Journal articles: 'Interlaminar and intralaminar damage'

1

Keršienė, Neringa, and Antanas Žiliukas. "INTERLAMINAR AND INTRALAMINAR DAMAGE MECHANISMS OF IMPACT RESISTANT AIRCRAFT MATERIALS UNDER LOW‐ENERGY IMPACT." Aviation 10, no. 3 (September 30, 2006): 3–8. http://dx.doi.org/10.3846/16487788.2006.9635933.

Full text

Abstract:

For low-velocity impact, drop‐weight impact tests performed by EADS (European Aeronautic Defence and Space Company) Corporate Research Center Germany have been carried out for 2‐D woven E‐Glass/epoxy composite systems to determine material response as a function of absorbed energy and damaged area. Nondestructive techniques like visual inspection and analysis of impact response of the woven fabric laminates at different energy levels are utilized to assess the initiation and progression of interlaminar and intralaminar damage. The dominant damage modes for woven reinforced composite systems were found to be matrix cracking with branching into the adjacent layers, intralaminar cracking by mixture of localized matrix shear and matrix/fibre interfacial debonding, front face indentation, and back face fibre damage. The use of woven fabrics as opposed to cross‐ply unidirectional prepreg tapes is specifically discussed from the point view of microstructure and property. In the case of low‐energy impact, damage resistance under impact loading of woven and multiaxial non‐crimp fabrics is presented and compared. The assumption that shear‐response dominated for woven reinforced composite systems was found to be in good agreement with the experimental results.

APA, Harvard, Vancouver, ISO, and other styles

2

Bruno, Domenico, Fabrizio Greco, and Paolo Lonetti. "Interaction Between Interlaminar and Intralaminar Damage in Fiber-Reinforced Composite Laminates." International Journal for Computational Methods in Engineering Science and Mechanics 9, no. 6 (September 30, 2008): 358–73. http://dx.doi.org/10.1080/15502280802365824.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Li, N., P. H. Chen, and Q. Ye. "A damage mechanics model for low-velocity impact damage analysis of composite laminates." Aeronautical Journal 121, no. 1238 (March 6, 2017): 515–32. http://dx.doi.org/10.1017/aer.2017.6.

Full text

Abstract:

ABSTRACTA method was developed to predict numerically the damage of composite laminates with multiple plies under low-velocity impact loading. The Puck criterion for 3D stress states was adopted to model the intralaminar damage including matrix cracking and fibre breakage, and to obtain the orientation of the fracture plane due to matrix failure. According to interlaminar delamination mechanism, a new delamination criterion was proposed. The influence of transverse and through-thickness normal stress, interlaminar shear stress and damage conditions of adjacent plies on delamination was considered. In order to predict the impact-induced damage of composite laminates with more plies quickly and efficiently, an approach, which can predict the specific damage of several plies in a single solid element, was proposed by interpolation on the strains of element integration points. Moreover, the proposed model can predict specific failure modes. A good agreement between the predicted delamination shapes and sizes and the experimental results shows correctness of the developed numerical method for predicting low-velocity impact damage on composite laminates.

APA, Harvard, Vancouver, ISO, and other styles

4

Liao, BB, and PF Liu. "Finite element analysis of dynamic progressive failure properties of GLARE hybrid laminates under low-velocity impact." Journal of Composite Materials 52, no. 10 (August 10, 2017): 1317–30. http://dx.doi.org/10.1177/0021998317724216.

Full text

Abstract:

This paper aims to study dynamic progressive failure properties of glass fiber composite/aluminium hybrid laminates under low-velocity impact. Intralaminar damage models using Puck failure criteria and strain-based damage evolution laws for composite layers are implemented by developing finite element codes using ABAQUS-VUMAT (user dynamic material subroutine), the interface delamination is simulated by bilinear cohesive model in ABAQUS and the mechanical properties of aluminium layers are described using the Johnson-Cook model. Effects of different layer thickness and impact energy on the impact force–time/displacement curves of glass fiber composite/aluminium laminates under low-velocity impact are discussed. Besides, damage evolution behaviors of matrix and delamination interface are explored. Finally, energy dissipation mechanisms due to intralaminar dynamic progressive failure, interlaminar delamination of composite layers and plastic deformation of aluminium layers are studied. Relatively good agreement is obtained between experimental and numerical results.

APA, Harvard, Vancouver, ISO, and other styles

5

Duplessis Kergomard, Y., J. Renard, A. Thionnet, and C. Landry. "Intralaminar and interlaminar damage in quasi-unidirectional stratified composite structures: Experimental analysis." Composites Science and Technology 70, no. 10 (September 30, 2010): 1504–12. http://dx.doi.org/10.1016/j.compscitech.2010.05.006.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Hassoon, Omar H., Mayyadah S. Abed, Jawad K. Oleiwi, and M. Tarfaoui. "Experimental and numerical investigation of drop weight impact of aramid and UHMWPE reinforced epoxy." Journal of the Mechanical Behavior of Materials 31, no. 1 (January 1, 2022): 71–82. http://dx.doi.org/10.1515/jmbm-2022-0008.

Full text

Abstract:

Abstract Due to their characteristics such as weight/strength ratio and absorbed energy, the widespread use of composite materials in the last decades engorged the companies to exploit these materials invariant applications like the aerospace, automobile, and marine hull. However, there are some obstructs to the use of these materials that may constrain that. This came from the fact, that composite materials suffer from different damages modes that occur during loading and can be lead to catastrophic failure in their structure, such as intralaminar and interlaminar damage. Consequently, this motivated the researchers to study its behavior considering different damage modes and at different loading states. This work performed a finite element simulation using the Abaqus program of low-velocity drop impact for epoxy reinforced with Kevlar 49 and Ultra High Molecular Weight Polyethylene (UHMWPE) with different thicknesses and number of layers. A user-defined material VUMAT subroutine-based progressive damage model, and the Hashin failure criteria implemented in Abaqus Explicit finite element code had been utilized in this work. In Addition, the interlaminar damage models depend on the cohesive zone model (CZM). The numerical simulation results were compared with the experiments data to confirm the reliability of the numerical model.

