Damage mechanisms and failure modes in cross-ply laminates under monotonic tensile loading: The influence of fiber sizing

Subramanian, S.; Lesko, John J.; Reifsnider, KL; Stinchcomb, WW

doi:10.1007/bf00568285

Cited by 6 publications

(4 citation statements)

References 16 publications

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“…This delamination initiation process in laminates composite materials is a result of competing factors, the main being the stress concentrations at the interface at the laminate's edges and the presence of weak (resin-rich) areas at the interface. So, in some cases delamination can start away from the edges; Such behaviour was reported by Subramanian et al [25] presenting experimental results for cross-ply laminate specimens, where multiple locations of delamination were observed in different specimens.…”

Section: Random Models-use Of Stochastic Cohesive Elementsmentioning

confidence: 62%

Interaction of Matrix Cracking and Delamination in Cross-ply Laminates: Simulations with Stochastic Cohesive Zone Elements

2010

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Two main damage mechanisms of laminates-matrix cracking and inter-ply delaminationare closely linked together (Joshi and Sun 1). This paper is focussed on interaction between matrix cracking and delamination failure mechanisms in CFRP crossply laminates under quasi-static tensile loading. In the first part of the work, a transverse crack is introduced in 90o layers of the cross-ply laminate [01/904/01], and the stresses and strains that arise due to tensile loading are analyzed. In the second part, the cohesive zone modelling approach where the constitutive behaviour of the cohesive elements is governed by traction-displacement relationship is employed to deal with the problem of delamination initiation from the matrix crack introduced in the 90o layers of the laminate specimen. Additionally, the effect of microstructural randomness, exhibited by CFRP laminates on the damage behaviour of these laminates is also accounted for in simulations. This effect is studied in numerical finite-element simulations by introducing stochastic cohesive zone elements. The proposed damage modelling effectively simulated the interaction between the matrix crack and delamination and the variations in the stresses, damage and crack lengths of the laminate specimen due to the microstructural randomness.

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Section: Random Models-use Of Stochastic Cohesive Elementsmentioning

confidence: 62%

Interaction of Matrix Cracking and Delamination in Cross-ply Laminates: Simulations with Stochastic Cohesive Zone Elements

2010

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“…28 To meet specified service and functional requirements cutouts/holes can have various shapes and sizes. While the fiber/matrix system and fiber/matrix interface constitute an obvious impact on damage progression mechanism, [29][30][31] some design factors, viz., stacking sequence of the laminate, shape, size and location of the cutout on the component play a significant role on stress distribution pattern, damage initiation and propagation. [32][33][34]…”

Section: Assembly and Joining Of Composite Componentmentioning

confidence: 99%

An overview of mechanical properties and failure mechanism of FRP laminates with hole/cutout

Gupta

Pal

Ray

2023

J of Applied Polymer Sci

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Aerospace and aircraft companies follow a pyramidal structure of testing, ranging from specimen tests to full-scale structure tests, for aircraft structural design. At the base level, open hole strength evaluation is one of the qualification procedures for composite components. The holes are made in the structural components to accommodate bolts and rivets in order to assemble the parts into a single unit. Holes in the component are also used to fulfill functional requirements, such as the passage of wire bundles. FRP components are sensitive to these holes/cutouts as substantial decrement in the strength is observed in several experiments. The degradation in the strength of the component is due to stress concentration around the hole. This review aims to comprehend the effect of the hole on the mechanical properties of FRP laminates; the emphasis is mainly on CFRP laminates and experimental results. An overview of tensile, compressive, flexural and post buckling properties of laminates with the hole is presented to aid in the optimal design of the component. Finally, the failure mechanism during loading is discussed and described through a graphical presentation.

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“…However, due to the brittle nature of carbon fibers, the carbon-fiber tows are inherently easy to generate fuzz for during processing and thus require protection [ 21 ]. In general, the surfaces of carbon fibers are protected by coating them with a thin layer of sizing, which can also improve the wettability as well as processibility of carbon fibers [ 22 , 23 , 24 ]. The most common type of sizing agent for carbon fibers is based on epoxy [ 25 , 26 ].…”

Section: Introductionmentioning

confidence: 99%

Effects of Styrene-Acrylic Sizing on the Mechanical Properties of Carbon Fiber Thermoplastic Towpregs and Their Composites

et al. 2018

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Thermoplastic towpregs are convenient and scalable raw materials for the fabrication of continuous fiber-reinforced thermoplastic matrix composites. In this paper, the potential to employ epoxy and styrene-acrylic sizing agents was evaluated for the making of carbon fiber thermoplastic towpregs via a powder-coating method. The protective effects and thermal stability of these sizing agents were investigated by single fiber tensile test and differential scanning calorimetry (DSC) measurement. The results indicate that the epoxy sizing agent provides better protection to carbon fibers, but it cannot be used for thermoplastic towpreg processing due to its poor chemical stability at high temperature. The bending rigidity of the tows and towpregs with two styrene-acrylic sizing agents was measured by cantilever and Kawabata methods. The styrene-acrylic sized towpregs show low torque values, and are suitable for further processing, such as weaving, preforming, and winding. Finally, composite panels were fabricated directly from the towpregs by hot compression molding. Both of the composite panels show superior flexural strength (>400 MPa), flexural modulus (>63 GPa), and interlaminar shear strength (>27 MPa), indicating the applicability of these two styrene-acrylic sizing agents for carbon fiber thermoplastic towpregs.

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Damage mechanisms and failure modes in cross-ply laminates under monotonic tensile loading: The influence of fiber sizing

Cited by 6 publications

References 16 publications

Interaction of Matrix Cracking and Delamination in Cross-ply Laminates: Simulations with Stochastic Cohesive Zone Elements

Interaction of Matrix Cracking and Delamination in Cross-ply Laminates: Simulations with Stochastic Cohesive Zone Elements

An overview of mechanical properties and failure mechanism of FRP laminates with hole/cutout

Effects of Styrene-Acrylic Sizing on the Mechanical Properties of Carbon Fiber Thermoplastic Towpregs and Their Composites

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