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Journal articles on the topic 'Interlaminar damage'

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Published: 4 June 2021
Last updated: 19 February 2022

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1

Miura, Masaya, Yasuhide Shindo, Tomo Takeda, and Fumio Narita. "Damage Development in Hybrid Composite Laminates under Three-Point Bending at Cryogenic Temperatures." Key Engineering Materials 452-453 (November 2010): 565–68. http://dx.doi.org/10.4028/www.scientific.net/kem.452-453.565.

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This paper studies the damage behavior and interlaminar shear properties of hybrid composite laminates subjected to bending at cryogenic temperatures. Cryogenic short beam shear tests were performed on hybrid laminates combining woven glass fiber reinforced polymer (GFRP) composites with polyimide films, and microscopic observations of the specimens were made after the tests. A progressive damage analysis was also conducted to simulate the initiation and growth of damage in the specimens and to determine the interlaminar shear strength based on the maximum shear stress in the failure region. The predicted load-deflection curve and damage pattern show good agreement with the test results, and the numerically determined interlaminar shear strength is higher than the apparent interlaminar shear strength.
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2

Allix, O., P. Ladevéze, and A. Corigliano. "Damage analysis of interlaminar fracture specimens." Composite Structures 31, no. 1 (January 1995): 61–74. http://dx.doi.org/10.1016/0263-8223(95)00002-x.

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3

Gillespie, J. W. "Damage Tolerance of Composite Structures: The Role of Interlaminar Fracture Mechanics." Journal of Offshore Mechanics and Arctic Engineering 113, no. 3 (August 1, 1991): 247–52. http://dx.doi.org/10.1115/1.2919927.

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Layered fiber-reinforced composite structures are susceptible to crack initiation and growth in the resin-rich layer between plies. Delamination represents one of the most prevalent life-limiting failure modes in laminated composite structures. Interlaminar fracture mechanics represents one approach to assess the damage tolerance of composite structures. This paper is organized into two major sections. The first sections introduces interlaminar fracture mechanics and test methods that have been developed to characterize the Mode I, II and III interlaminar fracture toughness of composite laminates. In the second section, the role of interlaminar fracture mechanics in assessing damage tolerance of composite structures is defined through the following case studies: residual compression after impact strength, instability related delamination growth in compressively loaded laminates and delamination growth in composite laminates with discontinuous internal plies.
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4

Abdullah, Muhammad A'imullah, Mohammad Reza Arjmandi, Seyed Saeid Rahimian Koloor, King Jye Wong, and Mohd Nasir Tamin. "Interlaminar Damage Behavior of CFRP Composite Laminates under Cyclic Shear Loading Conditions." Advanced Materials Research 1125 (October 2015): 121–25. http://dx.doi.org/10.4028/www.scientific.net/amr.1125.121.

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This paper provides quantitative description of interlaminar damage process in CFRP composite laminates under cyclic shear loading. Quasi-static end-notched flexural (ENF) test on 16-ply CFRP composite laminate beam, [0]16 and its complementary validated FE model provide the reference “no-interlaminar damage” condition. Two identical ENF samples were fatigue to 50000 cycles, but at different load amplitude of 90 and 180 N, respectively (Load ratio, R = 0.1) to induce selectively property degradation at the interface crack front region. Subsequent quasi-static ENF tests establish the characteristic of the interlaminar damage degradation. The residual peak load for the fatigued ENF samples is measured at 1048 and 914 N for the load amplitude of 90 and 180 N, respectively. Cyclic interlaminar shear damage is represented by a linear degradation of the residual critical energy release rate, GIIC with the accumulated damage. Reasonably close comparisons of the predicted residual load-displacement responses with measured curves serve to verify the suitability of the assumed bilinear traction-separation law for the cyclic cohesive zone model (CCZM) used.
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5

Lonetti, Paolo, Raffaele Zinno, Fabrizio Greco, and Ever J. Barbero. "Interlaminar Damage Model for Polymer Matrix Composites." Journal of Composite Materials 37, no. 16 (August 2003): 1485–504. http://dx.doi.org/10.1177/0021998303034741.

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6

Burlayenko, Vyacheslav, and Tomasz Sadowski. "FE modeling of delamination growth in interlaminar fracture specimens." Budownictwo i Architektura 2, no. 1 (June 11, 2008): 095–109. http://dx.doi.org/10.35784/bud-arch.2315.

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Interlaminar fracture specimens like Double Cantilever Beam (DCB), End Notched Flexural (ENF), Single Leg Bending (SLB) etc. are widely used for studying the interlaminar toughness of composite laminates. The aim of this paper is to analysis delamination specimens within the framework of a meso-level damage modeling of composite laminates. In this case interlaminar interface is assumed as a damageable homogeneous layer between adjacent layers of the specimen bulk material. The degradation of the interlaminar connection can be taken into account by means either of an appropriate damage initiation criterion and damage evolution law or using fracture mechanics approach. Onset and growth of the delamination pre-existing crack in the fracture specimens are simulated by using both modeling possibility within commercial finite element code ABAQUSTM. Comparisons between numerical predictions of used different finite element models as well as available experimental data have been performed.
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7

Castellanos, AG, Md S. Islam, E. Tarango, Y. Lin, and P. Prabhakar. "Interlaminar reinforcement for enhancing low-velocity impact response of woven composites." Textile Research Journal 88, no. 15 (May 12, 2017): 1710–20. http://dx.doi.org/10.1177/0040517517708536.

