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Journal articles on the topic 'Laminate; Impact; Failure'
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1
Zhou, Wei, Mao Sheng Cao, Hai Bo Jin, Yi Long Lei, and Ji Li Rong. "Compressive Failure of Carbon/Epoxy Laminate Composites under High Impact Loading." Key Engineering Materials 324-325 (November 2006): 1237–40. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.1237.
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The effect of strain rate on the dynamic compressive of carbon/epoxy composite materials was investigated via the split Hopkinson pressure bar (SHPB) technique. The specimens were tested in the thickness, as well as in the in-plane direction at different high strain rates. The macro- and micro-fracture morphology of the damaged laminated specimens was obtained utilizing the scanning electron microscope (SEM). The experimental results showed that the compressive properties could be significantly affected by the strain rates. The compressive strength and the ultimate strain in the in-plane direction were obviously lower than that in the thickness direction. As the strain rate increased, the laminate had not enough time to respond, the splitting failure of 0° ply of laminates loaded in-plane along 0° was firstly found, then interfacial crack and delamination were induced, the specimens were crushed to fragments at the highest strain rate. No obvious damage of laminates loaded through the thickness could be observed at strain rate below 2000 s-1. The main way of the dynamic compressive failures through the thickness was shear failure due to the brittle fracture of the fiber at 2260 s-1.
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Yuan, Q., T. Czigany, and L. Ye. "Failure Behaviour of Cross-Ply Carbon Fibre/Epoxy Laminates Subjected to Transverse Impact and Static Perforation." Advanced Composites Letters 9, no. 5 (September 2000): 096369350000900. http://dx.doi.org/10.1177/096369350000900506.
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Cross-ply carbon fibre reinforced epoxy laminates (CF/EP) were toughened with interleaf consisting of random PET fibre mat embedded in a modified epoxy resin. The interleaved laminate had a smaller delamination area but higher energy absorption than the base laminate during transverse impact perforation. In static tests, the interleaved laminate had a higher maximum load and greater deformation at the perforation, compared to the base laminate. The damage development was monitored using acoustic emission technique. The interleaved laminate had less cumulative acoustic emission events than the base laminate. The distribution of the rise time was used to identify the major failure mechanisms.
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Olsson, R. "Modelling of impact damage zones in composite laminates for strength after impact." Aeronautical Journal 116, no. 1186 (December 2012): 1349–65. http://dx.doi.org/10.1017/s0001924000007673.
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AbstractThis paper reviews findings on the type, morphology and constitutive behaviour of impact damage zones during loading after impact and their effect on the laminate strength and stability. The paper is limited to tape prepreg based monolithic laminates, although some similarities exist with impact damage in textile based laminates. Damage zones have a complex geometry with several damage types, which results in an interaction and competition between different failure mechanisms, e.g. local and global buckling, compressive failure, and delamination growth. Hence, simplified damage models may provide incorrect predictions of the failure load and failure mechanisms after impact. The constitutive behaviour of damage zones has been studied experimentally in tension and compression using an inverse method, and the results have been compared with detailed FE models of a generic impact damage. The paper is concluded with a discussion on analytical and computational models to predict the resulting strength of impacted laminates.
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Farrow, I. R., K. Potter, A. Fisher, and M. Kelly. "Impact of Adhesively Bonded Composite Joints with Edge Effect." Advanced Composites Letters 9, no. 6 (November 2000): 096369350000900. http://dx.doi.org/10.1177/096369350000900603.
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A pilot project has been carried out to investigate the effect of impact on single-lap bonded composite joints based on AS4-8552 laminates and Cybond BR4535A adhesive. Low velocity impacts at an energy level sufficient to cause barely visible impact damage, were conducted on single lap joint specimens at different joint positions. Impact caused delaminations in the upper and lower laminates and localised through-thickness cracking in the adhesive. Residual tensile joint strengths of the impacted joint specimens with near-edge damage were reduced to approximately 50% of the un-impacted value. Failure surface inspections revealed localised through-thickness adhesive shear cracking as a governor of the original impact delamination pattern in the laminates and laminate delamination as the cause of ultimate tensile failure.
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Koziol, Mateusz. "Mechanical Performance of Polymer-Matrix Laminate Reinforced with 3D Fabric during Three-Point Impact Bending." Solid State Phenomena 246 (February 2016): 193–96. http://dx.doi.org/10.4028/www.scientific.net/ssp.246.193.
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The paper presents the analysis of course and the results of impact 3-point bending tests conducted with use of instrumented Charpy hammer (CEAST RESIL 50 hammer + MC101 registrator + CALKA J computer program) on GFRP laminate specimens cut of the panels manufactured by RTM method on base of classic plain-woven fabric preform and 3D fabric. The specimens of the 3D laminate were cut alternatively along (W direction) and transverse (P direction) to the translaminar interweave strands. It was found that maximum force obtained in the tests is comparable for both the classic and the 3D laminates. Deformability of the 3D (W) specimen is by about 20% higher than those of the classic laminate, whereas it is higher by even 75% for 3D (P). The trend of deformability observed for the tested laminates differs from known trends characteristic for static conditions what confirms different material response mechanisms at low and higher load rate. Failure energy in the classic and in the 3D (W) specimen is on comparable level. However, 3D (P) specimen showed slightly lower summary failure energy than the classic one and almost twice a high failure initiation energy (first effects of failure occur before maksimum load is gained).
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Kumar, M. Ashok, A. M. K. Prasad, and D. V. Ravishankar. "Effect of Quasi-Static Loading on the Composite Laminates." Advanced Engineering Forum 20 (January 2017): 10–21. http://dx.doi.org/10.4028/www.scientific.net/aef.20.10.
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The low velocity impact is a common phenomenon which occurs in fiber reinforced polymer composite products like LPG cylinders, fighter aircraft fuel drop tanks, aircraft wing surfaces, sports goods etc. The consequences of low velocity impact will create a considerable damage and ultimately lead to a premature failure of the structure. Hence the polymer composites for engineering applications must be provided with a better design solution. From the literature survey it is observed that, the response of composite laminates subjected to quasi-static loading, exhibits similar results as that of low velocity impact. Polymer reinforced composites are poor in damage tolerance with better strength to weight ratio than conventional materials. However composite materials can be tailored to meet the design requirements by manipulating fiber orientations and laminae stacking sequence. In the present paper, principles of classical laminate theory are considered for analysis. FEM is implemented for thorough understanding of the failure mechanism of each laminate by layer wise. Simulated quasi-static loading tests and observed the layer wise distribution of transverse strain intensity. The experimental setup is designed and fabricated as per ASTM D 6264 standards. The E-glass/epoxy composite laminate is quasi-statically loaded at its center by a steel ball indenter of diameter 8.7mm and its response is measured by the degree of opacity or translucency in terms of interlaminar and intra-laminar damage area. The stacking sequence of composite laminates are chosen as [00/600]12, [00/750]12 and [00/900]12. The damage areas obtained from numerical analysis are in good agreement with experimental results.
