scholarly journals Discrete Cohesive Zone Model to Simulate Static Fracture in Carbon Fiber Composites

2005 ◽  
Author(s):  
De Xie ◽  
Amit Salvi ◽  
Anthony Waas ◽  
Ari Caliskan
Keyword(s):  
Carbon Fiber ◽  
Cohesive Zone ◽  
Cohesive Zone Model ◽  
Fiber Composites ◽  
Zone Model ◽  
Carbon Fiber Composites ◽  
Static Fracture

Discrete Cohesive Zone Model to Simulate Static Fracture in 2D Triaxially Braided Carbon Fiber Composites

2006 ◽  
Vol 40 (22) ◽  
pp. 2025-2046 ◽  
Author(s):  
De Xie ◽  
Amit G. Salvi ◽  
Ce Sun ◽  
Anthony M. Waas ◽  
Ari Caliskan
Keyword(s):  
Carbon Fiber ◽  
Cohesive Zone ◽  
Cohesive Zone Model ◽  
Fiber Composites ◽  
Zone Model ◽  
Carbon Fiber Composites ◽  
Static Fracture

The quantitative analysis of tensile strength of additively manufactured continuous carbon fiber reinforced polylactic acid (PLA)

2019 ◽  
Vol 25 (10) ◽  
pp. 1624-1636 ◽  
Author(s):  
Hongbin Li ◽  
Taiyong Wang ◽  
Sanjay Joshi ◽  
Zhiqiang Yu
Keyword(s):  
Tensile Strength ◽  
Carbon Fiber ◽  
Fracture Mechanism ◽  
Cohesive Zone ◽  
Cohesive Zone Model ◽  
Zone Model ◽  
Fiber Reinforced ◽  
Continuous Fiber ◽  
Content Type ◽  
Continuous Carbon Fiber

Purpose Continuous fiber-reinforced thermoplastic composites are being widely used in industry, but the fundamental understanding of their properties is still limited. The purpose of this paper is to quantitatively study the effects of carbon fiber content on the tensile strength of continuous carbon fiber-reinforced polylactic acid (CCFRPLA) fabricated through additive manufacturing using the fused deposition modeling (FDM) process. Design/methodology/approach The strength of these materials is highly dependent on the interface that forms between the continuous fiber and the plastic. A cohesive zone model is proposed as a theoretical means to understand the effect of carbon fiber on the tensile strength properties of CCFRPLA. The interface formation mechanism is explored, and the single fiber pulling-out experiment is implemented to investigate the interface properties of CCFRPLA. The fracture mechanism is also explored by using the cohesive zone model. Findings The interface between carbon fiber and PLA plays the main role in transferring external load to other fibers within CCFRPLA. The proposed model established in this paper quantitatively reveals the effects of continuous carbon fiber on the mechanical properties of CCFRPLA. The experimental results using additively manufacturing CCFRPLA provide validation and explanation of the observations based on the quantitative model that is established based on the micro-interface mechanics. Research limitations/implications The predict model is established imagining that all the fibers and PLA form a perfect interface. While in a practical situation, only the peripheral carbon fibers of the carbon fiber bundle can fully infiltrate with PLA and form a transmission interface. These internal fibers that cannot contract with PLA fully, because of the limit space of the nozzle, will not form an effective interface. Originality/value This paper theoretically reveals the fracture mechanism of CCFRPLA and provides a prediction model to estimate the tensile strength of CCFRPLA with different carbon fiber contents.

Finite Element Simulation of Delamination in Carbon Fiber/Epoxy Laminate Using Cohesive Zone Model: Effect of Meshing Variation

2019 ◽  
Vol 964 ◽  
pp. 257-262
Author(s):  
Victor D. Waas ◽  
Mas Irfan P. Hidayat ◽  
Lukman Noerochim
Keyword(s):  
Finite Element ◽  
Carbon Fiber ◽  
Cohesive Zone ◽  
Composite Laminate ◽  
Cohesive Zone Model ◽  
Critical Force ◽  
Zone Model ◽  
Interface Elements ◽  
Dcb Specimen ◽  
Carbon Fiber Epoxy

