Thickness effect on the compressive strength of T800/924C carbon fibre–epoxy laminates

Lee, J.; Soutis, C.

doi:10.1016/j.compositesa.2004.06.010

Cited by 38 publications

(27 citation statements)

References 21 publications

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“…For composite laminates in general, size effects with regard to scaling of the specimens on the one hand and thickness of the constitutive plies on the other hand should be considered [ 12 ]. Soutis [ 13 ] and Lee and Soutis [ 14 , 15 ] investigated the influence of specimen and layer thickness on the strength and failure behaviour for unnotched compression (UNC) [ 13 , 14 ] and open-hole compression (OHC) [ 15 , 16 ] load cases and compared the compression behaviour of open-hole specimens with that under tensile loading and found a strength increase with decreasing dimensions or ply thickness [ 17 ]. Arteiro et al [ 18 ] showed with micromechanical modelling and finite element simulation that the in situ effect in tension [ 19 ] exists as well under compression loading : They reported a higher ply strength with decreasing ply thickness and with increasing the stiffness of the surrounding layers [ 18 ].…”

Section: Introductionmentioning

confidence: 99%

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Compression Fracture of CFRP Laminates Containing Stress Intensifications

Leopold

Schütt²,

Liebig

et al. 2017

Materials

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Abstract:For brittle fracture behaviour of carbon fibre reinforced plastics (CFRP) under compression, several approaches exist, which describe different mechanisms during failure, especially at stress intensifications. The failure process is not only initiated by the buckling fibres, but a shear driven fibre compressive failure beneficiaries or initiates the formation of fibres into a kink-band. Starting from this kink-band further damage can be detected, which leads to the final failure. The subject of this work is an experimental investigation on the influence of ply thickness and stacking sequence in quasi-isotropic CFRP laminates containing stress intensifications under compression loading. Different effects that influence the compression failure and the role the stacking sequence has on damage development and the resulting compressive strength are identified and discussed. The influence of stress intensifications is investigated in detail at a hole in open hole compression (OHC) tests. A proposed interrupted test approach allows identifying the mechanisms of damage initiation and propagation from the free edge of the hole by causing a distinct damage state and examine it at a precise instant of time during fracture process. Compression after impact (CAI) tests are executed in order to compare the OHC results to a different type of stress intensifications. Unnotched compression tests are carried out for comparison as a reference. With this approach, a more detailed description of the failure mechanisms during the sudden compression failure of CFRP is achieved. By microscopic examination of single plies from various specimens, the different effects that influence the compression failure are identified. First damage of fibres occurs always in 0°-ply. Fibre shear failure leads to local microbuckling and the formation and growth of a kink-band as final failure mechanisms. The formation of a kink-band and finally steady state kinking is shifted to higher compressive strains with decreasing ply thickness. Final failure mode in laminates with stress intensification depends on ply thickness. In thick or inner plies, damage initiates as shear failure and fibre buckling into the drilled hole. The kink-band orientation angle is changing with increasing strain. In outer or thin plies shear failure of single fibres is observed as first damage and the kink-band orientation angle is constant until final failure. Decreasing ply thickness increases the unnotched compressive strength. When stress intensifications are present, the position of the 0°-layer is critical for stability under compression and is thus more important than the ply thickness. Central 0°-layers show best results for OHC and CAI strength due to higher bending stiffness and better supporting effect of the adjacent layers.

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Section: Introductionmentioning

confidence: 99%

“…At free edges, compression failure is hence partly a result of delamination growth. With increasing hole diameter/specimen width ratio, compressive strength decreases [ 14 , 15 , 16 , 27 ]. The OHC failure process depend on interlaminar toughness.…”

Section: Introductionmentioning

confidence: 99%

Compression Fracture of CFRP Laminates Containing Stress Intensifications

Leopold

Schütt²,

Liebig

et al. 2017

Materials

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“…Lee and Soutis laminated composites with various stacking sequence with an open hole in the centre. The conclusions shows that the strength of the specimen with the higher thickness is found increased and the measured failure strength is predictable [14]. Paiva et al conducted experiments on different matrix materials with carbon fiber as the reinforcement material [15].…”

Section: Introductionmentioning

confidence: 96%

Experimentation with Flexural Properties of the Carbon Fiber Graphite Fiber and Glass Fiber Composites

B.V.,

Sahu*,

Kumar M. S.

2019

IJRTE

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In the present work the flexural properties of selected composite plates are examined. The three point bending test happens to be widely acceptable method for the evaluation of flexural properties of the composite plates because of its simple geometry and structure. In this paper the influence of filler material and thickness of laminates under three point bending load on simply supported pins are reported for selected filler material combination. Filler materials used here are Glass fiber epoxy with silicon carbide, Graphite fiber epoxy with silicon carbide and Carbon fiber epoxy with silicon carbide. Investigation is carried out as per ASTM D790 standard. The mechanical properties such as flexural strength, flexural stiffness of the composite plates were investigated and reported. This work broadly points out that the flexural strength is dependent on the thickness of the laminates and amount of the filler material of the laminated composites. It was found that Carbon fiber composite shows the superior flexural strength with 6 wt% of SiC among the specimens under study.

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“…Similar to the work published by Uhl et al [17] and Lee and Soutis [18,19], the calculation of the updated material strength due to porosity was done according to the relation…”

Section: A Extended Non-destructive Testing Modulementioning

confidence: 99%

Material Selection for a Curved C-Spar Based on Cost Optimization

Kaufmann

Zenkert

Åkermo

2011

Journal of Aircraft

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A case study for the cost optimization of aircraft structures based on the operating cost as objective function is presented. The proposed optimization framework contains modules for estimation of the weight, manufacturing cost, non-destructive inspection cost and structural performance, the latter enhanced by a kinematic draping model which allows the fiber angles to be simulated more realistically. The case study includes five material systems:

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Thickness effect on the compressive strength of T800/924C carbon fibre–epoxy laminates

Cited by 38 publications

References 21 publications

Compression Fracture of CFRP Laminates Containing Stress Intensifications

Compression Fracture of CFRP Laminates Containing Stress Intensifications

Experimentation with Flexural Properties of the Carbon Fiber Graphite Fiber and Glass Fiber Composites

Material Selection for a Curved C-Spar Based on Cost Optimization

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