APA, Harvard, Vancouver, ISO, and other styles

7

Zou, Z., S. R. Reid, S. Li, and P. D. Soden. "Modelling Interlaminar and Intralaminar Damage in Filament-Wound Pipes under Quasi-Static Indentation." Journal of Composite Materials 36, no. 4 (February 2002): 477–99. http://dx.doi.org/10.1177/0021998302036004539.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

BALZANI, CLAUDIO, and WERNER WAGNER. "NUMERICAL TREATMENT OF DAMAGE PROPAGATION IN AXIALLY COMPRESSED COMPOSITE AIRFRAME PANELS." International Journal of Structural Stability and Dynamics 10, no. 04 (October 2010): 683–703. http://dx.doi.org/10.1142/s0219455410003683.

Full text

Abstract:

In the design phase of stringer-stiffened composite airframe panels, it is a key issue to exploit material reserves as far as possible to create lighter and safer aircraft. A recent approach is to apply postbuckling design — standard for metallic panels — also to composite parts. This work focusses on the development of a simulation procedure which accurately predicts the postbuckling response of composite panels while accounting for damage propagation. For this purpose we employ a robust shell element formulation which allows for arbitrary stacking sequences as well as a variable location of the reference plane. A ply discount model is incorporated to account for intralaminar damage growth. The cohesive zone approach is implemented in a so-called interface element to predict interlaminar damage growth, respective skin–stringer separation. The numerical model is validated via a numerical example with experimental evidence.

APA, Harvard, Vancouver, ISO, and other styles

9

Meon, M. S., N. H. Mohamad Nor, S. Shawal, J. B. Saedon, M. N. Rao, and K. U. Schröder. "On the Modelling Aspect of Low-Velocity Impact Composite Laminates." journal of Mechanical Engineering 17, no. 2 (July 15, 2020): 13–25. http://dx.doi.org/10.24191/jmeche.v17i2.15297.

Full text

Abstract:

Composites suffer a degradation of structural stiffness due to various types of impact loading resulting in damage which is difficult to observe from the surface of the structure. The paper deals with the finite element model (FEM) to study the possible modelling procedures in low-velocity impact (LVI) and failure mechanism of carbon fiber reinforced polymer (CFRP) composite laminate of CCF300/epoxy and its structural responses. In finite element calculation, a proposed three-dimensional progressive damage model is used to determine the intralaminar damage, whereas the cohesive contact formulation is employed to analyse the interlaminar damage. The failure model performances are validated and verified based on different boundary conditions while maintaining the impact energy. Through simulation, the variation in boundary conditions significantly changes the structural responses and energy absorption of the laminates. It is hoped this study will be a great tool in determining the different composite impact scenarios.

APA, Harvard, Vancouver, ISO, and other styles

10

Townsend, Patrick, Juan Carlos Suárez, Paz Pinilla, and Nadia Muñoz. "Insertion of a Viscoelastic Layer to Reduce the Propagation of Energy by Vertical Impacts of Slamming in Planing Hull Vessels." Key Engineering Materials 889 (June 16, 2021): 65–70. http://dx.doi.org/10.4028/www.scientific.net/kem.889.65.

Full text

Abstract:

For the design of vessels built by GFRP laminates, an insert with a viscoelastic layer is proposed to reduce the spread of damage produced by the vertical impact of the ship's bottom with the sea or slamming phenomenon. Using vertical drops-weight impact machine that reproduce the energy inferred to the panel during navigation, the propagation of the damage of OoA cured prepreg panels is studied comparing it with modified panels with insertion of viscoelastic layer. The use of acceleration data reading allows the benefits of viscoelastic modification during impact to be quantified through the developed formulation. The force, displacement and energy returned by the panel after impact have also been quantified, which does not become intralaminar and interlaminar damage. It is shown that under 40 joules of impact, the viscoelastic sheet has its best ability to return energy and above 130 joules it loses its capacity.

APA, Harvard, Vancouver, ISO, and other styles

11

Nikbakht, Masood, Hossein Hosseini Toudeshky, and Bijan Mohammadi. "Experimental validation of an empirical nonlinear shear failure model for laminated composite materials." Journal of Composite Materials 51, no. 16 (September 19, 2016): 2331–45. http://dx.doi.org/10.1177/0021998316669992.

Full text

Abstract:

This paper aims to develop a numerical nonlinear progressive damage model for laminated composite materials considering in-plane and out-of-plane shear stresses in combination with cohesive interface elements to predict the structural response and the failure mechanisms of laminated composite materials. For this purpose, the constitutive models for intralaminar and interlaminar damage modes have been developed as a numerical code by a UMAT subroutine and implemented in commercial finite element software. This model, which is based on the continuum damage mechanics approach, enables to predict the gradual degradation of material properties with five distinct damage parameters for different failure modes; three of these damage factors apply the shear damage contribution as a separate damage mode by a separate damage factor into the model and characterize it by shear damage dissipation energy, and two parameters for fiber and matrix in transverse directions. Also, a series of experiments have been performed to characterize and validate the nonlinear behavior of glass/epoxy laminate. This model is used to predict the behavior and the final strength of open-hole tension specimens. A reasonably good agreement was also achieved between numerical predictions and experimental observations in terms of shapes, orientations and sizes of individual intraply damages induced around the notch and also the final strength of open-hole tension specimen.

APA, Harvard, Vancouver, ISO, and other styles

12

Airoldi, Alessandro, Chiara Mirani, and Lucia Principito. "A bi-phasic modelling approach for interlaminar and intralaminar damage in the matrix of composite laminates." Composite Structures 234 (February 2020): 111747. http://dx.doi.org/10.1016/j.compstruct.2019.111747.

Full text

APA, Harvard, Vancouver, ISO, and other styles

13

Hu, Ping, Ditho Pulungan, Ran Tao, and Gilles Lubineau. "An experimental study on the influence of intralaminar damage on interlaminar delamination properties of laminated composites." Composites Part A: Applied Science and Manufacturing 131 (April 2020): 105783. http://dx.doi.org/10.1016/j.compositesa.2020.105783.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Ji, W., and A. M. Waas. "Progressive failure analysis for the interaction of interlaminar and intralaminar failure modes in composite structures with an initial delamination." Aeronautical Journal 117, no. 1187 (January 2013): 71–85. http://dx.doi.org/10.1017/s0001924000007764.