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Zhang, Chen, Yunfei Rao, Zhe Li, and Wei Li. "Low-Velocity Impact Behavior of Interlayer/Intralayer Hybrid Composites Based on Carbon and Glass Non-Crimp Fabric." Materials 11, no. 12 (December 5, 2018): 2472. http://dx.doi.org/10.3390/ma11122472.
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Composites have gained wide use in structural applications; however, they are sensitive to impact damage. The use of hybrid composites is an effective way to overcome this deficiency. The effects of various hybrid structures of interlayer and intralayer warp-knitted fabrics with carbon and glass fibers on the low-velocity impact behavior of composite laminates were studied. Drop-weight impact tests were conducted on two types of interlayer, sandwich and intralayer hybrid composite laminates, which were compared with homogenous composite laminates. During low-velocity impact tests, the time histories of impact forces and absorbed energy by laminate were recorded. The failure modes were analyzed using the micro-CT (computed tomography) and C-scan techniques. The results revealed that the hybrid structure played an important role in peak force and the absorbed energy, and that the hybrid interface had an influence on damage modes, whereas the intralayer hybrid composite laminate damage was affected by the impact location. The intralayer hybrid laminate with C:G = 1:1 exhibited better impact resistance compared to the other hybrid structures.
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Schwab, Martin, Melanie Todt, and Heinz E. Pettermann. "A multiscale approach for modelling impact on woven composites under consideration of the fabric topology." Journal of Composite Materials 52, no. 21 (February 14, 2018): 2859–74. http://dx.doi.org/10.1177/0021998318755865.
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A computationally efficient multiscale modelling approach for predicting impact damage within fabric reinforced laminated composites is presented. In contrast to common ply-level approaches, the topology of a multi-layered fabric reinforced laminate is resolved at tow-level for a sub-domain embedded in a shell layer with homogenised representation of the laminate. The detailed sub-domain is entirely modelled using shell elements, where material nonlinearities such as damage and plasticity-like behaviour of the tows, inelastic behaviour of unreinforced resin zones up to failure and delamination between plies are accounted for. To exemplify the capabilities of the approach, an explicit finite element simulation of a laminated plate consisting of eight carbon fabric reinforced epoxy plies with eight harness satin weaving style in a drop weight impact test setup is conducted. The spatial and temporal distribution of intra- and inter-ply damage is predicted and the total energy absorption by the plate, as well as the contributions of individual damage mechanisms are evaluated. The predictions show very good agreement with corresponding experimental data from the literature and give insight into the impact behaviour of the laminate beyond the capability of usual experiments. The new approach allows to resolve the stress concentrations due to fabric topology in detail. Compared to common ply-level approaches this is reflected in different predicted energy absorptions per mechanism although, the total energy absorption hardly differs. This is especially important when the post impact behaviour of laminates is predicted as it is strongly influenced by the extent of the individual damage mechanisms.
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Hasan, Md Zahid. "Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike." Aerospace 7, no. 3 (March 17, 2020): 28. http://dx.doi.org/10.3390/aerospace7030028.
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Many high-strength composite materials have been developed for aircraft structures. GLAss fiber REinforced aluminum (GLARE) is one of the high-performance composites. The review of articles, however, yielded no study on the impact damage of heated GLARE laminates. This study, therefore, aimed at developing a numerical model that can delineate the continuum damage of GLARE 5A-3/2-0.3 laminates at elevated temperatures. In the first stage, the inter-laminar interface failure of heated GLARE laminate had been investigated at room temperature and 80 °C. The numerical analysis employed a three-dimensional GLARE 5A-3/2-0.3 model that accommodated volumetric cohesive interfaces between mating material layers. Lagrangian smoothed particles populated the projectile. The model considered the degradation of tensile and shear modulus of glass fiber reinforced epoxy (GF/EP) at 80 °C, while incorporated temperature-dependent critical strain energy release rate of cohesive interfaces. When coupled with the material particulars, an 82 m/s bird impact at room temperature exhibited delamination first in the GF/EP 90°/0° interface farthest from the impacted side. Keeping the impact velocity, interface failure propagated at a slower rate at 80 °C than that at room temperature, which was in agreement with the impact damage determined in the experiments. The outcomes of this study will help optimize a GLARE laminate based on the anti-icing temperature of aircraft.
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Kim, Jae Hoon, Duck Hoi Kim, Hu Shik Kim, and Byoung Jun Park. "A Study on Low Velocity Impact of Woven Glass/Phenolic Composite Laminates Considering Environmental Effects." Key Engineering Materials 297-300 (November 2005): 1303–8. http://dx.doi.org/10.4028/www.scientific.net/kem.297-300.1303.
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The objectives of this study are to evaluate the internal damage and compressive residual strength of composite laminate by impact loading. To investigate the environmental effects, as-received and accelerated-aged glass/phenolic laminates are used. UT C-Scan is used to determine the impact damage characteristics and CAI tests are carried out to evaluate quantitatively the reduction of compressive strength by impact loading. The damage modes of the woven glass/phenolic laminates are evaluated. In the case of the accelerated-aged laminates, as aging time increases, initial failure energy and residual compressive strength decrease.
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Venkatraman, S., and S. Kishore. "Impact Studies in Glass Epoxy Laminates Containing Foam." Journal of Reinforced Plastics and Composites 16, no. 7 (July 1997): 618–30. http://dx.doi.org/10.1177/073168449701600703.
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E glass epoxy laminates were made by a hand layup process. Laminates containing the central portion having either a 2 layer larger cell sized thicker width or a 3 layer thinner width flexible foam were also fabricated by the same route using a room temperature curing resin. Test coupons were cut from the fabricated laminates and impacted by a pendulum, having facility to load specific values for its mass, on the face of the laminate. Impacts were made by a single mass or a two stage impact operations involving preliminary hits, first by a smaller mass and then by a larger mass. The energy values associated with the process were computed. Macroscopy on failed test coupons was done to identify the dominant mode of failure and correlate the mechanical test data with failure processes. It is seen that foam bearing materials absorb increased impact energy compared to plain laminates and further, the cell-size/interfacial area of the foam plays a significant role in altering the fracture phenomena.
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Julias, A. Arockia, and Vela Murali. "Experimental impact study on unidirectional glass-carbon hybrid composite laminates." Science and Engineering of Composite Materials 23, no. 6 (November 1, 2016): 721–28. http://dx.doi.org/10.1515/secm-2013-0063.
