Mechanical performance of carbon-epoxy laminates. Part II: quasi-static and fatigue tensile properties

Tarpani, José Ricardo; Milan, Marcelo; Spinelli, Dirceu; Bose, W. W.

doi:10.1590/s1516-14392006000200003

Cited by 11 publications

(7 citation statements)

References 17 publications

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“…Part I of this work investigates the quasi-static and impact bending performance of four carbon-epoxy laminates utilized in the Brazilian aeronautical industry, whereas Part II 7 evaluates their quasi-static and fatigue tensile properties.…”

Section: Introductionmentioning

confidence: 99%

Mechanical performance of carbon-epoxy laminates. Part I: quasi-static and impact bending properties

et al. 2006

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In Part I of this study, quasi-static and impact bending properties of four aeronautical grade carbon-epoxy laminates have been determined and compared. Materials tested were unidirectional cross-ply (tape) and bidirectional woven textile (fabric) carbon fiber lay-up architectures, impregnated with standard and rubber-toughened resins, respectively, giving rise to 1.5 mm-thick laminates. Quasi-static mechanical properties assessed in transversal mode loading were modulus of elasticity, flexural strength and tenacity at the maximum load, whereas the net absorbed energy was determined under translaminar impact conditions. Two-dimensional woven carbon fiber reinforcements embedded in a rubber-toughened matrix presented the best mechanical performance under static loading. Under dynamic loading conditions, woven fiber fabric pre-forms were favorably sensitive to increasing impact energies regardless the nature of the employed epoxy resin. However, it was concluded that great care should be taken with this material within the low energy impact regimen

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Section: Introductionmentioning

confidence: 99%

Mechanical performance of carbon-epoxy laminates. Part I: quasi-static and impact bending properties

et al. 2006

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“…Tensile test results of NC3DOW indicate the uniqueness of this structure. The stress concentration at the interlacing points, which results in fast microcrack growth and premature failure of fabric specimen [40] is much less than other kinds of 3D woven fabrics. When the tensile load is applied along the Z yarns direction, a small portion of the load is transferred to the warp and weft yarns.…”

Section: Resultsmentioning

confidence: 98%

Investigation into tensile strength of noncrimp three-dimensional orthogonal woven structure

Minapoor

Ajeli

Tehrani

2018

Journal of Industrial Textiles

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Noncrimp three-dimensional orthogonal carbon weave is a specific type of three-dimensional woven fabric which is expected to have high performance as composite reinforcement. In this paper, two different orthogonal weaves in terms of carbon fiber tow type and binder yarns insertion density are produced, and a comprehensive study on the tensile strength of carbon composite reinforcements is conducted. The fiber volume fraction and mechanical performance are found to be affected by these two weave parameters. The fabric architecture changes due to different binder yarns’ insertion densities, influencing the stress wave propagation by preventing crack growth, thus leading to improve tensile strength of three-dimensional orthogonal reinforcement. Based on experimental weave parameters, a set of numerical compression tests are simulated by using a meso-scale finite element model. The results show that the model can predict the tensile strength of noncrimp three-dimensional orthogonal carbon composite reinforcements.

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“…Furthermore, note that the flexural fatigue subsequently applied to the impact load of 10 J intensifies the decrease in ultimate strength of the PPS-C laminate, while after undergoing impact energy of 20 J, the subsequent fatigue to which the test coupon is subjected causes it to recover that mechanical property. This fact is reported frequently in the literature (e.g., Tarpani et al, 2006) but only under purely tensile cyclic loads, when it is commonly called wearin effect. It is therefore interesting to observe this occurrence also under flexural loading conditions, in which a combination of tension and compression is developed.…”

Section: Fatigue Testmentioning

confidence: 84%

Compression After Impact and Fatigue of Reconsolidated Fiber-reinforced Thermoplastic Matrix Solid Composite Laminate

Tarpani

Canto

Saracura

et al. 2014

Procedia Materials Science

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Carbon fiber-reinforced poly-phenylene sulfide laminate coupons were impacted at low-energy in a drop-tower machine and subsequently fatigued in a four-point bending fixture. The doubly damaged test pieces were then hot-press reconsolidated and inspected nondestructively by vibrothermography to check their structural integrity. The residual mechanical properties of the laminate in both the as-damaged and as-repaired conditions were determined by compression loading with the in-plane strain fields determined via a digital image correlation system. Cross-section views of damaged and repaired samples were analyzed by light optical microscopy and correlated to residual mechanical properties, as were the digital image correlation and nondestructive test results. Based on the values of stiffness and ultimate strength of the repaired laminates, 10 J was inferred as the maximum impact energy at which it is worthwhile performing hot-press reconsolidation, in view of the applied fatigue history following impact.

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Mechanical performance of carbon-epoxy laminates. Part II: quasi-static and fatigue tensile properties

Cited by 11 publications

References 17 publications

Mechanical performance of carbon-epoxy laminates. Part I: quasi-static and impact bending properties

Mechanical performance of carbon-epoxy laminates. Part I: quasi-static and impact bending properties

Investigation into tensile strength of noncrimp three-dimensional orthogonal woven structure

Compression After Impact and Fatigue of Reconsolidated Fiber-reinforced Thermoplastic Matrix Solid Composite Laminate

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