Full text

Abstract:

AbstractThis paper is concerned with the development of a failure initiation and progressive failure analysis (PFA) method for advanced composite structures. The present PFA model is capable of predicting interactive out-of-plane and in-plane failure modes observed in fiber reinforced composite laminates including interlaminar behavior and matrix microdamage at the mesoscale. A probability analysis tool is coupled with the PFA to account for uncertainty in modelling parameters caused by material variability and manufacturing inconsistencies. The progressive damage response of a laminated composite panel with an initial delamination is studied and used to demonstrate the PFA modelling framework that is presented here.

APA, Harvard, Vancouver, ISO, and other styles

15

Toubia, Elias A., Sadra Emami, and Donald Klosterman. "Failure mechanism of woven roving fabric/vinyl ester composites in freeze–thaw saline environment." Journal of Composite Materials 51, no. 23 (November 30, 2016): 3269–80. http://dx.doi.org/10.1177/0021998316681860.

Full text

Abstract:

This experimental study investigates the degradation mechanisms of a glass fiber-reinforced plastic material commonly used in civil engineering applications. A substantial reduction in tensile, shear, and compression properties was observed after 100 days of freeze–thaw cycling in saline environment (−20℃ to 20℃). Non-destructive inspection techniques were progressively conducted on unexposed (ambient condition) and exposed (conditioned) specimens. The dynamic mechanical analysis showed permanent decrease in storage modulus that was attributed to physical degradation of the polymer and/or fiber–matrix interface. This indicated the formation of internal cracks inside the exposed glass fiber-reinforced plastic laminate. The 3D X-ray tomography identified preferred damage sites related to intralaminar and interlaminar cracks. The ultrasonic C-scan and optical microscopy showed the nature of the damage and fibers fracture. The thermal cycling events degraded the matrix binding the warp and fill fibers, thus impairing the structural integrity of the cross-ply laminate. The result of this work could benefit a multi-scale durability and damage tolerance model to predict the material state of composite structures under typical service environments.

APA, Harvard, Vancouver, ISO, and other styles

16

Aveiga, David, and Marcelo L. Ribeiro. "A Delamination Propagation Model for Fiber Reinforced Laminated Composite Materials." Mathematical Problems in Engineering 2018 (June 19, 2018): 1–9. http://dx.doi.org/10.1155/2018/1861268.

Full text

Abstract:

The employment of composite materials in the aerospace industry has been gradually considered due to the fundamental lightweight and strength characteristics that this type of materials has. The science material and technological progress reached matched perfectly with the requirements for high-performance materials in aircraft and aerospace structures; thus, the development of primary structure elements applying composite materials became something very convenient. It is extremely important to pay attention to the failure modes that influence composite materials performances, since these failures lead to a loss of stiffness and strength of the laminate. Delamination is a failure mode present in most of the damaged structures and can be ruinous, considering that the evolution of interlaminar defects can carry the structure to a total failure followed by its collapse. The present work aims at the development of a delamination propagation model to estimate a progressive interlaminar delamination failure in laminated composite materials and to allow the prediction of material’s degradation due to delamination phenomenon. Experimental data, available at literature, was considered to determine some model parameters, like the strain energy release rate, using GFRPs laminated composites. This new delamination propagation model was implemented as subroutines in FORTRAN language (UMAT-User Material Subroutine) with formulations based on the Fracture Mechanics and Continuum Damage Mechanics. Finally, the UMAT subroutine was complemented with an intralaminar model and compiled beside the commercial Finite Element (FE) software ABAQUS™.

APA, Harvard, Vancouver, ISO, and other styles

17

Townsend, Patrick, Juan C. Suárez-Bermejo, and Álvaro Rodríguez-Ortíz. "A Methodology for Evaluating the Progression of Damage in a Glass Fibre Reinforced Polymer Laminate Subjected to Vertical Weight Drop Impacts." Polymers 13, no. 13 (June 29, 2021): 2131. http://dx.doi.org/10.3390/polym13132131.

Full text

Abstract:

This study describes a methodology that allows evaluating the behavior of a glass fibre reinforced polymer (GFRP) laminate impacted by a vertical weight drop, analyzing the damage that occurred inside. The purpose of the designers was, by means of characterization tests of the curing processes, evaluation of the cohesion of a particular laminate, application of vertical tests by weight drops and with the use of the readings of an accelerometer in a single direction, know the trend of how intralaminar breaks in the matrix and interlaminar breaks between layers occur. It is proposed to establish the behavior of the laminate before the tests by analyzing curing times, for after the tests by observations with penetrating fluorescent inks. This allows researchers to know the response of the laminate to the loads imposed on the applied structure. For the tests, prepreg material cured outside the autoclave in an oven was used and qualitative quantification of the damage by observing sections of the tested material infiltrated with penetrating fluorescent ink exposed to ultraviolet light.

APA, Harvard, Vancouver, ISO, and other styles

18

Gao, Wei, Zhiqiang Yu, Aijie Ma, and Zhangxin Guo. "Numerical simulation of composite grid sandwich structure under low-velocity impact." Science and Engineering of Composite Materials 29, no. 1 (January 1, 2022): 516–28. http://dx.doi.org/10.1515/secm-2022-0176.

Full text

Abstract:

Abstract The low-velocity impact finite element model of the carbon fiber-reinforced composite grid sandwich structure was established by ABAQUS. Its panels and grid are both carbon fiber-reinforced composite laminates. The constitutive relation of composite laminates is written into the VUMAT user subroutine using the Fortran language. Simulation of intralaminar failure behavior of composite laminates using the three-dimensional Hashin failure criterion. The quadratic stress criterion and the B-K energy criterion were used to simulate the interlaminar failure behavior, and the delamination damage of the composite panel and the interface debonding damage were simulated. The finite element models of four different types of composite grid sandwich structures, including quadrilateral configuration, triangular configuration, mixed configuration, and diamond configuration, were established. The influence of the single grid width and the height of the grid on the impact resistance of each composite grid configuration was studied. Compared with other geometric configurations, triangular grid sandwich structure provides the best energy absorption characteristics, and T-6-10 has the highest fracture absorption energy (15816.46 mJ). The damage propagation law of carbon fiber-reinforced composite grid sandwich structure under impact load is analyzed.