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AbstractIn this experimental study, the impact response of unidirectional hybrid composite laminate was investigated. Hybrid laminates with different stacking sequences were fabricated, using unidirectional glass and carbon fiber as reinforcement and epoxy resin as matrix. ASTM standard D5628 was followed to conduct the experiment using the instrumented drop weight impact test apparatus. All the square specimens were tested at an impact velocity of 3.43 m/s and the time histories of force and energy absorbed were recorded. The impacted specimens and their X-ray images were visually inspected to understand the failure pattern. The experimental results showed that the addition of carbon fiber increases the impact strength by absorbing more force and energy. Furthermore, the laminate can be stiffened with the carbon fiber layers by interfacing glass fiber layers on either side.
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Xiao-Yu, Sun, Teng Jian-Xin, He Zheng, and Gu Xuan. "A Study on the Failure Mechanisms of Composite Laminates Simultaneously Impacted by Two Projectiles." Advanced Composites Letters 27, no. 3 (May 2018): 096369351802700. http://dx.doi.org/10.1177/096369351802700302.
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With most studies concentrated on the single point isolated impact events, this work mainly investigates the failure mechanisms of composite laminates simultaneously impacted by two projectiles over low energies. A 3D intralaminar damage model combining continuum damage mechanics to analyze the in-ply damage and cohesive interface elements to simulate the delamination are applied to model the damage evolution of E-glass/epoxy composites simultaneously impacted by two projectiles. The damage model is incorporated into the Abaqus/Explicit by the subroutine VUMAT. A comparison between the simulated predictions and the experimental observations of laminates impacted by one projectile is made to verify the reasonability of the damage model applied. The simulation results indicate that the delamination initiation is not largely affected by the impact energy and the number of the projectiles. As the combined effects of the two projectiles on the laminate, the intersection of matrix damage areas in plies and the connection of delamination regions at interfaces, largely decrease the overall stiffness of the laminate and result in more serious damage.
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Zelepugin, S. A., A. S. Zelepugin, A. A. Popov, and D. V. Yanov. "Failure of the laminate composites under impact loading." Journal of Physics: Conference Series 1115 (November 2018): 042018. http://dx.doi.org/10.1088/1742-6596/1115/4/042018.
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de Corte, Wouter, Arne Jansseune, Wim van Paepegem, and Jan Peeters. "Elastic Properties and Failure Behavior of Tiled Laminate Composites." Key Engineering Materials 774 (August 2018): 564–69. http://dx.doi.org/10.4028/www.scientific.net/kem.774.564.
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This paper focuses on the elastic properties and the failure behavior of tiled laminate composites. Such laminates, in which the plies are not parallel to the outer surfaces are found in InfraCore® based GFRP panels. This technology is developed for the construction of a robust FRP panel that is applicable for highly loaded structures, e.g. for bridges or lock gates. In general, the drawback in traditional FRP sandwich structures has always been debonding of skin and core. Such a debonding problem may occur after impact, followed by fatigue loading. Through the use of the InfraCore® technology, debonding is no longer possible, as multiple overlapping Z-shaped and two-flanged web structures are alternated with polyurethane foam cores acting as non-structural permanent formwork. Consequently, the fibers in the upper and lower skins as well as in the vertical webs run in all directions, especially in the connection between them, rendering a resin-dominated crack propagation impossible. As a result of the integration of core and skin reinforcement, a skin material is created in which the reinforcement is not parallel to the outer surfaces, but at a small angle. Such stacking is called a tiled laminate (TL), as opposed to plane-parallel (PP) and is not fully described by the classic laminate theory. In the paper, finite element analysis is used to assess the effect of the ply angle and the interlaminar properties on the assessment of stiffness and failure behavior of a tiled laminate.
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Chen, Fengyan, Yong Peng, Xuanzhen Chen, Kui Wang, Zhixiang Liu, and Chao Chen. "Investigation of the Ballistic Performance of GFRP Laminate under 150 m/s High-Velocity Impact: Simulation and Experiment." Polymers 13, no. 4 (February 17, 2021): 604. http://dx.doi.org/10.3390/polym13040604.
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The ballistic resistance of GFRP laminates subjected to high-velocity impact was studied. Based on the damage situation of GFRP laminate observed from the single-stage gas gun testing, the three-dimensional (3D) model combining strain rate effect and Hashin failure criterion was established, and the result presented good agreement between the simulation and experiment. Three factors, including layer angle, stacking sequence and proportion of different layer angles, were taken into consideration in the models. An orthogonal test method was used for the analysis, which can reduce the number of simulations effectively without sacrificing the accuracy of the result. The result indicated a correlation between the ballistic resistance and layouts of GFRP laminates, on which the stacking sequence contributed stronger influence. What was more, the laminate with layer angles 0°/90° and ±45° presented greater ballistic resistance than the other angle pairs, and adopting an equal proportion of different layer angles is helpful for GFRP laminates to resist impact as well.
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Jakubczak, Patryk, Magda Droździel, Piotr Podolak, and Jesus Pernas-Sánchez. "Experimental Investigation on the Low Velocity Impact Response of Fibre Foam Metal Laminates." Materials 14, no. 19 (September 23, 2021): 5510. http://dx.doi.org/10.3390/ma14195510.
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The combination of fibre metal laminates (FML) and sandwich structures can significantly increase the performance under impact of FMLs. The goal of this work was to create a material that will combine the superior properties of FMLs and foam sandwich structures in terms of the impact resistance and simultaneously have lower density and fewer disadvantages related to the manufacturing. An extensive impact testing campaign has been done using conventional fibre metal laminates (carbon- and glass-based) and in the proposed fibre foam metal laminates to assess and compare their behaviour. The main difference was observed in the energy absorption mechanisms. The dominant failure mechanism for fibre foam laminates is the formation of delaminations and matrix cracks while in the conventional fibre metal laminate the main failure mode is fibre cracking due to high local stress concentrations. The reduction in the fibre cracking leads to a better after-impact resistance of this type of structure improving the safety of the structures manufactured with these materials.
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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.
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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, 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.
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Ravandi, M., U. Kureemun, M. Banu, WS Teo, Liu Tong, TE Tay, and HP Lee. "Effect of interlayer carbon fiber dispersion on the low-velocity impact performance of woven flax-carbon hybrid composites." Journal of Composite Materials 53, no. 12 (October 23, 2018): 1717–34. http://dx.doi.org/10.1177/0021998318808355.