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This paper proposes a novel technique for improving the low-velocity impact response of woven composites, which involves synthesizing ZnO nanowires on dry woven carbon fabric layers. ZnO nanowire reinforcements were added to the interlaminar regions that are most susceptible to damage within layered composites, which were determined using finite element method analysis. Upon fabricating the laminates with and without ZnO nanowire interlaminar reinforcements, low-velocity impact responses were investigated next and the degree of damage was experimentally determined. The physical tests reveal that the samples with ZnO nanowires experience a lower degree of damage, up to a maximum of 25% for different impact energies, in comparison to the samples without ZnO nanowires. Therefore, the study presented in this paper shows the potential of using ZnO nanowires as interlaminar reinforcements for woven composites to improve their impact damage resistance.
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8

Cui, W. C., M. R. Wisnom, and M. Jones. "Failure mechanisms in three and four point short beam bending tests of unidirectional glass/epoxy." Journal of Strain Analysis for Engineering Design 27, no. 4 (October 1, 1992): 235–43. http://dx.doi.org/10.1243/03093247v274235.

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Three and four point bending tests are compared both analytically and experimentally. In all the three point bending tests, damage was observed under the loading roller in addition to the interlaminar shear failure, while in the four point bending tests, only interlaminar shear failure was observed. Therefore, this four point bending test is valid for measuring the interlaminar shear strength. From the finite element analysis, it is found that the roller diameter is a critical parameter in determining the stress concentrations in short beam tests. In order to avoid damage under the roller and thus to make the short beam test a valid means for measuring the interlaminar shear strength, the appropriate roller diameters should be chosen. The damage under the loading roller in the three point bending test basically reduces the effective specimen thickness and thus this test underestimates the interlaminar shear strength. The interlaminar shear cracks in the short beam tests were found to be randomly distributed in a region between 30 percent and 70 percent through the thickness from the top surface. This is due to the non-linear shear response which means that the shear stress distribution is more uniform near the middle of the section. Also the maximum value of the shear stress is lower than the maximum value given by beam theory. A non-linear shear correction factor is suggested to account for this effect and for the glass/epoxy composite tested here, the actual interlaminar shear strength is only about 83 percent of the apparent value from classical beam theory. The interlaminar shear crack does not occur at the location of maximum shear stress. This may be because there is insufficient energy to propagate a crack at this location.
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9

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.

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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 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.
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10

Constantinescu, Dan Mihai, Marin Sandu, Liviu Marsavina, Radu Negru, Matei Constantin Miron, and Dragos Alexandru Apostol. "Evaluation of Interlaminar Damage and Crack Propagation through Digital Image Correlation Method." Key Engineering Materials 399 (October 2008): 105–12. http://dx.doi.org/10.4028/www.scientific.net/kem.399.105.

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Interface damage characterization and interlaminar failure of sandwich specimens with two initial interlaminar defects (inserts) is done by using the digital image correlation method. Mode I tests reveal interesting particularities on damage localization and unstable crack propagation. After analyzing the experimentally obtained results, we propose as a failure parameter the local strain at the crack tip or, alternatively, the crack tip opening displacement which quantifies the non-linear phenomena.
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11

Koloor, S. S. R., Majid R. Ayatollahi, and M. N. Tamin. "Modeling Interlaminar Shear Crack-Jump Phenomenon in Fiber-Reinforced Polymer Composites." Advanced Materials Research 1125 (October 2015): 74–78. http://dx.doi.org/10.4028/www.scientific.net/amr.1125.74.

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This paper discusses the simulation technique for the development of a validated finite element model to capture the stable shear crack-jump phenomenon in carbon fiber-reinforced polymer composite laminates. The interlaminar cracking process is characterized using a 16-ply unidirectional ([0]16) end-notch flexure (ENF) specimens. Complementary FE models of the test setup are developed to capture the mechanics of the observed interlaminar crack-jump phenomenon. The cohesive interface response is represented by a damage model with bilinear traction-displacement softening law. Close comparison of measured and FE-predicted load-central deflection response of the beam specimen serves to validate the FE model for the stable shear crack-jump. FE simulation predicts an early onset of damage at the interlaminar crack front corresponding to 13.4 pct. of the maximum deflection at fracture. The mechanism of stable crack-jump is described by the characteristic evolution of the interface damage parameter, and quantified by the damage dissipation energy.
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12

Zhao, Li Jun, Feng Peng Zhang, Xiao Zhi Hu, and Bao Zong Huang. "Study on Interlaminar Shear and Damage Behavior of Carbon Fiber Composites with Short Fiber Interleaves: 2. Micro-Mechanical Simulation." Advanced Materials Research 41-42 (April 2008): 341–47. http://dx.doi.org/10.4028/www.scientific.net/amr.41-42.341.