APA, Harvard, Vancouver, ISO, and other styles

19

Tan, K. T., N. Watanabe, and Y. Iwahori. "Impact Damage Resistance, Response, and Mechanisms of Laminated Composites Reinforced by Through-Thickness Stitching." International Journal of Damage Mechanics 21, no. 1 (January 13, 2011): 51–80. http://dx.doi.org/10.1177/1056789510397070.

Full text

Abstract:

In this article, the study of impact damage of laminated composites reinforced by through-thickness stitching is investigated and presented in threefold. Specimens stitched with varying stitch density and stitch thread thickness are subjected to low-velocity impact via a drop-weight machine. Impact damage resistance is first studied by examining the extent of delamination area in damaged specimens using ultrasonic C-scan analysis. It is revealed that higher stitch density is more capable of impeding delamination growth by arresting cracks at closer interval and suppressing crack propagation. The use of thicker stitch thread offers slight improvement to damage resistance by marginal reduction in delamination propagation, and is more pertinent at high impact energy levels. Impact damage response is then analyzed from the impact history response curves of impacted laminates. The impact response of load–time graphs demonstrates that the onset of delamination is not influenced by stitch density and stitch thread thickness, but the maximum residual impact force is related to the delamination size of the laminates, which is sequentially related to stitch parameters. Finally, impact damage mechanisms are elucidated by employing X-ray radiography and micro-Computed Tomography to reveal subsurface damages, primarily dominated by intralaminar matrix cracks, interlaminar delamination, and stitch fiber/matrix debonding. It is revealed that stitches act as crack initiation sites, due to the presence of weak resin-rich pockets around stitch threads, thus inadvertently resulting in densely stitched composites having more stitch-induced matrix cracks upon impact loading. Contrarily, specimens with higher stitch density and thread thickness are more capable of impeding delamination growth by effectively bridging delamination cracks and arresting crack propagation. Principal mechanisms responsible for impact resistance performance of stitching namely crack arresting and crack bridging are presented and discussed.

APA, Harvard, Vancouver, ISO, and other styles

20

Saeedifar, Milad, Mehdi Ahmadi Najafabadi, Dimitrios Zarouchas, Hossein Hosseini Toudeshky, and Meisam Jalalvand. "Clustering of interlaminar and intralaminar damages in laminated composites under indentation loading using Acoustic Emission." Composites Part B: Engineering 144 (July 2018): 206–19. http://dx.doi.org/10.1016/j.compositesb.2018.02.028.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Khan, Sanan H., and Ankush P. Sharma. "Progressive damage modeling and interface delamination of cross-ply laminates subjected to low-velocity impact." Journal of Strain Analysis for Engineering Design 53, no. 6 (June 22, 2018): 435–45. http://dx.doi.org/10.1177/0309324718780598.

Full text

Abstract:

In this study, Hashin failure criteria were enhanced with Puck’s action plane concept to develop a user material model that can accurately predict the damage development inside the composite laminate when it is subjected to low-velocity impact. A simple cross-ply laminate [0/90]s was chosen to demonstrate the applicability of the material model. Experiments were also performed to observe the real behavior of the laminate. A good correlation between the experiment and simulation results was obtained in terms of peak force and displacement. However, the model under-predicted the absorbed energy, but the discrepancy decreased with the increase in impact energy. Moreover, the interface delamination study was performed by comparing the signatures in post-impact samples of the experiment and numerical simulation. It was observed that the experimentally detected delamination area was closely predicted by the simulation. It was further noticed that the top interface delamination increases faster than bottom interface delamination. Furthermore, the total energy absorbed by the laminates in intralaminar and interlaminar damage modes and friction effects were found to be closely matching with the final absorbed energy of the laminate. Hence, it was seen that the developed finite element model was able to closely capture the behavior occurring in experiments.

APA, Harvard, Vancouver, ISO, and other styles

22

Tasdemir, Burcu, and Demirkan Coker. "Fatigue and static damage in curved woven fabric carbon fiber reinforced polymer laminates." Journal of Composite Materials 56, no. 11 (March 25, 2022): 1693–708. http://dx.doi.org/10.1177/00219983221078787.

Full text

Abstract:

Failure mechanisms of curved cross-ply laminates under static and fatigue loading have been studied extensively, but the examination of fabric laminates which are the most commonly used ply type in curved supports in airplane wing structures is lacking. In this study, unidirectional (UD) and fabric carbon fiber reinforced polymer (CFRP) laminates are examined to elucidate the failure initiation mechanisms of laminated composites under fatigue and static loading. The crucial point of the research is applying the analyses using fabric laminate with a currently used stacking sequence in commercial airplanes. In addition to the fabric laminate, UD laminate is also included in the research to compare the real complex stacking with the simplest stacking. In the experiments, it is observed that both static and fatigue failures initiate roughly at the maximum radial stress location (approximately 35% of the thickness from the inner radius). For UD laminates, there is no visible difference between the failure mechanisms under static and fatigue loadings. However, for fabric laminates, fatigue failure is observed to occur as a single major crack at the maximum radial stress location as in UD laminates, whereas static failure is observed to occur as multiple diffusive cracks at the maximum radial stress location. Additionally, cracks grow mostly as intralaminar cracks connected with regions of occasional interlaminar cracks.

APA, Harvard, Vancouver, ISO, and other styles

23

Pietropaoli, Elisa, and Aniello Riccio. "A Global/Local Finite Element Approach for Predicting Interlaminar and Intralaminar Damage Evolution in Composite Stiffened Panels Under Compressive Load." Applied Composite Materials 18, no. 2 (April 15, 2010): 113–25. http://dx.doi.org/10.1007/s10443-010-9135-1.

Full text

APA, Harvard, Vancouver, ISO, and other styles

24

Amir, A. N., H. Ghazali, H. Wang, L. Ye, N. A. Fadi, W. F. F. W. Ali, and R. Yusoff. "Fracture energy for orthogonal cutting in unidirectional CFRP at different cutting directions." IOP Conference Series: Materials Science and Engineering 1217, no. 1 (January 1, 2022): 012011. http://dx.doi.org/10.1088/1757-899x/1217/1/012011.