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This work investigates the effects of interlayer hybrid fiber dispersion on the impact response of carbon-flax epoxy hybrid laminates at low carbon volume fractions, and benchmarks the mechanical performance enhancement against the non-hybrid flax epoxy. Five hybrid laminate stacking sequences with similar carbon-to-flax weight ratio were fabricated and subjected to low-velocity impact at three different energy values, generating non-perforated and perforated damage states. A virtual drop-weight impact test that models intralaminar failure based on continuum damage mechanics approach, and delamination using cohesive elements, was also implemented to evaluate the material behavior and damage development in the composites. Simulation results were then verified against experimental data. Results suggested that positioning stiffer carbon plies at the impact face does not necessarily lead to enhancement of the hybrid's impact properties. On the contrary, flax plies at the impacted side lead to significant improvement in impact resistance compared to the non-hybrid flax composite with similar thickness. Results of finite element analysis showed that carbon plies play a significant role in the hybrid laminate's energy absorption characteristics due to lower failure strain.
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Hosseini-Toudeshky, Hossein, M. Saeed Goodarzi, and Bijan Mohammadi. "Multiple Delaminations Growth in Composite Laminates under Compressive Cyclic Loading in Post-Buckling." Applied Mechanics and Materials 225 (November 2012): 195–200. http://dx.doi.org/10.4028/www.scientific.net/amm.225.195.
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Due to discontinuity of mechanical properties in composite laminates, failure occurs in different damage mechanisms. Delamination growth of adjacent layers is a major failure mechanism in laminates with various layup configurations. Pre existing delamination may initiate in composite laminate before use, due to impact in assembly and fabrication process. Cyclic compressive loading may cause delamination growth due to both post-bucking behavior and fatigue nature of loading. In this paper, a 3D mixed-mode interface element model has been developed to simulate the growth of multiple delaminations under compressive cyclic loading. For this purpose, the presented model should be able to handle the geometry nonlinearity of post-buckling and material nonlinearity of cohesive zone constitutive law under cyclic loading at interfaces. Because of mixed-mode condition of stress field at the delamination-front of post-buckled laminates, a mixed-mode bilinear constitutive law has been used as user material in this model. Paris Law has been used to relate the energy release rate to the fatigue crack growth in cohesive zone. A composite laminate with pre-existing delamination under buckling load, available from the literature has been reproduced with the present approach. Finally, laminates containing multiple delaminations in various interface layers have been analyzed under compressive fatigue loading. It is shown that the pre-existing delamination with more depth from the surface of laminate causes more initial static and fatigue delamination growth rate.
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Mahesh, Vishwas, Ashutosh Nilabh, Sharnappa Joladarashi, and Satyabodh M. Kulkarni. "Analysis of Impact Behaviour of Sisal-Epoxy Composites under Low Velocity Regime." Revue des composites et des matériaux avancés 31, no. 1 (February 28, 2021): 57–63. http://dx.doi.org/10.18280/rcma.310108.
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The present study concentrates on development of conceptual proof for sisal reinforced polymer matrix composite for structural applications subjected to low velocity impact using a finite element (FE) approach. The proposed sisal-epoxy composite of various thicknesses of 3.2 mm, 4 mm and 4.8 mm is subjected to different impact velocities of 1 m/s, 2 m/s and 3 m/s ranging in the low velocity impact regime to study the energy absorbed and damage mitigation behaviour of the proposed composite. The consequence of velocity of impact and thickness of laminate on the sisal epoxy composite’s impact behaviour is assessed statistically using Taguchi’s experimental design. Outcome of the present study discloses that the energy absorption increases with increased impact velocity and laminate thickness. However, the statistical study shows that impact velocity is predominant factor affecting the impact response of sisal epoxy composite laminate compared to laminate thickness. The role of matrix and fiber in damage initiation is studied using Hashin criteria and it is found that matrix failure is predominant over the fiber failure.
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Jakubczak, Patryk, Jarosław Bienias, and Barbara Surowska. "The influence of fibre orientation in aluminium–carbon laminates on low-velocity impact resistance." Journal of Composite Materials 52, no. 8 (July 7, 2017): 1005–16. http://dx.doi.org/10.1177/0021998317719569.
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The objective of this study was to assess the influence of fibre orientation in hybrid fibre metal laminates based on aluminium and carbon fibres on the impact of low-velocity impact. The analysis was conducted on the basis of fibre metal laminate impact resistance criteria, including impact force, energy absorption, bending stiffness, damage area and failure. To assess the resistance of various aluminium–carbon laminates, qualitative and quantitative evaluation criteria were employed, including the shape of the force–time curve, characteristic impact forces, energy absorption, bending stiffness, damage area and external failure analysis. Among others, authors concluded that no explicit influence of the composite layer fibre orientation on the shape and value of characteristic forces was observed. It was found that the fibre orientation and the changing number of interfaces of low durability show no explicit influence on the size and shape of delaminations.
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Abrate, Serge. "Impact on Laminated Composite Materials." Applied Mechanics Reviews 44, no. 4 (April 1, 1991): 155–90. http://dx.doi.org/10.1115/1.3119500.
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Laminated composite materials are used extensively in aerospace and other applications. With their high specific modulus, high specific strength, and the capability of being tailored for a specific application, these materials offer definite advantages compared to more traditional materials. However, their behavior under impact is a concern, since impacts do occur during manufacture, normal operations, or maintenance. The situation is critical for impacts which induce significant internal damage, undetectable by visual inspection, that cause large drops in the strength and stability of the structure. Impact dynamics, including the motion of both the impactor and the target and the force developed at the interface, can be predicted accurately using a number of models. The state of stress in the vicinity of the impact is very complex and requires detailed analyses. Accurate criteria for predicting initial failure are generally not available, and analyses after initial failure are questionable. For these reasons, it can be said that a general method for estimating the type and size of impact damage is not available at this time. However, a large amount of experimental data has been published, and several important features of impact damage have been identified. In particular, interply delaminations are known to occur at the interface between plies with different fiber orientation. Their shape is generally elongated in the direction of the fibers in the lower ply at that interface. The delaminated area is known to increase linearly with the kinetic energy of the impactor after a certain threshold value has been reached. The effect of impact damage on the properties of the laminate has obvious implications for design and inspection of actual structures. Experimental results concerning the residual strength of impact damaged specimens subjected to tension, compression, shear, bending, and both static and fatigue loading are available. Analyses concentrate primarily on predicting residual tensile and compressive strength. In order to fully understand the effect of foreign object impact damage, one should understand impact dynamics and be able to predict the location, type, and size of the damage induced and the residual properties of the laminate. This article is organized along these lines and presents a comprehensive review of the literature on impact of laminated composites, considering both experimental and analytical approaches.
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Ahmadi, H., M. Ekrami, H. Sabouri, and M. Bayat. "Experimental and numerical investigation on the effect of projectile nose shape in low-velocity impact loading on fiber metal laminate panels." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (October 9, 2018): 3665–79. http://dx.doi.org/10.1177/0954410018804384.