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A micro-mechanical model and simulation for the damage behavior of short fiber interleaves (SFIs) were developed based on Mori-Tanaka method and an equivalent approach to interface debonding (Fitoussi etc 1990). The damage evolution and the stress-strain relation of SFIs have been predicted in the cases of interlaminar shear, out-of and in-plane tension, respectively. The simulation indicates that the damage always starts from the interface debonding of fibers perpendicular to load and the matrix cracking in the direction parallel to fibers, and then rapidly spreads to more fibers during loading. The strength and the ultimate strain in out-of-plane tension are much lower than that in interlaminar shear and in-pane tension. The strength and failure probability of interface bonding are the most considerable factors to affect the damage and failure of SFIs. The comparison of the simulation with the interlaminar shear test shows a good agreement.
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13

Wang, Sian, Yunhe Zhang, and Gaohui Wu. "Interlaminar Shear Properties of Z-Pinned Carbon Fiber Reinforced Aluminum Matrix Composites by Short-Beam Shear Test." Materials 11, no. 10 (October 1, 2018): 1874. http://dx.doi.org/10.3390/ma11101874.

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This paper presents the effect of through-thickness reinforcement by steel z-pins on the interlaminar shear properties and strengthening mechanisms of carbon fiber reinforced aluminum matrix composites (Cf/Al) with a short beam shear test method. Microstructural analysis reveals that z-pins cause minor microstructural damage including to fiber waviness and aluminum-rich regions, and interface reaction causes a strong interface between the stainless steel pin and the aluminum matrix. Z-pinned Cf/Al composites show reduced apparent interlaminar shear strength due to a change in the failure mode compared to unpinned specimens. The changed failure mode could result from decreased flexural strength due to microstructural damage as well as increased actual interlaminar shear strength. Fracture work is improved significantly with a z-pin diameter. The strong interface allows the deformation resistance of the steel pin to contribute to the crack bridging forces, which greatly enhances the interlaminar shear properties.
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14

Peng, Wen Jie, and Jian Qiao Chen. "Numerical Evaluation of Ultimate Strengths of Composites Considering Both In-Plane Damage and Delamination." Key Engineering Materials 324-325 (November 2006): 771–74. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.771.

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Traditional laminate strength analysis only considers face failure under in-plane loads. In fact, owing to the mismatch of the mechanical properties of the adjacent layers, a three-dimensional interlaminar singular stress fields develop in a small boundary region in the vicinity of the free edges of the laminate under mechanical load, which may lead to interlaminar delamination failure. Neglecting this interlaminar failure mode, the failure strength of laminate will be overestimated. In this paper, face failure and interlaminar failure are both considered. So for a lamina, three major failure modes are considered: matrix failure, fiber breakage and delamination. Finite element method is used to obtain the stresses in a laminate under mechanical loads. Stress-based criterions are adopted to predict the failure mode of laminas. When a lamina is failed, the lamina stiffness is reduced according to the corresponding failure mode, and the stresses of the laminate are re-analyzed. This procedure is repeatedly performed until the whole laminate fails and thus the ultimate strength is determined. The predicted ultimate strengths are in good agreement with experiment results in the open literature.
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15

Lonetti, Paolo, Ever J. Barbero, Raffaele Zinno, and Fabrizio Greco. "Erratum: Interlaminar Damage Model for Polymer Matrix Composites." Journal of Composite Materials 38, no. 9 (May 2004): 799–800. http://dx.doi.org/10.1177/0021998304042699.

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16

Yoon, Sung Ho, Kwang Su Heo, Jin Oh Oh, Jong Cheol Jeong, Sang Jin Lee, Jung Seok Kim, and Seong Ho Han. "Damage Tolerance of Carbon Fabric/Epoxy Composite for Korean Tilting Train Carbody." Key Engineering Materials 334-335 (March 2007): 449–52. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.449.

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Interlaminar fracture behavior of carbon fabric/epoxy composite, which is one of the candidate composites for the Korean tilting train carbody, was investigated. Specimens were made of a CF3227 plain fabric with an epoxy resin. An initial starter crack was formed by inserting a 12.5 thick Teflon film at the one end of the specimen. Interlaminar fracture toughness was evaluated using the mixed mode flexural fixture, which provides a wide range of mixed mode deformation by varying the length of lever arm. According to the results, the crack growth was progressive and stable under mode I dominantly mixed mode ratio and was relatively rapid and unstable under mode II dominantly mixed mode ratio. The mixed mode interlaminar fracture behavior can be predicted by a mixed mode fracture criterion depending on the point at which the crack growth was associated.
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17

Lu, Xianqiang, and Dahsin Liu. "An Interlaminar Shear Stress Continuity Theory for Both Thin and Thick Composite Laminates." Journal of Applied Mechanics 59, no. 3 (September 1, 1992): 502–9. http://dx.doi.org/10.1115/1.2893752.

