficient approximations in the failure probability computation. Section 44.2 to Section 44.4 present these methods and illustrate them with simple examples, with a practical application for a composite aircraft wing presented in Section 44.4.5.The characteristics of fatigue-damage growth in composite materials are different from those of damage growth in homogeneous materials. Continuum damage mechanics concepts have been used to evaluate the degradation of composite materials under cyclic loading. Damage-accumulation models that capture the unique characteristics of composite materials are presented in Section 44.5. The predictions from the models are compared with experimental data.Fatigue leads to delamination in several laminated composite applications, affected by anisotropic material properties of various plies, ply thicknesses and orientations, loads, and boundary conditions. The limit state can be formulated in terms of the strain energy release rate computed based on the virtual crack-closure technique. The critical value of the strain energy release rate, obtained from test data, is seen to be a random function of life of the structure. Once the delamination initiation probability is estimated, the propagation life until system failure is estimated through the exploration of multiple paths through the branch-and-bound enumeration technique. The analysis is then repeated for multiple initiation sites, and the overall probability of failure is computed through the union of the multiple initiation/growth events. These techniques are presented and illustrated in Section 44.6 using a practical applicationfatigue-delamination analysis of a helicopter rotor component.Composite materials are particularly attractive for high-temperature applications, as in engine components. Therefore, creep reliability models for high-temperature comp...

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“…The initiation, growth, and postponing of matrix cracks in the vicinity of interface predominantly depends on lay‐up sequence and loading condition . This transverse matrix cracking and the intermediate distance has a significant effect on stiffness reduction . Vassilopoulos and Philippidis reported a lower stiffness reduction for higher stressed specimens for various off‐axis GFRP laminates.…”

Section: Introductionmentioning

confidence: 99%

Effect of fatigue loading on stiffness degradation, energy dissipation, and matrix cracking damage of CFRP [±45]_3Scomposite laminate

Behera

Dupare

Thawre

et al. 2019

Fatigue Fract Eng Mat Struct

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In this study, a concept of using experimental matrix crack density, residual stiffness, and energy dissipation as a comparative life monitoring tool for any arbitrary stacking sequence is proposed. First, IMA/M21 [±45]3S carbon fibre‐reinforced polymer (CFRP) multidirectional (MD) laminates were fabricated by autoclaving technique. The static tension and compression tests were conducted to determine the fatigue stress levels. Then, constant amplitude tension–tension fatigue tests were carried out at two stress ratios (R = σmin/σmax) of 0.1 and 0.5. Three stress levels on the basis of cycles to failure (Nf) were chosen, ie, lower stress run‐out (LSR), lower stress fractured (LSF), and higher stress fractured (HSF). The LSF and LSR specimens primarily degraded due to matrix cracking that caused higher stiffness degradation and lower energy parameter, whereas HSF specimens having the least possibility of matrix crack growth showed lower stiffness degradation and higher energy parameter in a fibre‐dominated failure.

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A cumulative damage model to predict the fatigue life of composite laminates including the effect of a fibre-matrix interphase

Cited by 113 publications

References 13 publications

Damage accumulation during cyclic loading of a continuous alumina fibre reinforced aluminium composite

Damage accumulation during cyclic loading of a continuous alumina fibre reinforced aluminium composite

Reliability Analysis of Composite Structures and Materials

Effect of fatigue loading on stiffness degradation, energy dissipation, and matrix cracking damage of CFRP [±45]_3Scomposite laminate

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A cumulative damage model to predict the fatigue life of composite laminates including the effect of a fibre-matrix interphase

Cited by 113 publications

References 13 publications

Damage accumulation during cyclic loading of a continuous alumina fibre reinforced aluminium composite

Damage accumulation during cyclic loading of a continuous alumina fibre reinforced aluminium composite

Reliability Analysis of Composite Structures and Materials

Effect of fatigue loading on stiffness degradation, energy dissipation, and matrix cracking damage of CFRP [±45]3Scomposite laminate

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Effect of fatigue loading on stiffness degradation, energy dissipation, and matrix cracking damage of CFRP [±45]_3Scomposite laminate