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In this paper, low-velocity impact responses of 2/1 GLARE 3 (a commercial type of fiber metal laminate) specimens were studied experimentally and numerically. The effects of indenter's nose shape (flat, conical, and hemispherical) on energy absorption and failure mechanisms were thoroughly investigated. Drop weight testing machine with different impact energies was used for experimental tests and numerical simulation was also carried out. Failure mechanisms, such as delamination, debonding, aluminum sheet rupture, and composite laminate fracture, were discussed by sectioning the tested specimens. The results indicate that maximum and minimum contact force occurred with flat and conical indenters, respectively. Also, the target absorbs the utmost energy under the penetration of flat indenter and least energy during conical indenter perforation. It is depicted that the deflection at the peak load represents the main failure of the panel. Consequently, front aluminum sheet failure is determinant in fiber metal laminate panels impacted by flat and hemispherical indenters where back aluminum sheet is more significant for fiber metal laminate panels impacted by the conical indenter. Numerical simulation verified by experimental results is extended to lower impact weights and more velocities, which are discussed.
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Montero, Marc Villa, Ehsan Barjasteh, Harsh K. Baid, Cody Godines, Frank Abdi, and Kamran Nikbin. "Multi-Scale Impact and Compression-After-Impact Modeling of Reinforced Benzoxazine/Epoxy Composites using Micromechanics Approach." Journal of Multiscale Modelling 08, no. 01 (February 22, 2017): 1750002. http://dx.doi.org/10.1142/s1756973717500020.
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A multi-scale micromechanics approach along with finite element (FE) model predictive tool is developed to analyze low-energy-impact damage footprint and compression-after-impact (CAI) of composite laminates which is also tested and verified with experimental data. Effective fiber and matrix properties were reverse-engineered from lamina properties using an optimization algorithm and used to assess damage at the micro-level during impact and post-impact FE simulations. Progressive failure dynamic analysis (PFDA) was performed for a two step-process simulation. Damage mechanisms at the micro-level were continuously evaluated during the analyses. Contribution of each failure mode was tracked during the simulations and damage and delamination footprint size and shape were predicted to understand when, where and why failure occurred during both impact and CAI events. The composite laminate was manufactured by the vacuum infusion of the aero-grade toughened Benzoxazine system into the fabric preform. Delamination footprint was measured using C-scan data from the impacted panels and compared with the predicated values obtained from proposed multi-scale micromechanics coupled with FE analysis. Furthermore, the residual strength was predicted from the load-displacement curve and compared with the experimental values as well.
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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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Ghazali, Nazwan, Mohamed Shaik Dawood, and S. M. Kashif. "Effects of Piezoelectric Actuation on Delamination in Transversely Loaded Composite Plates." Advanced Materials Research 1115 (July 2015): 560–63. http://dx.doi.org/10.4028/www.scientific.net/amr.1115.560.
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Fiber reinforced composite materials are known to have poor tolerance to impact loads. Damages can be observed in the forms of matrix crack, fiber failure and delamination. In the case of low velocity impact, delamination is often a major concern due to its hidden nature. In this work, the effects of piezoelectric actuation on delamination in composite plates subjected to low velocity impact have been studied using LS-DYNA. It was found that, piezoelectric actuators can be used to reduce delamination in composite laminates. This was achieved by actuating the laminate to curve in the opposite direction of the incoming impact load.
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Luo, Xiang Cheng, Tao Zhang, and Qing Shan Wang. "Ply Thickness’ Effect on Composite Laminate under Low-Velocity Impact." Advanced Materials Research 989-994 (July 2014): 74–78. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.74.
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Based on the two-dimensional Hashin failure criteria and the introduction of material degradation damage factor, low-speed impact model of composite laminated plate was established by ABAQUS with fiber and matrix’s failure modes being taken into consideration. The mode is verified by referring to Karakuzu test. Next, it analyzes single ply thickness’ effect on laminated plate’s response and damaged under low-velocity impact. The result shows that with the thickness increasing, impact contact time and laminated plate impact point’s deflection displacement reduce, while the impact force and volatile shocks are more obvious.
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Yokoyama, Takashi. "Impact Compressive Failure of a Unidirectional Carbon/Epoxy Laminated Composite in Three Principal Material Directions." Materials Science Forum 706-709 (January 2012): 799–804. http://dx.doi.org/10.4028/www.scientific.net/msf.706-709.799.
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The impact compressive failure behavior of a unidirectional T700/2521 carbon/epoxy laminated composite in three principal material directions or fiber (1-), in-plane transverse (2-) and through-thickness (3-) directions is investigated on the conventional split Hopkinson pressure bar (SHPB). Cubic and rectangular block specimens with identical square cross section are machined from an about 10 mm thick composite laminate. The uniaxial compressive stress-strain curves up to failure at quasi-static and intermediate strain rates are measured on an Instron testing machine. It is shown that the ultimate compressive strength and strain exhibit no strain-rate effect in the 1-direction, but a slight strain-rate effect in the 2-and 3-direction over a range of strain rates from10-3to 103/s.
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Jakubczak, P., B. Surowska, and J. Bieniaś. "Evaluation of Force-Time Changes During Impact of Hybrid Laminates Made of Titanium and Fibrous Composite." Archives of Metallurgy and Materials 61, no. 2 (June 1, 2016): 689–94. http://dx.doi.org/10.1515/amm-2016-0117.
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AbstractFibre metal laminates (FML) are the modern hybrid materials with potential wide range of applications in aerospace technology due to their excellent mechanical properties (particularly fatigue strength, resistance to impacts) and also excellent corrosion resistance. The study describes the resistance to low velocity impacts in Ti/CFRP laminates. Tested laminates were produced in autoclave process. The laminates were characterized in terms of their response to impacts in specified energy range (5J, 10J, 20J). The tests were performed in accordance with ASTM D7137 standard. The laminates were subjected to impacts by means of hemispherical impactor with diameter of 12,7 mm. The following values have been determined: impact force vs. time, maximum force and the force at which the material destruction process commences (Pi). It has been found that fibre titanium laminates are characterized by high resistance to impacts. This feature is associated with elasto-plastic properties of metal and high rigidity of epoxy - fibre composite. It has been observed that Ti/CFRP laminates are characterized by more instable force during impact in stage of stabilization of impactor-laminate system and stage of force growth that glass fibre laminates. It has been observed more stable force decrease in stage of stress relaxation and withdrawal of the impactor. In energy range under test, the laminates based on titanium with glass and carbon fibres reinforcement demonstrate similar and high resistance to low-velocity impact, measured by means of failure initiation force and impact maximum force.
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Zhang, X., F. Bianchi, and H. Liu. "Predicting low-velocity impact damage in composites by a quasi-static load model with cohesive interface elements." Aeronautical Journal 116, no. 1186 (December 2012): 1367–81. http://dx.doi.org/10.1017/s0001924000007685.