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The interlaminar shear stress plays a very important role in the damage of composite laminates. With higher interlaminar shear stress, delamination can easily occur on the composite interface. In order to calculate the interlaminar shear stress, a laminate theory, which accounts for both the interlaminar shear stress continuity and the transverse shear deformation, was presented in this study. Verification of the theory was performed by comparing the present theory with Pagano’s elasticity analysis. It was found that the present theory was able to give excellent results for both stresses and displacements. More importantly, the interlaminar shear stress can be presented directly from the constitutive equations instead of being recovered from the equilibrium equations.
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18

Butler, Shaoluo, Mark Gurvich, Anindya Ghoshal, Gregory Welsh, Paul Attridge, Howard Winston, Michael Urban, and Nathaniel Bordick. "Effect of embedded sensors on interlaminar damage in composite structures." Journal of Intelligent Material Systems and Structures 22, no. 16 (August 30, 2011): 1857–68. http://dx.doi.org/10.1177/1045389x11414225.

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This research focuses on developing an embedded sensor system to monitor the health of a composite rotor component. To support this objective, simulations were developed to investigate the impact of sensor insertions on local structural micro-mechanics and sensor responses. In particular, the potential side-effects (e.g., delamination onset and growth) of imbedding lead zirconate titanate (PZT) piezoelectric sensors in composite structures were studied. A modeling approach for evaluating interlaminar damage under the influence of embedded PZT sensors is proposed. The approach uses finite element cohesive zone models to describe interlaminar damage between plies or at ply ends. In addition, an embedded multi-ply PZT model was developed and integrated with the damage models. The approach presented in this paper analyzes the propagation of interlaminar damage in the vicinity of sensors and quantifies the effect of sensor presence on damage growth. A parametric study was performed to understand how damage zones, the size and geometry of resin pockets, and the locations and properties of PZT sensors affected interfacial strength. Damage behavior, under the influence of an embedded PZT sensor, was examined in specimens having a configuration similar to that of a selected rotating rotorcraft component. Finally, optimal locations of embedded PZT transducers were determined for the specimen under consideration.
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19

Hinz, Stephan, Jens Heidemann, and Karl Schulte. "Damage Evaluation of GLARE®4B under Interlaminar Shear Loading at Different Temperature Conditions." Advanced Composites Letters 14, no. 2 (March 2005): 096369350501400. http://dx.doi.org/10.1177/096369350501400201.

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The fibre reinforced metal laminate GLARE®4B was investigated under interlaminar shear loading conditions at temperatures between −50°C and 110°C. Short beam shear (ILSS) and double notched shear (DNS) tests were performed. The interlaminar shear strength decreases strongly with increasing temperature. The DNS test shows that the shear strain increases and the interlaminar shear stiffness decreases with increasing temperature. The observed damage occurs mainly in the 90°-fibre layer. For low temperatures delamination between the fibre-layers is the dominant failure mode. The higher the temperature, the more cracks develop in the 90°-layers. These multiple cracks coalesce with increasing shear load and form the final fracture surface. Light and scanning electron microscopy showed that the cracks are mainly based on fibre-matrix interface failure.
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20

Kamiya, Shoji, and Hideki Sekine. "Damage Mechanism and Apparent Fracture Strength of Notched Fiber-Reinforced Composite Laminates." Key Engineering Materials 430 (March 2010): 53–67. http://dx.doi.org/10.4028/www.scientific.net/kem.430.53.

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Apparent fracture strength of notched fiber-reinforced composite laminates depends on the notch tip radius even if it is evaluated in terms of the local parameters such as the stresses at a notch tip or the stress intensity factors. Although numbers of phenomenological explanations have been made, this phenomenon has not yet been physically clear enough. In order to elucidate its key mechanism, our interest is here focused on the interlaminar crack extension from a notch tip in cross-ply laminates subjected to mode-I loading. We find a stochastically expected upper bound of interlaminar crack length due to the probabilistic breakage process of fibers in load-bearing laminas inside the delaminated zone. This upper bound, i.e., the critical length of interlaminar crack, is inherent to the laminate and corresponds to its notched strength. The well-known variation in apparent fracture strength of notched fiber-reinforced composite laminates with respect to the notch tip radius is clearly explained as the scale effect of this constant critical length in different displacement distributions ahead of notch tips of different radii.
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21

Tanaka, Kazuto, Kosuke Ishida, Keisuke Takemoto, and Tsutao Katayama. "Effect of Resin Layer Thickness on Mode II Delamination Growth Property of CFRTP Laminates under Static Loadings." Key Engineering Materials 827 (December 2019): 446–51. http://dx.doi.org/10.4028/www.scientific.net/kem.827.446.