Full text

Abstract:

Abstract A unidirectional carbon fibre reinforced polymer (CFRP) laminate is a composite material made up of strong parallel carbon fibres incorporated in a polymer matrix such as epoxy to provide high stiffness and strength in the fibre direction of the laminate. Unfortunately, the interlaminar or intralaminar plane of this material has a low resistance to damages as the fracture toughness of a unidirectional CFRP laminate is related to the energy dissipation during the orthogonal cutting. The aim of this study is on cutting a unidirectional CFRP along the longitudinal or transverse directions, characterizing orthogonal cutting forces and the related fracture energy. Orthogonal cutting is performed using braised carbide tools for a range of cutting depth of 10-100 ³m with a rake angle of 30° to quantify the cutting forces and to observe the fracture mechanisms. The fibre orientations have a significant impact on surface bouncing-back. For some fibre orientations, the energy balance model is applicable, deducting the reasonable value of fracture toughness due to high normal force (F t). Fibre subsurface damage and cutting forces during cutting are found to be strongly influenced by the cutting depth. The input energy of cutting is released in form of new surface energy, fibre breakage, high bending energy, and chip fracture energy.

APA, Harvard, Vancouver, ISO, and other styles

25

Liu, P. F., J. Yang, B. Wang, Z. F. Zhou, and J. Y. Zheng. "A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission." Journal of Failure Analysis and Prevention 15, no. 1 (November 11, 2014): 101–21. http://dx.doi.org/10.1007/s11668-014-9901-8.

Full text

APA, Harvard, Vancouver, ISO, and other styles

26

Tan, W., F. Naya, L. Yang, T. Chang, B. G. Falzon, L. Zhan, J. M. Molina-Aldareguía, C. González, and J. Llorca. "The role of interfacial properties on the intralaminar and interlaminar damage behaviour of unidirectional composite laminates: Experimental characterization and multiscale modelling." Composites Part B: Engineering 138 (April 2018): 206–21. http://dx.doi.org/10.1016/j.compositesb.2017.11.043.

Full text

APA, Harvard, Vancouver, ISO, and other styles

27

Wei, Guangkai, Kunkun Fu, and Yuan Chen. "Crashworthiness and Failure Analyses of FRP Composite Tubes under Low Velocity Transverse Impact." Sustainability 15, no. 1 (December 21, 2022): 56. http://dx.doi.org/10.3390/su15010056.

Full text

Abstract:

Currently, FRP composite tubes are drawing increasing attention in many industrial applications, due to their excellent mechanical and lightweight properties, with reduced energy consumption and enhanced sustainability. This study investigates the failure mechanisms and crashworthiness performance of glass and carbon fibre reinforced polymer (GFRP and CFRP) composite tubes under low velocity transverse impact. Finite element methods were developed to establish numerical models to predict the failure responses of FRP composite tubes with a complex ply sequence of both woven and unidirectional layers. In the modelling, continuum damage mechanics and cohesive zone method were used to calculate the intralaminar and interlaminar failure behaviours, respectively, in FRP composite tubes. The numerical models were validated by corresponding experiments, and the effects of the impact energy and material type were investigated. The experimental results show that the initial impact energy does not significantly affect the specific energy absorption (SEA) and peak force (PF) of GFRP composite tubes, and the SEA and PF are generally around 0.5 kJ/kg and 600 N, respectively, when the impact energy varies from 10 J to 50 J. Failure mechanism analyses show that GFRP tubes and CFRP tubes with totally unidirectional plies present global bending deformation with significant matrix damage, and CFRP tubes with “hybrid layer type” exhibit local penetration with severe fibre and matrix damage. The crashworthiness analyses indicate that CFRP tubes perform better in SEA while GFRP tubes possess smaller PF when subjected to low velocity transverse impact.

APA, Harvard, Vancouver, ISO, and other styles

28

Rezasefat, Mohammad, Sandro Campos Amico, Marco Giglio, and Andrea Manes. "A Numerical Study on the Influence of Strain Rate in Finite-Discrete Element Simulation of the Perforation Behaviour of Woven Composites." Polymers 14, no. 20 (October 12, 2022): 4279. http://dx.doi.org/10.3390/polym14204279.

Full text

Abstract:

Predicting the perforation limit of composite laminates is an important design aspect and is a complex task due to the multi-mode failure mechanism and complex material constitutive behaviour required. This requires high-fidelity numerical models for a better understanding of the physics of the perforation event. This work presents a numerical study on the perforation behaviour of a satin-weave S2-glass/epoxy composite subjected to low-velocity impact. A novel strain-rate-dependent finite-discrete element model (FDEM) is presented and validated by comparison with experimental data for impacts at several energies higher and lower than their perforation limit. The strain rate sensitivity was included in the model by developing a novel user-defined material model, which had a rate-dependent bilinear traction separation cohesive behaviour, implemented using a VUSDFLD subroutine in Abaqus/Explicit. The capability of the model in predicting the perforation limit of the composite was investigated by developing rate-sensitive and insensitive models. The results showed that taking the strain rate into account leads to more accurate predictions of the perforation limit and damage morphology of the laminate subjected to impacts at different energies. The experimental penetration threshold of 89 J was estimated as 79 J by the strain-rate-sensitive models, which was more accurate compared to 52 J predicted by the strain-rate-insensitive model. Additionally, the coupling between interlaminar and intralaminar failure modes in the models led to a more accurate prediction of the delamination area when considering the rate sensitivity.

APA, Harvard, Vancouver, ISO, and other styles

29

Haldar, Sandip, Claudio S. Lopes, and Carlos Gonzalez. "Interlaminar and Intralaminar Fracture Behavior of Carbon Fiber Reinforced Polymer Composites." Key Engineering Materials 713 (September 2016): 325–28. http://dx.doi.org/10.4028/www.scientific.net/kem.713.325.

Full text

Abstract:

Interlaminar and intralaminar fracture behavior of carbon fiber reinforced composites have been experimentally studied. Unidirectional, woven reinforcement and thermoplastic and thermoset polymer matrix laminates have been characterized using double cantilever beam (DCB) and end notch flexure (ENF) specimens for Mode-I and Mode-II fracture toughness, respectively and compact tension (CT) specimens for intralaminar fracture. AS4/PEEK, AS4/8552 and AGP193PW/8552 laminates have been characterized in this study. The fracture toughness determined from the experimental data could be related to the constituents and reinforcements. It has been observed between the two UD laminates, AS4/PEEK exhibit higher fracture resistance under both interlaminar and intralaminar fracture. Woven reinforcement is found to show higher mode-II interlaminar fracture toughness.