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AbstractA numerical model is developed for predicting low-velocity impact damage in laminated composites. Stacked shell elements are employed to model laminate plies with discrete interface elements in pre-determined zones to model the onset and propagation of matrix cracks and delamination. These interface elements are governed by a bi-linear cohesive failure law. Cohesive element zone size is determined by a separate finite element analysis using solid elements to identify the stress concentration sites. In order to save the computational effort, low-velocity impact load is modelled by quasi-static loading. Influence of contact force induced friction on shear driven mode II delamination is modelled by a friction model. For a clustered cross-ply laminate, calculated impact force and damage area are in good agreement with the test results. It is shown that matrix cracks should be included in the model in order to simulate delamination in adjacent interface. The practical outcome of this research is a validated modelling approach that can be further improved for predicting low-velocity impact damage in other stacking sequences.
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Kinawy, Moustafa, Felice Rubino, Giacomo Canale, Roberto Citarella, and Richard Butler. "Face Damage Growth of Sandwich Composites under Compressive Loading: Experiments, Analytical and Finite Element Modeling." Materials 14, no. 19 (September 24, 2021): 5553. http://dx.doi.org/10.3390/ma14195553.
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Sandwich panels with composite laminate skins having [(±45C)2,(0C,0G)4,(±45C)2] stacking sequence (subscript C for carbon fibers, G for glass) and containing barely visible impact damage (BVID) induced on the whole sandwich structure impacted at low energy, were tested in edge after-impact-compression with load direction parallel and transversal to the fibers direction (0-dir.). The morphology of impact damage on the sandwich structure was determined by using ultrasonic C-Scan and visual observation of laminate cross section. A Digital Image Correlation (DIC) system was used to measure the delamination evolution during the test. Two different failure behaviors were observed in two different impacted panels. Panel with fibers oriented transversally to the compressive load showed an opening (Mode-I) propagation of a delamination, while the panel with fibers parallel to the load showed shear (Mode-II) propagation. The static load such to determine local buckling of the composite face and failure was experimentally measured. An analytical model was implemented to predict the static strength of laminate with Mode-I opening. An FE model was instead built to predict the local buckling failure mode of the laminate with BVID, which is the first phenomenon to appear. The results of the analytical model and the numerical simulation correlate well with the test.
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Lou, Xiaofei, Hongneng Cai, Pengfei Yu, Fei Jiao, and Xuecheng Han. "Failure analysis of composite laminate under low-velocity impact based on micromechanics of failure." Composite Structures 163 (March 2017): 238–47. http://dx.doi.org/10.1016/j.compstruct.2016.12.030.
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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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Bernhardt, S., M. Ramulu, and A. S. Kobayashi. "Low-Velocity Impact Response Characterization of a Hybrid Titanium Composite Laminate." Journal of Engineering Materials and Technology 129, no. 2 (July 13, 2006): 220–26. http://dx.doi.org/10.1115/1.2400272.
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The low-velocity impact response of a hybrid titanium composite laminate, known as TiGr, was compared to that of graphite/epoxy composite. The TiGr material comprised of two outer plies of titanium foil surrounding a composite core. The composite core was PIXA-M (a high temperature thermoplastic) reinforced by IM-6 graphite fibers and consolidated by an induction heating process. The impact response of TiGr was characterized by two modes of failure which differed by failure or nonfailure in tension of the bottom titanium ply. The ductility of titanium caused buckling by yielding whereas the brittle adjacent composite ply lead to fracture. The maximum failure force of the material correlated well with the previously reported static flexural data, and the material outperformed the commonly used graphite/epoxy.
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Wachowski, Marcin, Teresa Fras, Robert Kosturek, Lucjan Śnieżek, Ireneusz Szachogłuchowicz, and Krzysztof Grzelak. "The Effect of Hypervelocity Impact Loading on Explosively Welded Ti/Al/Al Plate." MATEC Web of Conferences 253 (2019): 01007. http://dx.doi.org/10.1051/matecconf/201925301007.
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The aim of this paper is to investigate the ballistic properties of explosively welded Ti6Al4V/AA1050/AA2519 laminate under hypervelocity (4000 m/s) impact loading of projectile made of aluminium ball. The paper describes the influence of the projectile impact energy on the structure of the laminate components and delamination of bonds depending on its strength and presence of intermetallic phases. Observation of the failure is performed for the plate impacted for aluminium alloy side. Results revealed ductile shearing as a dominant process leading to perforation.
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Xing, Du, He, Zhao, Zhang, and Li. "Finite Element Study on the Impact Resistance of Laminated and Textile Composites." Polymers 11, no. 11 (November 1, 2019): 1798. http://dx.doi.org/10.3390/polym11111798.
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The impact resistance of fiber-reinforced polymer composites is a critical concern for structure design in aerospace applications. In this work, experiments were conducted to evaluate the impact performance of four types of composite panels, using a gas-gun test system. Computational efficient finite element models were developed to model the high-speed ballistic impact behavior of laminate and textile composites. The models were first validated by comparing the critical impact threshold and the failure patterns against experimental results. The damage progression and energy evolution behavior were combined to analyze the impact failure process of the composite panels. Numerical parametric studies were designed to investigate the sensitivity of impact resistance against impact attitude, including impact deflection angles and projectile deflection angles, which provide a comprehensive understanding of the damage tolerance of the composite panels. The numerical results elaborate the different impact resistances for laminate and textile composites and their different sensitivities to deflection angles.
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Duan, Miaomiao, Zhufeng Yue, and Qianguang Song. "Investigation of damage to thick composite laminates under low-velocity impact and frequency-sweep vibration loading conditions." Advances in Mechanical Engineering 12, no. 10 (October 2020): 168781402096504. http://dx.doi.org/10.1177/1687814020965042.
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A detailed investigation of damage and failure mechanisms of composite laminates under low-velocity impact (LVI) by experimental tests and numerical modeling is presented. Five impact energy levels were investigated on composite laminates by drop-weight tests. Permanent indentations were measured, and delamination areas of each interface induced by each LVI event were captured using an ultrasonic C-scan. The 3D volume elements with a user-defined, material-based finite element model (FEM) has been applied to predict the LVI event considering damage modes, including intra-ply damage and inter-ply damage. The results of the FEM were found to agree well with experimental observations. Internal damage of the laminate during the impact process was analyzed. For thick laminates, the initiation of damage is observed at the first layer, and then spreads from the impact surface to the back, leading to a pine-type damage pattern as the thickness increases. Frequency-sweep vibration tests of composite laminates subjected to LVI events were studied under a “fixed ends” boundary condition. Our results show that it is reasonable to use frequency-sweep vibration experiments to evaluate the damage of laminates subjected to LVI events.