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Carbon Fibre Reinforced Thermoplastics (CFRTP) are expected to be used in various fields for the point of their superior mechanical properties. CFRP laminates with continuous fibres tend to be damaged by microcracks in the layer and interlaminar delamination. Especially, it is necessary to evaluate the mode II delamination growth property, which is correlated with compression after impact (CAI) strength. It is reported that CF/Epoxy laminates with a thicker interlaminar resin layer show higher toughness. By applying an extra thick interlaminar resin layer to CFRTP in which thermoplastic resin with relatively higher fracture toughness is used for the matrix, CFRTP with higher interlaminar fracture toughness can be developed. In this study, the mode II delamination growth property of CFRTP laminates under static loading was evaluated for the specimens with various layer thicknesses of polyamide (PA) resin in the middle layer of the laminates. Their moldability and damage propagation properties were evaluated by three-point bending tests and end notched flexure (ENF) tests. CF/PA laminated composites with a thicker PA layer showed superior mode II delamination growth property under static loading since they had more ductile fracture due to a thicker PA layer.
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22

Talreja, Ramesh. "A Damage Mechanics Analysis of Interlaminar Cracking in Composites." Key Engineering Materials 37 (January 1991): 21–34. http://dx.doi.org/10.4028/www.scientific.net/kem.37.21.

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23

Kashtalyan, Maria, and Costas Soutis. "Analysis of composite laminates with intra- and interlaminar damage." Progress in Aerospace Sciences 41, no. 2 (February 2005): 152–73. http://dx.doi.org/10.1016/j.paerosci.2005.03.004.

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24

Dong, Y. "On-line observation of interlaminar damage by ultrasonic inspection." Composites Science and Technology 59, no. 6 (May 1999): 957–61. http://dx.doi.org/10.1016/s0266-3538(98)00134-1.

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25

AOKI, Yuichiro, Hiroshi SUEMASU, and Toshio NAGASHIMA. "Damage analysis of interlaminar fracture behavior using interface element." Proceedings of the JSME annual meeting 2002.6 (2002): 7–8. http://dx.doi.org/10.1299/jsmemecjo.2002.6.0_7.

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26

Iwahori, Yutaka, and Takashi Ishikawa. "Impact Damage Evaluation of Interlaminar Strength Improved CFRP Laminates." Proceedings of the Materials and processing conference 2004.12 (2004): 185–86. http://dx.doi.org/10.1299/jsmemp.2004.12.185.

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27

Bilisik, Kadir, Gulhan Erdogan, and Erdal Sapanci. "Interlaminar shear properties of nanostitched/nanoprepreg aramid/phenolic composites by short beam method." Journal of Composite Materials 53, no. 21 (November 14, 2018): 2941–57. http://dx.doi.org/10.1177/0021998318811523.

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The interlaminar shear strengths of nanostitched 3D aramid/phenolic composites were studied. Stitching slightly improved the interlaminar strength of the z-stitching/nanotube composites. In addition, the stitching fiber type influenced the interlaminar strength of the z-stitching/nanotube aramid/phenolic composites. The failures of all structures in the compression and tensile sides were almost negligible. However, all structures had interlaminar shear failure where delamination in z-stitching/nanotube composites was arrested. The introduction of the stitching yarn in the baseline structure improved its out-of-plane failure properties without reducing the in-plane properties. The effects of stitching and multiwall carbon nanotubes on the 3D aramid/phenolic composite were encouraging and the nanostitched para-aramid/phenolic nanocomposite could be considered as damage tolerance material.
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28

Fleet, Elliot J., Yi Zhang, Simon A. Hayes, and Patrick J. Smith. "Inkjet printing of self-healing polymers for enhanced composite interlaminar properties." Journal of Materials Chemistry A 3, no. 5 (2015): 2283–93. http://dx.doi.org/10.1039/c4ta05422a.

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29

Chow, C. L., and F. Yang. "Elastic Damage Analysis of Interlaminar Stress Distributions in Symmetrical Composite Laminates with Edge Delamination Cracks." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 208, no. 1 (January 1994): 1–11. http://dx.doi.org/10.1243/pime_proc_1994_208_093_02.

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This paper is intended to present a study of elastic-damaged behaviour of symmetrical composite laminates with edge delamination cracks subjected to uniformly applied uniaxial tensile load. The response of composite laminates is investigated by a quasi-three-dimensional finite element analysis including the damage characterization of constituent plies. Of principal concern are the effects of edge delamination cracks as well as the influence of damage on stress distributions in graphite/epoxy [0/90°]s, [90/0°]s and [±45°], laminates. The computed results between the behaviours of laminates with stiffness damage consideration and those of geometrically similar laminates without stiffness damage are compared and the significance of damage in stress analysis of fibre-reinforced composite materials is elucidated.
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30

Zhao, Li Jun, Feng Peng Zhang, Xiao Zhi Hu, and Bao Zong Huang. "Study on Interlaminar Shear and Damage Behavior of Carbon Fiber Composites with Short Fiber Interleaves: 1. The Comparative Test." Advanced Materials Research 41-42 (April 2008): 335–40. http://dx.doi.org/10.4028/www.scientific.net/amr.41-42.335.