APA, Harvard, Vancouver, ISO, and other styles

30

May, Michael, Sebastian Kilchert, and Tobias Gerster. "A Modified Compact Tension Test for Characterization of the Intralaminar Fracture Toughness of Tri-Axial Braided Composites." Materials 14, no. 17 (August 27, 2021): 4890. http://dx.doi.org/10.3390/ma14174890.

Full text

Abstract:

The application of braided composite materials in the automotive industry requires an in-depth understanding of the mechanical properties. To date, the intralaminar fracture toughness of braided composite materials, typically used for describing post-failure behavior, has not been well-characterized experimentally. In this paper, a modified compact tension test, utilizing a relatively large specimen and a metallic loading frame, is used to measure the transverse intralaminar fracture toughness of a tri-axial braided composite. During testing, a relatively long fracture process zone ahead of the crack tip was observed. Crack propagation could be correlated to the failure of individual unit cells, which required failure of bias-yarns. The transverse interlaminar fracture toughness was found to be two orders of magnitude higher than the reference interlaminar fracture toughness of the same material. This is due to the fact, that intralaminar crack propagation requires breaking of fibers, which is not the case for interlaminar testing.

APA, Harvard, Vancouver, ISO, and other styles

31

Garg, Amar C. "Intralaminar and interlaminar fracture in graphite/epoxy laminates." Engineering Fracture Mechanics 23, no. 4 (January 1986): 719–33. http://dx.doi.org/10.1016/0013-7944(86)90118-9.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

McCallum, Stuart, Takuhei Tsukada, and Nobuo Takeda. "The influence of skin-core residual stress and cooling rate on the impact response of carbon fibre/polyphenylenesulphide." Journal of Thermoplastic Composite Materials 31, no. 9 (November 20, 2017): 1232–51. http://dx.doi.org/10.1177/0892705717734607.

Full text

Abstract:

This study investigates the influence of macroscale skin-core residual stress and cooling rate on the impact response of aerospace grade carbon fibre/polyphenylenesulphide (CF/PPS). Numerical simulations are developed which analyse the thermal shrinkage and residual stress development of unidirectional (UD) lay-up configurations. Macroscale skin-core residual stresses are then incorporated into low-velocity impact simulations based on an orthotropic elastic material model. Interlaminar delamination is modelled using a bilinear cohesive traction–separation law, and intralaminar failure is modelled using the Chang–Chang strength-based failure criterion. The simulation results are compared with the results of drop tower impact tests showing qualitative agreement in terms of maximum impact force and delamination. The results of this work highlight the importance of cooling rate on the interlaminar delamination and intralaminar failure of CF/PPS.

APA, Harvard, Vancouver, ISO, and other styles

33

Adams, Daniel O’Hare, and Michael W. Hyer. "Analysis of Layer Waviness in Flat Compression-Loaded Thermoplastic Composite Laminates." Journal of Engineering Materials and Technology 118, no. 1 (January 1, 1996): 63–70. http://dx.doi.org/10.1115/1.2805935.

Full text

Abstract:

A finite element analysis was used to investigate layer waviness effects in flat compression-loaded composite laminates. Stress distributions in the vicinity of the layer waves as well as the locations and modes of failure were investigated. Two layer wave geometries were considered, each modeled within an otherwise wave-free thermoplastic composite laminate. These two wave geometries, classified as moderate and severe, corresponded to layer waves fabricated in actual laminates and tested under uniaxial compression loading. Material nonlinearities obtained from intralaminar shear and 0 and 90 deg tension and compression testing were incorporated into the analysis. The nonlinearity observed in the intralaminar shear stress-strain behavior was assumed to be valid for interlaminar shear stress-strain behavior, and the nonlinearity observed in the 90 deg tension and compression stress-strain behavior was assumed to be valid for interlaminar normal stress-strain behavior. Failure was predicted using a maximum stress failure theory. An interlaminar tension failure was predicted for the severe layer wave geometry, producing a large compression strength reduction in comparison to the wave-free laminate. Fiber compression failure was predicted for the moderate layer wave, producing only a slight compression strength reduction. Although significant material nonlinearity was present in the interlaminar compression and shear response of the material, the inclusion of material nonlinearity produced only slight decreases in predicted compression strengths relative to predictions based on linear material behavior.

APA, Harvard, Vancouver, ISO, and other styles

34

Garg, Amar C. "Interlaminar and intralaminar fracture surface morphology in graphite/epoxy laminates." Engineering Fracture Mechanics 23, no. 6 (January 1986): 1031–50. http://dx.doi.org/10.1016/0013-7944(86)90146-3.

Full text

APA, Harvard, Vancouver, ISO, and other styles

35

Li, Fei, AnZhong Deng, QiLin Zhao, and Jinhui Duan. "Research on Influence mechanism of composite interlaminar shear strength under normal stress." Science and Engineering of Composite Materials 27, no. 1 (May 4, 2020): 119–28. http://dx.doi.org/10.1515/secm-2020-0011.

Full text

Abstract:

AbstractThe normal stress along the shear plane has great effect on the composite intralaminar shear strength. However, the influence mechanism on composite interlaminar shear strength under the normal stress along the shear plane was not truly reflected by the double-notch shear experiment. In this paper, the interlaminar shear strength of composite specimens under different external normal stresses was first obtained using the improved double-notch shear experiment. Furthermore, to research the influence mechanism on interlaminar shear strength under normal stress along the shear plane, the characteristic curve method based on the double-notch shear specimen was studied. Finally, the experimental results analyzed by the characteristic curve method were compared with a range of failure criteria presented in the literature. The experimental data obtained in this study agreed best with the NU theory criterion, with a maximum numerical difference of 4%. And the NU theory criterion can reflect the influence mechanism of the composite interlaminar shear strength best.

APA, Harvard, Vancouver, ISO, and other styles

36

Wicks, Sunny S., Roberto Guzman de Villoria, and Brian L. Wardle. "Interlaminar and intralaminar reinforcement of composite laminates with aligned carbon nanotubes." Composites Science and Technology 70, no. 1 (January 2010): 20–28. http://dx.doi.org/10.1016/j.compscitech.2009.09.001.