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Vishwanath, K. S. "Computational Investigation of Square Embedded Delamination of a Composite Laminate using Surface based Cohesive Contact Behavior." International Journal for Research in Applied Science and Engineering Technology 9, no. VI (June 14, 2021): 909–13. http://dx.doi.org/10.22214/ijraset.2021.35114.
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The fiber reinforced polymer laminates have found extensive applications because of its advantages over other materials in terms of thrust to weight ratio, strength to weight ratio, manufacturing benefits such as tailoring, resistance to erosion and corrosion and so on. In the transverse direction, strength, stiffness and stability are comparatively less so that a failure mechanism called interface delamination comes into picture due to poor manufacturing or when tools are dropped that would create an impact load. In this paper, Surface based Cohesive contact behavior is implemented at the interface between base and sub laminate to investigate for 60mm square embedded buckling driven delamination growth. The computational prediction of delamination growth initiation is obtained by solving a HTA/6376C composite laminate specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the inplane loads versus out of plane displacements.
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Xu, Y. G., Z. Shen, W. Tiu, Y. Z. Xu, Yong K. Chen, and G. Haritos. "Delamination Threshold Load of Composite Laminates under Low-Velocity Impact." Key Engineering Materials 525-526 (November 2012): 521–24. http://dx.doi.org/10.4028/www.scientific.net/kem.525-526.521.
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A key factor affecting the use of carbon fibre reinforced composite laminates is the low velocity impact damage which may be introduced accidentally during manufacture, operation or maintenance of the component. Among the several barely visible impact damages, interlaminar delamination is the dominant failure mode and may reduce the post-impact compressive strength of the component significantly. This paper focuses on the study of the delamination threshold load (DTL) above which significant increase of delamination and thus large reduction of the residual compressive strength of the component may occur. Instrumented drop weight tests were carried out under various impact energy levels to determine the delamination threshold load. Efforts are directed to the study of the laminate thickness effect on the reliability of the detection of the DTL. The validity of the concept of DTL has been investigated and possible implications on the measurement of the DTL has been discussed. It is demonstrated that DTL exists but its detection requires proper testing conditions.
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Ariffin, Abdullah Atiq, Wen Xue Wang, and Terutake Matsubara. "Comparative Analysis of Crashworthiness Capability of Laminate Tubes Structure with 0° Plies of Unidirectinally Arrayed Chopped Strand." Key Engineering Materials 744 (July 2017): 305–10. http://dx.doi.org/10.4028/www.scientific.net/kem.744.305.
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This paper presents the crashworthiness performance of carbon reinforced epoxy laminate tubular structure of three different kind tubes made of 0˚ plies Unidirectionally Arrayed Chopped Strand (UACS) introduced into laminate tube. UACS plies with discontinuous angled slit and slit perpendicular to fiber direction, namely bi-angle slits and staggered slits were used as 0˚ ply, respectively, instead of conventional continuous fiber ply to investigate relationship between crashworthiness capacities and progressive collapse behavior under quasi-static crushing tests. Newly designed laminate tube for crashworthy structure made of 0˚ plies UACS bi-angle slits and staggered slit was succesfully enhanced specific energy absorption by about 9.1% and 4.3% respectively compare to conventional continuous fiber laminate tube. The crushed laminate tubes then were sectioned through the impact point and micro-photograph were taken to show the failure behavior, which include effect of distribution slit on delamination, matrix cracking, curvature size, friction, etc. It is shown that UACS laminate beside of showing excellent formability also become newly auto trigger mechanism to achieve much stable and controllable collapse with much extensive fiber fracture occurred.
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Xueling, Fan, Yuan Meini, and Qin Qiang. "Failure Mechanisms of Ti-Al3Ti metal-Intermetallic Laminate Composites Under High-Speed Impact." Rare Metal Materials and Engineering 47, no. 9 (September 2018): 2615–20. http://dx.doi.org/10.1016/s1875-5372(18)30197-8.
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Corderley, G., F. Mostert, and J. J. Krüger. "Failure modes in a carbon / titanium fibre metal laminate under hyper-velocity impact." International Journal of Impact Engineering 125 (March 2019): 180–87. http://dx.doi.org/10.1016/j.ijimpeng.2018.11.011.
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Meo, Michele, Francesco Rizzo, Mark Portus, and Fulvio Pinto. "Bioinspired Helicoidal Composite Structure Featuring Functionally Graded Variable Ply Pitch." Materials 14, no. 18 (September 7, 2021): 5133. http://dx.doi.org/10.3390/ma14185133.
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Composite laminated materials have been largely implemented in advanced applications due to the high tailorability of their mechanical performance and low weight. However, due to their low resistance against out-of-plane loading, they are prone to generate damage as a consequence of an impact event, leading to the loss of mechanical properties and eventually to the catastrophic failure of the entire structure. In order to overcome this issue, the high tailorability can be exploited to replicate complex biological structures that are naturally optimised to withstand extreme impact loading. Bioinspired helicoidal laminates have been already studied in-depth with good results; however, they have been manufactured by applying a constant pitch rotation between each consecutive ply. This is in contrast to that observed in biological structures where the pitch rotation is not constant along the thickness, but gradually increases from the outer shell to the inner core in order to optimise energy absorption and stress distribution. Based on this concept, Functionally Graded Pitch (FGP) laminated composites were designed and manufactured in order to improve the impact resistance relative to a benchmark laminate, exploiting the tough nature of helicoidal structures with variable rotation angles. To the authors’ knowledge, this is one of the first attempts to fully reproduce the helicoidal arrangement found in nature using a mathematically scaled form of the triangular sequence to define the lamination layup. Samples were subject to three-point bending and tested under Low Velocity Impact (LVI) conditions at 15 J and 25 J impact energies and ultrasonic testing was used to evaluate the damaged area. Flexural After Impact (FAI) tests were used to evaluate the post-impact residual energy to confirm the superior impact resistance offered by these bioinspired structures. Vast improvements in impact behaviour were observed in the FGP laminates over the benchmark, with an average reduction of 41% of the damaged area and an increase in post-impact residual energy of 111%. The absorbed energy was similarly reduced (−44%), and greater mechanical strength (+21%) and elastic energy capacity (+78%) were demonstrated in the three-point bending test.
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Vishwanath, K. S. "Computational Investigation of through the Width Delamination of a Composite Laminate using VCCT." International Journal for Research in Applied Science and Engineering Technology 9, no. VI (June 10, 2021): 128–31. http://dx.doi.org/10.22214/ijraset.2021.34890.
