Fatigue design allowables for GRP laminates based on stiffness degradation measurements

Philippidis, T.P.; Vassilopoulos, Anastasios P.

doi:10.1016/s0266-3538(00)00150-0

Cited by 82 publications

(57 citation statements)

References 9 publications

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“…Various statistical methods have been developed to analyse the distribution of fatigue life data [11][12][13]. Among these methods, Weibull distribution function has been well-established to characterise the fatigue life of laminated composites [11].…”

Section: Introductionmentioning

confidence: 99%

Quantification of flexural fatigue life and 3D damage in carbon fibre reinforced polymer laminates

Liu

Srikanth

et al. 2016

Composites Part A: Applied Science and Manufacturing

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Carbon fibre reinforced polymer (CFRP) laminated composites have become attractive in the application of wind turbine blade structures. The cyclic load in the blades necessitates the investigation on the flexural fatigue behaviour of CFRP laminates. In this study, the flexural fatigue life of the [+45/-45/0]2s CFRP laminates was determined and then analysed statistically. X-ray microtomography was conducted to quantitatively characterise the 3D fatigue damage. It was found that the fatigue life data can be well represented by the two-parameter Weibull distribution; the life can be reliably predicted as a function of applied deflections by the combined Weibull and Sigmodal models. The delamination at the interfaces in the 1 st ply group is the major failure mode for the flexural fatigue damage in the CFRP laminate. The calculated delamination area is larger at the interfaces adjacent to the 0 ply. The delamination propagation mechanism is primarily matrix/fibre debonding and secondarily matrix cracking.

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Section: Introductionmentioning

confidence: 99%

Quantification of flexural fatigue life and 3D damage in carbon fibre reinforced polymer laminates

Liu

Srikanth

et al. 2016

Composites Part A: Applied Science and Manufacturing

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“…Through the damage, this will therefore also have an effect on the stiffness decrease during fatigue. Philippidis and Vassilopoulos (2000), for example, showed that the stiffness variation during fatigue in UD-based angle-ply laminates is more pronounced for laminates with greater off-axis angles.…”

Section: Stiffness Evolutionmentioning

confidence: 99%

Fatigue in non-crimp fabric composites

Vallons¹

2011

Non-Crimp Fabric Composites

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Knowledge of the fatigue behaviour of a material is essential for safe use in structural applications. This chapter discusses recent fi ndings concerning the tensile fatigue properties of non-crimp fabric (NCF) composites (fatigue life, stiffness evolution and damage development). It is also briefl y describes how fatigue infl uences the residual static performance of these materials.In most applications, materials are not simply subjected to static loading conditions; other loading modes are often equally, or sometimes more, important. For many applications, like cars and aeroplanes, it is very important to know how the material behaves under fatigue. This chapter focuses on the fatigue behaviour of non-crimp fabric (NCF) composites. The discussions are limited to tensile fatigue loading conditions.In most metals, tensile fatigue is characterised by the initiation of a single crack that then propagates until catastrophic failure, which occurs with little warning. Unlike metals, however, composite materials are inhomogeneous and anisotropic on the mesoscale. They accumulate damage in a general, rather than a localised, fashion, and, most often, failure does not occur by the propagation of a single macroscopic crack. The microstructural mechanisms of fatigue damage in a composite can include fi bre breakage, matrix cracking, debonding, and delamination. These damage modes may occur independently or interact with each other, and the dominant mechanism can depend on material variables and testing conditions. This makes fatigue in composites a very complex issue (Harris, 2003).The present chapter deals with fatigue in one particular type of continuous fi bre composite, the non-crimp fabric (NCF) composites. While fatigue in Unidirectional (UD) based laminates and woven fabric laminates has been investigated widely in the past, the knowledge about the specifi c fatigue properties of NCF composites is still relatively limited. The following paragraph discusses a number of recent fi ndings concerning the fatigue life, damage development and stiffness evolution of composites based on NCFs. The infl uence of the composite orientation compared to the loading direction is also briefl y considered. After that, the infl uence of fatigue loading on the residual static properties of the composite material is looked into.

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“…To assess the efficiency of the modified damage model in evaluating fatigue damage of 0°and θ°unidirectional GRP composites as number of cycles increases, several sets of fatigue data of unidirectional composite laminates with various stress magnitudes, R-ratios, and off-axis angles were taken from the literature [2,3,5,21,22]. Table 2 represents fatigue testing details for GRP components performed at room temperature under constant amplitude loading conditions and various stress ratios based on ASTM D3090M.…”

Section: Unidirectional Compositesmentioning

confidence: 99%

“…Details of unidirectional fatigue damage assessment of various off-axis angles by Eq. (2) have been addressed in reference [8].…”

Section: Unidirectional Compositesmentioning

confidence: 99%

See 1 more Smart Citation

A Stiffness Degradation Based Fatigue Damage Model for FRP Composites of (0/θ) Laminate Systems

Shirazi

Varvani‐Farahani

2009

Appl Compos Mater

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The present study develops a stiffness reduction-based model to characterize fatigue damage in unidirectional 0˚and θ°plies and (0/θ) laminates of fiber-reinforced polymer (FRP) composites. The proposed damage model was constructed based on (i) cracking mechanism and damage progress in matrix (Region I), matrix-fiber interface (Region II) and fiber (Region III) and (ii) corresponding stiffness reduction of unidirectional composite laminates as the number of cycles progresses. The proposed model enabled damage assessment of FRP (0/θ) composite laminates by integrating the fatigue damage values of 0˚and θ°plies. A weighting factor η was introduced to partition the efficiency of load carrying plies of 0°and θ°in the (0/θ) composite lamina. The fatigue damage curves of unidirectional FRP composite samples with off-axis angles of 0˚, 30˚, 45˚, and 90˚and composite laminate systems of (0˚/30˚), (0˚/45˚) and (0˚/90˚) predicted based on the proposed damage model were found in good agreement with experimental data reported at various cyclic stress levels and stress ratios in the literature.

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Fatigue design allowables for GRP laminates based on stiffness degradation measurements

Cited by 82 publications

References 9 publications

Quantification of flexural fatigue life and 3D damage in carbon fibre reinforced polymer laminates

Quantification of flexural fatigue life and 3D damage in carbon fibre reinforced polymer laminates

Fatigue in non-crimp fabric composites

A Stiffness Degradation Based Fatigue Damage Model for FRP Composites of (0/θ) Laminate Systems

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