Full text

APA, Harvard, Vancouver, ISO, and other styles

37

de Moura, M. F. S. F., R. D. S. G. Campilho, A. M. Amaro, and P. N. B. Reis. "Interlaminar and intralaminar fracture characterization of composites under mode I loading." Composite Structures 92, no. 1 (January 2010): 144–49. http://dx.doi.org/10.1016/j.compstruct.2009.07.012.

Full text

APA, Harvard, Vancouver, ISO, and other styles

38

Ferrer, Camilo, Helen Hsieh, and Lonnie P. Wollmuth. "Input-specific maturation of NMDAR-mediated transmission onto parvalbumin-expressing interneurons in layers 2/3 of the visual cortex." Journal of Neurophysiology 120, no. 6 (December 1, 2018): 3063–76. http://dx.doi.org/10.1152/jn.00495.2018.

Full text

Abstract:

Parvalbumin-expressing (PV) GABAergic interneurons regulate local circuit dynamics. In terms of the excitation driving PV interneuron activity, the N-methyl-d-aspartate receptor (NMDAR)-mediated component onto PV interneurons tends to be smaller than that onto pyramidal neurons but makes a significant contribution to their physiology and development. In the visual cortex, PV interneurons mature during the critical period. We hypothesize that during the critical period, the NMDAR-mediated signaling and functional properties of glutamatergic synapses onto PV interneurons are developmentally regulated. We therefore compared the α-amino-3-hydroxy-5-methyl-4-isoxazolepropionic acid receptor (AMPAR)- and NMDAR-mediated synaptic responses before (postnatal days 15–20, P15–P20), during (P25–P40), and after (P50–P60) the visual critical period. AMPAR miniature excitatory postsynaptic currents (mEPSCs) showed a developmental decrease in frequency, whereas NMDAR mEPSCs were absent or showed extremely low frequencies throughout development. For evoked responses, we consistently saw a NMDAR-mediated component, suggesting pre- or postsynaptic differences between evoked and spontaneous neurotransmission. Evoked responses showed input-specific developmental changes. For intralaminar inputs, the NMDAR-mediated component significantly decreased with development. This resulted in adult intralaminar inputs almost exclusively mediated by AMPARs, suited for the computation of synaptic inputs with precise timing, and likely having NMDAR-independent forms of plasticity. In contrast, interlaminar inputs maintained a stable NMDAR-mediated component throughout development but had a shift in the AMPAR paired-pulse ratio from depression to facilitation. Adult interlaminar inputs with facilitating AMPAR responses and a substantial NMDAR component would favor temporal integration of synaptic responses and could be modulated by NMDAR-dependent forms of plasticity. NEW & NOTEWORTHY We show for the first time input-specific developmental changes in the N-methyl-d-aspartate receptor component and short-term plasticity of the excitatory drive onto layers 2/3 parvalbumin-expressing (PV) interneurons in the visual cortex during the critical period. These developmental changes would lead to functionally distinct adult intralaminar and interlaminar glutamatergic inputs that would engage PV interneuron-mediated inhibition differently.

APA, Harvard, Vancouver, ISO, and other styles

39

Gu, Li, and Su. "A Continuum Damage Model for Intralaminar Progressive Failure Analysis of CFRP Laminates Based on the Modified Puck’s Theory." Materials 12, no. 20 (October 10, 2019): 3292. http://dx.doi.org/10.3390/ma12203292.

Full text

Abstract:

A continuum damage model is proposed to predict the intralaminar progressive failure of CFRP laminates based on the modified Puck’s theory. Puck’s failure criteria, with consideration of the in situ strength effect, are employed to evaluate the onset of intralaminar failure including fiber fracture and inter-fiber fracture. After damage initiation, a bilinear constitutive relation is used to describe the damage evolution process. In strict accordance with Puck’s concept of action plane, the extent of damage is quantified by the damage variables defined in the fracture plane coordinate system, rather than the traditional material principal coordinate system. Theoretical and experimental evaluation of CFRP laminates under different loading conditions demonstrates the rationality and effectiveness of the proposed numerical model. The model has been successfully implemented in a finite element (FE) software to simulate the intralaminar progressive failure process of CFRP laminates. A good agreement between the experimental and numerical results demonstrates that the present model is capable of predicting the intralaminar failure of CFRP laminates.

APA, Harvard, Vancouver, ISO, and other styles

40

Sedlacek, Frantisek, Tomas Kalina, and Karel Raz. "Determination of Mode II Interlaminar Fracture Toughness of CFRP Composites Using Numerical Simulations." Key Engineering Materials 801 (May 2019): 71–76. http://dx.doi.org/10.4028/www.scientific.net/kem.801.71.

Full text

Abstract:

This paper deals with a numerical simulation of the interlaminar fracture toughness of woven carbon fibre reinforced polymer. Composite materials are increasingly used for their unique properties in many branches of engineering. They are also used for flexible components such as springs, couplings, etc. The strength of these parts must be determined not only in terms of their intralaminar properties but also in terms of their interlaminar properties. This paper provides a methodology for determining the main parameters for Mode II interlaminar fracture toughness using numerical simulation. End Notch Flexure (ENF) specimens were created for fitting fracture toughness parameters of the laminate according to ASTM standards. Three point bending ENF tests were carried out on a Zwick/Roell Z050 machine. The numerical simulation was created in Siemens Simcenter 12.0 using NX Nastran nonlinear solver. The results from the numerical simulation correspond to those from the experimental test with an accuracy of 4%.

APA, Harvard, Vancouver, ISO, and other styles

41

Goyal, Vinay K., Navin R. Jaunky, Eric R. Johnson, and Damodar R. Ambur. "Intralaminar and interlaminar progressive failure analyses of composite panels with circular cutouts." Composite Structures 64, no. 1 (April 2004): 91–105. http://dx.doi.org/10.1016/s0263-8223(03)00217-4.

Full text

APA, Harvard, Vancouver, ISO, and other styles

42

Macedo, F. S., A. B. Pereira, and A. B. de Morais. "Mixed Bending-Tension (MBT) test for mode I interlaminar and intralaminar fracture." Composites Science and Technology 72, no. 9 (May 2012): 1049–55. http://dx.doi.org/10.1016/j.compscitech.2012.03.023.