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A special test setup was designed and used in compression shear test of unidirectional carbon fiber composites to study the effect of short fiber interleaves (SFIs) on the interlaminar shear behavior. The comparative tests for two kinds of double-notched compression specimens, with and without SFIs, were carried out to determine the interlaminar shear strength and modulus (ILSS and ILSM) and to examine the failure characteristics. To determine ILSM of the specimens with SFIs an inversion analysis method was proposed based on comparing compression displacement of specimens with and without SFIs. The experimental results show that SFIs makes ILSS decreasing due to lower interface strength, and the complex damage process of SFIs leads to a considerable increase of interlaminar shear compliance.
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31

Liu, Yong Shou, Xiao Jun Shao, and Zhu Feng Yue. "Study of Three-Dimensional Stress Distribution and Damage Characterization of Bolt Composite Joint." Key Engineering Materials 324-325 (November 2006): 395–98. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.395.

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A 3D finite element model of bolt composite joint has been established to determine the stress distribution on the contact surface. The effects of clamping torque and friction on the contact stress and interlaminar normal stress are considered. From the analysis results, contact stress is bared mainly by the 0° layer. The distribution and magnitude of contact stress are conducted by friction. The effect of clamping torque on interlaminar normal stress is very strong. A 3D damage user subroutine is added to the FEM to simulate the damage of joint. By the means of damage simulation, the initiation and progression direction of three types damage are predicted. Matrix cracking and fiber-matrix shear occur at first, and fiber buckling is founded subsequently. The matrix cracking and fiber-matrix debonding initiate at circumferential angle 45°and 135°, and fiber buckling initiate at the 0° layer on the bearing plane. The friction and bolt clamping torque can restrain damage initiation and development.
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32

Hosseini-Toudeshky, Hossein, Meisam Jalalvand, and Bijan Mohammadi. "Delamination of Laminates Governed by Free Edge Interlaminar Stresses Using Interface Element." Key Engineering Materials 385-387 (July 2008): 821–24. http://dx.doi.org/10.4028/www.scientific.net/kem.385-387.821.

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In this paper, interface element with de-cohesive constitutive law is used to predict the delamination progress of laminates in which delamination is the prominent failure mode. For this purpose, a finite element program is developed to perform nonlinear damage analysis. The analyses are carried out based on the interlaminar constitutive law of elastic-plastic-damage proposed before in the literature. Delamination initiation and propagation of several laminates with dominant interlaminar shear stresses at free edges are investigated to find the failure load. It is shown that the difference between the predicted failure loads using the present study and the experimental results are 3.1% to 19.4% for various laminates.
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33

SHINDO, Ysuhide, Mayumi SUMIKAWA, Tomo TAKEDA, Satoru TAKANO, and Fumio NARITA. "Analysis of mode I Interlaminar Fracture and Damage Behavior of GFRP Woven Laminates at Cryogenic Temperatures." Proceedings of The Computational Mechanics Conference 2004.17 (2004): 235–36. http://dx.doi.org/10.1299/jsmecmd.2004.17.235.

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34

Di Caprio, F., S. Saputo, and A. Sellitto. "Numerical-Experimental Correlation of Interlaminar Damage Growth in Composite Structures: Setting Cohesive Zone Model Parameters." Advances in Materials Science and Engineering 2019 (October 13, 2019): 1–16. http://dx.doi.org/10.1155/2019/2150921.

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Composite laminates are characterized by high mechanical in-plane properties while experiencing, on the contrary, a poor out-of-plane response. The composite laminates, indeed, are often highly vulnerable to interlaminar damages, also called “delaminations.” One of the main techniques used for the numerical prediction of interlaminar damage onset and growth is the cohesive zone model (CZM). However, this approach is characterised by uncertainties in the definition of the parameters needed for the implementation of the cohesive behaviour in the numerical software. To overcome this issue, in the present paper, a numerical-experimental procedure for the calibration of material parameters governing the mechanical behaviour of CZM based on cohesive surface and cohesive element approaches is presented. Indeed, by comparing the results obtained from the double cantilever beam (DCB) and end-notched flexure (ENF) experimental tests with the corresponding numerical results, it has been possible to accurately calibrate the parameters of the numerical models needed to simulate the delamination growth phenomenon at coupon level.
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35

Birur, A., A. Gupta, and J. Raghavan. "Creep Rupture of Multidirectional Polymer Composite Laminates — Influence of Time-Dependent Damage." Journal of Engineering Materials and Technology 128, no. 4 (June 23, 2006): 611–17. http://dx.doi.org/10.1115/1.2345454.