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The fiber reinforced polymer laminates have found extensive applications because of its advantages over other materials in terms of strength, stiffness, stability, weight saving features, resistance to corrosion and erosion and many more. But due to poor transverse direction strength, a failure mechanism called delamination will occur in case of poor manufacturing or when tools are dropped which would make an impact. In this paper, VCCT is implemented at the interface between base and sub laminate to investigate for 20mm through the width buckling driven delamination growth. The computational prediction of delamination growth initiation is obtained by solving a T300/976 specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the required energy release rate at the edge of delamination geometry.
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Lisowski, Bartłomiej. "Impact of Fiber Metal Laminates - Literature Research." Mechanics and Mechanical Engineering 22, no. 4 (September 2, 2020): 1355–70. http://dx.doi.org/10.2478/mme-2018-0106.
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AbstractThe paper refers the general idea of composite materials especially Fiber Metal Laminates (FMLs) with respect to low-velocity impact incidents. This phenomenon was characterized by basic parameters and energy dissipation mechanisms. Further considerations are matched with analytical procedures with reference to linearized spring-mass models, impact characteristics divided into energy correlations (global flexure, delamination, tensile fracture and petaling absorbed energies) and set of motion second order differential equations. Experimental tests were based on analytical solutions for different types of FML - GLARE type plates and were held in accordance to ASTM standards. The structure model reveals plenty of dependences related to strain rate effect, deflection represented by the correlations among plate and intender deformation, separate flexure characteristics for aluminium and composite, contact definition based on intender end-radius shape stress analysis supported by FSDT, von Karman strains as well as CLT. Failure criteria were conformed to layers specifications with respect to von Misses stress-strain criterion for aluminium matched with Tsai-Hill or Puck criterion for unidirectional laminate. At the final stage numerical simulation were made in FEM programs such as ABAQUS and ANSYS. Future prospects were based on the experiments held over 3D-fiberglass (3DFG) FMLs with magnesium alloy layers which covers more favorable mechanical properties than FMLs.
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Yokoyama, Takashi, and Kenji Nakai. "Impact Compressive Failure of a Unidirectional Carbon/Epoxy Composite: Effect of Loading Directions." Applied Mechanics and Materials 13-14 (July 2008): 195–201. http://dx.doi.org/10.4028/www.scientific.net/amm.13-14.195.
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The impact compressive failure behaviour of a unidirectional T700/2521 carbon/epoxy composite in three principal material directions is investigated in the conventional split Hopkinson pressure bar. Two different types of specimens with square cross sections are machined from the composite in the plane of the laminate. The uniaxial compressive stress-strain curves up to failure at quasi-static and intermediate strain rates are measured on an Instron testing machine. It is demonstrated that the ultimate compressive strength (or maximum stress) increases slightly, while the ultimate compressive strain (or failure strain) decreases marginally with strain rate in the range of 10-3 to 103/s in all three directions. Dominant failure mechanisms are found to significantly vary with strain rate and loading directions along three principal material axes.
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Cao, Yang, Siyuan Zhao, Limin Sun, Wenbin He, and Jun Ma. "Experimental and simulated research on the ballistic performance of Ti/Al3Ti laminate composites." Advanced Composites Letters 29 (January 1, 2020): 2633366X2092088. http://dx.doi.org/10.1177/2633366x20920884.
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The metal-intermetallic laminate composite Ti/Al3Ti can be used as protective armor in aerospace and military applications, due to its low density, high strength, and superior impact-resistant performance. The ballistic performance of the laminate composite was studied by ballistic testing and finite element technology. The failure modes, such as radical cracks, layer delamination, and plastic deformation, have been found after the ballistic test, and the specific energy absorption was used to evaluate the ballistic capacity of the material. The finite element model of the Ti/Al3Ti impacted by the projectile was established by considering the interface, which was simulated by the solid elements with zero thickness. The simulation results demonstrate the failure process of the interface during penetration. The interfacial failure allowed for layer detachment with its labor layers. The simulation results agree well with that of the experiment, and the practicality and credibility of the model is verified.
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Beaumont, P. W. R. "The failure of fibre composites: An overview." Journal of Strain Analysis for Engineering Design 24, no. 4 (October 1, 1989): 189–205. http://dx.doi.org/10.1243/03093247v244189.
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Static and cyclic loading, impact, and environmental attack all contribute to the accumulation of damage in composite laminates. The damage can take many forms: delamination and splitting during load cycling, matrix cracking during thermal fatigue, and so on. With this diversity of damage mechanisms, it is no wonder that variability in static strength is significantly enhanced by service in the field. We recognise, therefore, that damage is progressive and is accompanied by a gradual deterioration in strength and stiffness of the laminate. In other words, static strength and life-time are part of the same design phenomenon. One way forward is to identify the broad rules governing fibre composite behaviour. There are two directions: continuum modelling and microscopic modelling. Continuum modelling is useful, but generally demands a formidable experimental programme to determine important design parameters. On a much smaller scale, microscopic modelling provides insight into the damaging mechanisms, but alone is too imprecise to be of much practical use to the design engineer. In parallel, however, they can give guidance towards the development of constitutive laws, the path of model-informed empiricism, which leads to predictive design. In other words, extension of basic damage models of composite failure to generic design features can lead to a formulation of design procedures for composite hardware; this is a powerful route to take.
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Kajale, Pranali Yogesh. "Design Optimization of Composite Lay-up Sequence and Orientation to Achieve Minimum Weight for Racing Seat." International Journal of Recent Technology and Engineering (IJRTE) 10, no. 3 (September 30, 2021): 157–63. http://dx.doi.org/10.35940/ijrte.c6453.0910321.
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Composites have proved their usefulness in the automotive industry during recent years. Many automobile companies use them in different parts to reduce weight without hampering strength. In a composite material, Lay-up sequence and orientation highly affects the properties of the laminate. Therefore, it is important to perform design optimization on a component to achieve high strength in minimum weight. This paper deals with the optimization of lay-up for composite Racing Seat using finite element analysis. Different lay-up sequences for laminates including, cross-ply [0/90]n, angle-ply [±α]n, and [0/90/±α]n are analysed. The lay-up sequence, orientation and ply number are optimized using composite material carbon fibre/Epoxy. Driver’s ergonomics and impact sustainability are considered constraints for weight optimization. Driver’s ergonomics were based on 95th percentile male and 5th percentile female rule. Force analysis is performed on the seat according to SFI 39.2 to evaluate the strength requirement. Finite element analysis of composite racing seat is performed via commercial finite element code ANSYS and using the capabilities of ANSYS Composite PrepPost (ACP) to form desired composite lay-up. A finite element code is based on classical lamination theory; including Puck’s failure criterion for first-ply failure. The seat is divided into three portions with a different number of layers considering the values and specific nature of acting forces; which resulted in different thicknesses in different regions. The optimization results show that for all the angles of Angle-ply laminate considered, Angle-ply laminates with an angle of 45⁰ provides a more optimum design. The minimum weight obtained is 10.15 kg.