Delamination or interlaminar fracture often occurs in composite laminate due to several factors such as high interlaminar stress, stress concentration, impact stress as well as imperfections in manufacturing processes. In this study, finite element (FE) simulation of mode I delamination in double cantilever beam (DCB) specimen of carbon fiber/epoxy laminate HTA/6376C is investigated using cohesive zone model (CZM). 3D geometry of DCB specimen is developed in ANSYS Mechanical software and 8-node interface elements with bi-linear formulation are employed to connect the upper and lower parts of DCB. Effect of variation of number of elements on the laminate critical force is particularly examined. The mesh variation includes coarse, fine, and finest mesh. Simulation results show that the finest mesh needs to be employed to produce an accurate assessment of laminate critical force, which is compared with the one obtained from exact solution. This study hence addresses suitable number of elements as a reference to be used for 3D simulation of delamination progress in the composite laminate, which is less explored in existing studies of delamination of composites so far.

scholarly journals MODELLING OF CRACK DEVELOPMENT PROCESSES IN COMPOSITE ELEMENTS BASED ON VIRTUAL CRACK CLOSURE TECHNIQUE AND COHESIVE ZONE MODEL

2020 ◽  
Vol 17 (35) ◽  
pp. 591-599
Author(s):  
Yulong; ; LI ◽  
Vasiliy N. DOBRYANSKIY ◽  
Alexander A. OREKHOV
Keyword(s):  
Composite Materials ◽  
Polymer Composite ◽  
Cohesive Zone ◽  
Cohesive Zone Model ◽  
Fiber Composites ◽  
Polymer Composite Materials ◽  
Zone Model ◽  
Virtual Crack Closure Technique ◽  
Closure Technique

Fiber composites based on polymer matrices are promising structural materials that meet high requirements for strength, reliability, durability, and hardness. Therefore, composite materials are widely used as structural materials for aerospace products. The problems associated with the destruction of fiber composites were relevant at all stages of technology development. A variety of reinforcing fibers and polymer binders, as well as reinforcement schemes, allow directional control of strength, stiffness, level of working temperatures and other properties of polymer composite materials. This article discusses a methodology for experimental determination of the mechanical properties of carbon-based fiber-reinforced polymer composite materials, including the determination of the interlayer fracture toughness under loading under separation conditions using the doublecantilever beam method (DCB) and the fracture toughness under transverse shear conditions using the ENF (End-Notched Flexure) method and interlayer strength. The test results of samples of polymer composite materials with a carbon reinforcing filler with different surface densities are presented. The experimental data were used to identify the parameters of the VCCT (Virtual Crack Closure Technique) and CZM (Cohesive Zone Model) closure models used to describe the development of cracks in the composites under consideration. It was found that the parameters determining the strength of layered composites are such characteristics as interlayer strength and crack resistance. It was found that the decrease in the strength of individual layers of the composite does not always affect the current stress state of the entire structure, which is often difficult to detect experimentally, but can significantly affect the further behavior of the object under study provided that the crack develops further.

Material and adhesive effect in adhesively-bonded composite stepped-lap joints

2020 ◽  
Vol 234 (13) ◽  
pp. 1967-1979
Author(s):  
RFN Brito ◽  
RDSG Campilho ◽  
RDF Moreira ◽  
IJ Sánchez-Arce
Keyword(s):  
Carbon Fiber ◽  
Cohesive Zone ◽  
Cohesive Zone Model ◽  
Lap Joints ◽  
Fiber Reinforced Polymer ◽  
Carbon Fiber Reinforced Polymer ◽  
Zone Model ◽  
Fiber Reinforced ◽  
Reinforced Polymer ◽  
Carbon Fiber Reinforced

Adhesive bonding is a predominant bonding technique in the aeronautical and automotive industries. Cohesive zone models, used together with the finite element method, are a viable tool to predict the strength of adhesive joints. The main objective of this study is to evaluate experimentally and numerically (by cohesive zone model) the mechanical performance of carbon-fiber reinforced polymer stepped-lap bonded joints submitted to tensile loads, for different overlap lengths ( LO) and adhesives. The failure mode analysis showed a predominant failure type for all adhesives and good correspondence with the numerical predictions. Normalized peel ( σy) and shear ( τxy) stresses in the adhesive highly increased with LO, which then reflected on different maximum load ( Pm) evolution with LO, depending on the adhesive's ductility. The damage variable SDEG (stiffness degradation) was also evaluated and emphasized on the smaller damage zone at Pm for the brittle adhesive. A significant geometry and material effect were found on Pm of the stepped-lap joints, with benefit for large LO. In this regard, cohesive zone model revealed to be a suitable tool in determining the behavior of different joints. Comparison with joints with aluminum showed that, provided that no carbon-fiber reinforced polymer delamination occurs, stepped-lap joints between carbon-fiber reinforced polymer adherends give better results due to the higher composite stiffness.

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