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Evolution of various damage modes with time, in multidirectional laminates of a polymer composite (Hexcel F263-7/T300) subjected to a constant load, was experimentally studied and correlated to experimental creep rupture results to understand the influence of the former on the latter. Influence of various parameters, such as stress, temperature, thickness of inner plies, and outer-ply constraint, on damage evolution was evaluated. Observed damages include transverse (also referred in the literature as matrix cracks) cracking due to in-plane stresses, vertical cracking due to out-of-plane normal stress, delamination due to interlaminar stresses, splitting, and fiber fracture. The sequence of evolution of these damages varied with laminate stacking sequence, stress, and temperature. These damages significantly influenced one another and the creep rupture time.
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36

Bellini, Costanzo. "Damage analysis of a GLARE laminate subjected to interlaminar shear." Procedia Structural Integrity 25 (2020): 262–67. http://dx.doi.org/10.1016/j.prostr.2020.04.031.

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37

Kumar, Prashant, and R. K. Singh. "Impact damage area and interlaminar toughness of modified FRP laminates." Advanced Composite Materials 9, no. 2 (January 2000): 77–88. http://dx.doi.org/10.1163/15685510050518587.

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38

Hinz, Stephan, Toshihiro Omoori, Masaki Hojo, and Karl Schulte. "Damage characterisation of fibre metal laminates under interlaminar shear load." Composites Part A: Applied Science and Manufacturing 40, no. 6-7 (July 2009): 925–31. http://dx.doi.org/10.1016/j.compositesa.2009.04.020.

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39

Zhao, Shi Yang, and Pu Xue. "Prediction of Impact Damage of Composite Laminates Using a Mixed Damage Model." Applied Mechanics and Materials 513-517 (February 2014): 235–37. http://dx.doi.org/10.4028/www.scientific.net/amm.513-517.235.

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In order to effectively describe the damage process of composite laminates and reduce the complexity of material model, a mixed damage model based on Linde Criteria and Hashin Criteria is proposed for prediction of impact damage in the study. The mixed damage model can predict baisc failure modes, including fiber fracture, matrix tensile damage, matrix compressive damage. Fiber damage and matrix damage in compression are described based on the progressive damage mechanics; and matrix damage in tension is described based on Continuous Damage Mechanics (CDM). Meanwhile, for interlaminar delamination, damage is described by cohesive model. A finite element model is established to analyze the damage process of composite laminate. A good agreement is got between damage predictions and experimental results.
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40

Katerelos, Dionisios T. G. "Investigation of the Free Edge Interlaminar Stresses Dependence on the PLY Thickness and Orientation." Advanced Composites Letters 15, no. 1 (January 2006): 096369350601500. http://dx.doi.org/10.1177/096369350601500102.

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Among the principal damage modes in composite laminates, is delamination. Design details, such as free, straight or curved, edges, induce large local out-of-plane loads, generating interlaminar stresses. In the present work, the effect of ply thickness and the angle between two adjacent layers on the interlaminar stresses developed at the vicinity of straight and curved free edges in composite laminates under thermomechanical loading is examined. The results are obtained by the application of a 3-dimensional Finite Element Analysis.
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41

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.

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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 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.
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42

Wang, Qinghua, Shien Ri, Hiroshi Tsuda, Yosuke Takashita, Ryuta Kitamura, and Shinji Ogihara. "Interlaminar Shear Behavior of Laminated Carbon Fiber Reinforced Plastic from Microscale Strain Distributions Measured by Sampling Moiré Technique." Materials 11, no. 9 (September 11, 2018): 1684. http://dx.doi.org/10.3390/ma11091684.

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In this article, the interlaminar shear behavior of a [±45°]4s laminated carbon fiber reinforced plastic (CFRP) specimen is investigated, by utilizing microscale strain mapping in a wide field of view. A three-point bending device is developed under a laser scanning microscope, and the full-field strain distributions, including normal, shear and principal strains on the cross section of CFRP, in a three-point bending test, are measured using a developed sampling Moiré technique. The microscale shear strain concentrations at interfaces between each two adjacent layers were successfully detected and found to be positive-negative alternately distributed before damage occurrence. The 45° layers slipped to the right relative to the −45° layers, visualized from the revised Moiré phases, and shear strain distributions of the angle-ply CFRP under different loads. The absolute values of the shear strain at interfaces gradually rose with the increase of the bending load, and the sudden decrease of the shear strain peak value implied the occurrence of interlaminar damage. The evolution of the shear strain concentrations is useful in the quantitative evaluation of the potential interlaminar shear failure.
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43

Qian, Guoping, Shunjun Li, Huanan Yu, and Xiangbing Gong. "Interlaminar Bonding Properties on Cement Concrete Deck and Phosphorous Slag Asphalt Pavement." Materials 12, no. 9 (May 1, 2019): 1427. http://dx.doi.org/10.3390/ma12091427.