Full text

APA, Harvard, Vancouver, ISO, and other styles

43

Otsuka, T., and Y. Kawaguchi. "Cortical Inhibitory Cell Types Differentially Form Intralaminar and Interlaminar Subnetworks withExcitatory Neurons." Journal of Neuroscience 29, no. 34 (August 26, 2009): 10533–40. http://dx.doi.org/10.1523/jneurosci.2219-09.2009.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Bazhenov, S. L. "Interlaminar and intralaminar fracture modes in 0/90 cross-ply glass/epoxy laminate." Composites 26, no. 2 (February 1995): 125–33. http://dx.doi.org/10.1016/0010-4361(95)90412-s.

Full text

APA, Harvard, Vancouver, ISO, and other styles

45

Wang, Vincent Z., John D. Ginger, and Krishneel Narayan. "Intralaminar and interlaminar fracture characterization in glued-laminated timber members using image analysis." Engineering Fracture Mechanics 82 (March 2012): 73–84. http://dx.doi.org/10.1016/j.engfracmech.2011.11.024.

Full text

APA, Harvard, Vancouver, ISO, and other styles

46

Vokoun, C. R., M. B. Jackson, and M. A. Basso. "Intralaminar and Interlaminar Activity within the Rodent Superior Colliculus Visualized with Voltage Imaging." Journal of Neuroscience 30, no. 32 (August 11, 2010): 10667–82. http://dx.doi.org/10.1523/jneurosci.1387-10.2010.

Full text

APA, Harvard, Vancouver, ISO, and other styles

47

Chen, Fangliang, and Pizhong Qiao. "On the intralaminar and interlaminar stress analysis of adhesive joints in plated beams." International Journal of Adhesion and Adhesives 36 (July 2012): 44–55. http://dx.doi.org/10.1016/j.ijadhadh.2012.03.005.

Full text

APA, Harvard, Vancouver, ISO, and other styles

48

Barbosa Marques, Luís Felipe, Jonas Frank Reis, Ana Beatriz Ramos Moreira Abrahão, Luis Rogério D. Oliveira Hein, Edson Cocchieri Botelho, and Michelle L. Costa. "Interfacial, mechanical, and thermal behavior of PEI/glass fiber welded joints influenced by hygrothermal conditioning." Journal of Composite Materials 56, no. 2 (November 10, 2021): 239–49. http://dx.doi.org/10.1177/00219983211055826.

Full text

Abstract:

This work aims to characterize the influence of hygrothermal conditioning on the mechanical and thermal behavior as well as the fractographic aspects of the interface of poly(ether imide) and glass fiber composite joints welded by electrical resistance using 400 mesh of AISI 304 stainless steel. The composites were mechanically characterized by Lap Shear Strength (LSS) and End Notched Flexure (ENF) testing to investigate maximum shear stress and energy from mode II interlaminar fracture toughness. Fractography was performed by SEM, while the influence on glass transition temperature and working temperature were evaluated by Dynamic-Mechanical Analysis and thermogravimetry. In the conditioned samples, the mechanical properties reduced 23% in the LSS test and 28% in the ENF test, while the fractography studies revealed elements of interlaminar and intralaminar fracture in both conditions. Thermal properties did not change significantly to disqualify this composite when applied to welding.

APA, Harvard, Vancouver, ISO, and other styles

49

McDonald, Erin E., Landon F. Wallace, Gregory J. S. Hickman, and Kuang-Ting Hsiao. "Manufacturing and Shear Response Characterization of Carbon Nanofiber Modified CFRP Using the Out-of-Autoclave-Vacuum-Bag-Only Cure Process." Scientific World Journal 2014 (2014): 1–9. http://dx.doi.org/10.1155/2014/830295.

Full text

Abstract:

The interlaminar shear response is studied for carbon nanofiber (CNF) modified out-of-autoclave-vacuum-bag-only (OOA-VBO) carbon fiber reinforced plastic (CFRP). Commercial OOA-VBO prepregs were coated with a CNF modified epoxy solution and a control epoxy solution without CNF to make CNF modified samples and control samples, respectively. Tensile testingwas used to study the in-plane shear performance of [±45°]4scomposite laminates. Significant difference in failure modes between the control and CNF modified CFRPs was identified. The control samples experienced half-plane interlaminar delamination, whereas the CNF modified samples experienced a localized failure in the intralaminar region. Digital image correlation (DIC) surface strain results of the control sample showed no further surface strain increase along the delaminated section when the sample was further elongated prior to sample failure. On the other hand, the DIC results of the CNF modified sample showed that the surface strain increased relatively and uniformly across the CFRP as the sample was further elongated until sample failure. The failure mode evidence along with microscope pictures indicated that the CNF modification acted as a beneficial reinforcement inhibiting interlaminar delamination.

APA, Harvard, Vancouver, ISO, and other styles

50

Yun, Kumchol, Songhun Kwak, Zhenqing Wang, Mengzhou Chang, Jonggun Kim, Jingbiao Liu, and Cholsu Ri. "A Damage Model Reflecting the Interaction between Delamination and Intralaminar Crack for Failure Analysis of FRP Laminates." Applied Sciences 9, no. 2 (January 16, 2019): 314. http://dx.doi.org/10.3390/app9020314.

Full text

Abstract:

In this paper, a progressive damage model reflecting the interaction between delamination and intralaminar crack is developed to predict fracture behaviors and the ultimate load-bearing ability of the fiber-reinforced polymer laminates subject to quasi-static load. Initiation and evolution of intralaminar crack in composites are modeled using a continuum damage mechanics model, which has the capability to reliably predict the discrete crack direction by introducing the crack direction parameter while analyzing the multi-failure of FRP composites. Delamination is modeled using a cohesive zone method with the mixed bilinear law. When the continuum damage model and cohesive zone model are used together, the interactive behavior between multiple failure mechanisms such as delamination induced by matrix cracking often seen in the failure of composite laminates is not generally captured. Interaction between delamination and intralaminar crack in FRP composite structures is investigated in detail and reflected in a finite element analysis in order to eliminate the drawbacks of using both models together. Good agreements between numerical results and experimental data are obtained.

APA, Harvard, Vancouver, ISO, and other styles

Journal articles on the topic 'Interlaminar and intralaminar damage'

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles