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Journal articles on the topic 'Interlaminar and intralaminar damage'

Author: Grafiati

Published: 7 April 2023

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1

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

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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 we

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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 (2008): 358–73. http://dx.doi.org/10.1080/15502280802365824.

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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 (2017): 515–32. http://dx.doi.org/10.1017/aer.2017.6.

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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 conside

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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 (2017): 1317–30. http://dx.doi.org/10.1177/0021998317724216.

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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 imp

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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 (2010): 1504–12. http://dx.doi.org/10.1016/j.compscitech.2010.05.006.

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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 (2022): 71–82. http://dx.doi.org/10.1515/jmbm-2022-0008.

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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 m

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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 (2002): 477–99. http://dx.doi.org/10.1177/0021998302036004539.

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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 (2010): 683–703. http://dx.doi.org/10.1142/s0219455410003683.

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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

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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 (2020): 13–25. http://dx.doi.org/10.24191/jmeche.v17i2.15297.

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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 formula

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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.

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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

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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 (2016): 2331–45. http://dx.doi.org/10.1177/0021998316669992.

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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

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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.

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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.

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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 (2013): 71–85. http://dx.doi.org/10.1017/s0001924000007764.

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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 compo

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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 (2016): 3269–80. http://dx.doi.org/10.1177/0021998316681860.

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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 fibe

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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.

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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 fail

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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 (2021): 2131. http://dx.doi.org/10.3390/polym13132131.

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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

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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 (2022): 516–28. http://dx.doi.org/10.1515/secm-2022-0176.

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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 da

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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 (2011): 51–80. http://dx.doi.org/10.1177/1056789510397070.

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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. T

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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.

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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 (2018): 435–45. http://dx.doi.org/10.1177/0309324718780598.

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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,

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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 (2022): 1693–708. http://dx.doi.org/10.1177/00219983221078787.

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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 commercia

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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 (2010): 113–25. http://dx.doi.org/10.1007/s10443-010-9135-1.

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24

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

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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 direction

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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 (2014): 101–21. http://dx.doi.org/10.1007/s11668-014-9901-8.

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26

Tan, W., F. Naya, L. Yang, et al. "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.

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

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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 l

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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 (2022): 4279. http://dx.doi.org/10.3390/polym14204279.

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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

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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.

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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 c

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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 (2021): 4890. http://dx.doi.org/10.3390/ma14174890.

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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 th

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31

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

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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 (2017): 1232–51. http://dx.doi.org/10.1177/0892705717734607.

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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 model

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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 (1996): 63–70. http://dx.doi.org/10.1115/1.2805935.

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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

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

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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 (2020): 119–28. http://dx.doi.org/10.1515/secm-2020-0011.

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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

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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 (2010): 20–28. http://dx.doi.org/10.1016/j.compscitech.2009.09.001.

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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 (2010): 144–49. http://dx.doi.org/10.1016/j.compstruct.2009.07.012.

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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 (2018): 3063–76. http://dx.doi.org/10.1152/jn.00495.2018.

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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 regu

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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 (2019): 3292. http://dx.doi.org/10.3390/ma12203292.

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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,

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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.

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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

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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 (2004): 91–105. http://dx.doi.org/10.1016/s0263-8223(03)00217-4.

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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 (2012): 1049–55. http://dx.doi.org/10.1016/j.compscitech.2012.03.023.

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

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

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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.

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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 (2010): 10667–82. http://dx.doi.org/10.1523/jneurosci.1387-10.2010.

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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.

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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 (2021): 239–49. http://dx.doi.org/10.1177/00219983211055826.

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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 workin

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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.

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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 delamin

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Yun, Kumchol, Songhun Kwak, Zhenqing Wang, et al. "A Damage Model Reflecting the Interaction between Delamination and Intralaminar Crack for Failure Analysis of FRP Laminates." Applied Sciences 9, no. 2 (2019): 314. http://dx.doi.org/10.3390/app9020314.

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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 m

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