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The slippage damage caused by weak interlaminar bonding between cement concrete deck and asphalt surface is a serious issue for bridge pavement. In order to evaluate the interlaminar bonding of cement concrete bridge deck and phosphorous slag (PS) asphalt pavement, the shear resistance properties of the bonding layer structure were studied through direct shear tests. The impact of PS as a substitute of asphalt mixture aggregate, interface characteristics, normal pressure, waterproof and cohesive layer types, temperature and shear rate on the interlaminar bonding properties were analyzed. The test results indicated that the interlaminar bonding of bridge deck pavement is improved after asphalt mixture fine aggregate was substituted with PS and PS powder, and the result indicated that the shear strength of grooved and aggregate-exposed interfaces is significantly higher than untreated interface, the PS micro-powder or anti-stripping agent can also improve the adhesion between layers when mixed into SBS asphalt. This study provided important theoretical and practical guidance for improving the shear stability of bridge deck pavement.
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44

Sánchez-Romate, Xoan F., Andrés Alvarado, Alberto Jiménez-Suárez, and Silvia G. Prolongo. "Carbon Nanotube Reinforced Poly(ε-caprolactone)/Epoxy Blends for Superior Mechanical and Self-Sensing Performance in Multiscale Glass Fiber Composites." Polymers 13, no. 18 (September 18, 2021): 3159. http://dx.doi.org/10.3390/polym13183159.

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In this paper, a novel carbon nanotube (CNT) polycaprolactone (PCL), epoxy, and glass fiber (GF) composite is reported. Here, the nanoreinforced composites show a flexural strength increase of around 30%, whereas the interlaminar shear strength increases by 10–15% in comparison to unenhanced samples. This occurs because the addition of the CNTs induces a better PCL/epoxy/GF interaction. Furthermore, the nanoparticles also give novel functionalities to the multiscale composite, such as strain and damage monitoring. Here, the electrical response of the tensile- and compressive-subjected faces was simultaneously measured during flexural tests as well as the transverse conductivity in interlaminar tests, showing an exceptional capability for damage detection. Moreover, it was observed that the electrical sensitivity increases with PCL content due to a higher efficiency of the dispersion process that promotes the creation of a more uniform electrical network.
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45

Williams, J. C., S. W. Yurgartis, and J. C. Moosbrugger. "Interlaminar Shear Fatigue Damage Evolution of 2-D Carbon-Carbon Composites." Journal of Composite Materials 30, no. 7 (May 1996): 785–99. http://dx.doi.org/10.1177/002199839603000702.

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46

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.

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47

Zhang, Han, Yi Liu, Emiliano Bilotti, and Ton Peijs. "In-Situ Monitoring of Interlaminar Shear Damage in Carbon Fibre Composites." Advanced Composites Letters 24, no. 4 (July 2015): 096369351502400. http://dx.doi.org/10.1177/096369351502400405.

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The in-situ damage sensing of carbon/epoxy composites during interlaminar shear testing is investigated. Next to direct monitoring of woven fabric carbon/epoxy reference laminates, the introduction of carbon nanotubes (CNTs) onto these carbon fibre fabrics via a spray coating technique for damage sensing is evaluated. We observed very different sensing behaviour compared to previous studies, which is believed to be more useful for real applications. Through-thickness measurements showed for both reference and CNT modified specimens a continuous increase in electrical resistivity, due to reduced contact areas and conductive pathways. The effect of the introduced CNT network at the interfacial region is also been compared and analysed.
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48

Bajpai, Vivek, and Ramesh Singh. "Brittle damage and interlaminar decohesion in orthogonal micromachining of pyrolytic carbon." International Journal of Machine Tools and Manufacture 64 (January 2013): 20–30. http://dx.doi.org/10.1016/j.ijmachtools.2012.07.007.

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49

Goodarzi, Mohammad Saeed, Hossein Hosseini-Toudeshky, and Hadi Ghashochi-bargh. "Nanoindentation characterization of Glass/Epoxy composite for viscoelastic damage interlaminar modeling." Engineering Fracture Mechanics 226 (March 2020): 106873. http://dx.doi.org/10.1016/j.engfracmech.2020.106873.

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50

Liu, Xiang, Weimin Gu, Qiwen Liu, Xin Lai, and Lisheng Liu. "Damage of Hygrothermally Conditioned Carbon Epoxy Composites under High-Velocity Impact." Materials 11, no. 12 (December 12, 2018): 2525. http://dx.doi.org/10.3390/ma11122525.

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The influence of hygrothermal aging on high-velocity impact damage of carbon fiber-reinforced polymer (CFRP) laminates is investigated. Composite laminate specimens were preconditioned in water at 70 °C. The laminates were subsequently impacted by flat-, sphere-, and cone- ended projectiles with velocities of 45, 68, and 86 m/s. The incident and residual velocities were collected during the impact test. The impact-induced damages were measured by ultrasonic C-scan, a digital microscope system, and a scanning electron microscope. The results show that the hygrothermally conditioned laminates offer a higher energy absorption during high-velocity impact. Due to the weakening of the interlaminar properties, the hygrothermally conditioned laminates are more susceptible to delamination failure, and shear-induced debonding dominates. The projected delamination area increases with the increment of impact velocity. The damaged region becomes close to a circular shape after hydrothermal conditioning, and close to a rhomboidal shape for the dry specimens.
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