Journal articles: 'Laminate composite NCF'

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Monticeli, Francisco Maciel, David Daou, Mirko Dinulović, Herman Jacobus Cornelis Voorwald, and Maria Odila Hilário Cioffi. "Mechanical behavior simulation: NCF/epoxy composite processed by RTM." Polymers and Polymer Composites 27, no. 2 (December 9, 2018): 66–75. http://dx.doi.org/10.1177/0967391118817174.

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Considering aeronautics requirements, academies and industries are developing matrixes and reinforcements with higher mechanical performance. The same occurs with the process where new studies focus on obtaining composites with suitable matrix/reinforcement interface. The use of epoxy resin and carbon fiber with high mechanical performance does not guarantee a composite with high mechanical properties, considering imperfections and void formation along the laminate in case of inappropriate processing parameters. The aim of this article was to analyze and quantify the mechanical behavior of polymer composite reinforced with continuous fibers using finite element methodology and postprocessing software simulation. In addition, the classical laminate theory and finite elements were used to simulate flexural and tensile tests of composite specimens. Simulation results were compared with experimental test results using a carbon fiber noncrimp fabric quadriaxial/epoxy resin composite processed by resin transfer molding. Although void volume fraction for structural materials presenting results under aeronautics requirements regarding of 2%, imperfections like lack of resin and impregnation discontinuity showed an influence in tensile and flexural experimental results. Experimental mechanical behavior decreased 10% of strength, in comparison with simulation results due to imperfection on impregnation measured by C-Scan map. Improvement in processing procedures could able to provide greater impregnation continuity, reducing defect formation and ensuring better matrix/reinforcement interface. As a final conclusion, the process plays a role as important as the characteristics of reinforcement and matrix and, consequently, the mechanical properties.

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Mitchell, Cynthia J., James A. Sherwood, Konstantine A. Fetfatsidis, and Lisa M. Dangora. "Characterization of Cured Composite Materials for Wind Turbine Blades." Key Engineering Materials 554-557 (June 2013): 478–83. http://dx.doi.org/10.4028/www.scientific.net/kem.554-557.478.

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NCFs (Non-Crimp Fabrics) infused with epoxy resin are popular in the design of wind turbine blades and other complex systems due to their ability to conform to complex shapes. Past work in the development of a combination beam-shell modeling approach to simulate the forming of NCF composites has been demonstrated to capture the change in the orientations of the yarns during a forming process. The structural performance of these manufactured blades is often analyzed using finite element simulations that consider the material properties of the fibers and of the resin based on the rule of mixtures and orthotropic shells where the model is sectioned into zones that account for changes in the material properties due to variations in the orientations of the lamina and number of layers. With the availability of the beam-shell model, the use of zones can be removed if the individual contributions of the yarns (beam elements) and resin (shell elements) can be characterized and the orientations of the yarns resulting from a forming simulation can be used to account for the variations in the material properties of the composite throughout the blade. This research uses a combination of static flexure tests and impact modal tests to ascertain the material properties of the fibers and resin in a unidirectional and biaxial non-crimp fabric laminate plates. The material properties are used in a finite element model of the plate and the model is analyzed in flexure and in a free-free modal configuration to compare to experimental results. Two different approaches are used in the commercially available software Abaqus to model the plate. One approach uses a combination of beam and shell elements to represent the fibers and the resin, respectively. The other approach uses orthotropic shell elements to capture the unbalanced behavior of the fiber/resin composite. The beam/shell modeling approach better represents the overall behavior of a single-layer plate and can be extended to consider multiple plies.

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Papila, Melih. "Design of and with thin-ply non-crimp fabric as building blocks for composites." Science and Engineering of Composite Materials 25, no. 3 (April 25, 2018): 501–16. http://dx.doi.org/10.1515/secm-2015-0386.

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Abstract New generation non-crimp fabric (NCF) offers an attractive thin and lightweight building block alternative in the design of composite materials and structures. Pre-assembly of multiple plies of parallel fibers, each laying in a different orientation would not require crimping of the fibers and would enable one-axis lay-up that can substantially reduce the labor, scrap, and manufacturing costs. A state-of-the-art tow-spreading technique enables ply thickness to be reduced to as low as one-third of the typical commercial high quality pre-preg ply thickness. The thin-ply NCF stacks result in well-dispersed plies of different fiber orientations and creates the so-called homogenized laminates without ply clustering. As an option, bi-angle thin-ply NCF offers two different fiber orientations with one being off-axis, e.g. at ϕ°, along with an on-axis 0° forming (0/ϕ) assembly. This allows to design in anisotropic properties within the NCF building block. An overview of several aspects of the thin-ply bi-angle NCF composites is provided to address associated benefits and opportunities in the lightweight structural composites design process.

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Mohsin, Muhammad Ameerul Atrash, Lorenzo Iannucci, and Emile S. Greenhalgh. "Delamination of Novel Carbon Fibre-Based Non-Crimp Fabric-Reinforced Thermoplastic Composites in Mode I: Experimental and Fractographic Analysis." Polymers 15, no. 7 (March 23, 2023): 1611. http://dx.doi.org/10.3390/polym15071611.

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Delamination, a form of composite failure, is a significant concern in laminated composites. The increasing use of out-of-autoclave manufacturing techniques for automotive applications, such as compression moulding and thermoforming, has led to increased interest in understanding the delamination resistance of carbon-fibre-reinforced thermoplastic (CFRTP) composites compared to traditional carbon-fibre-reinforced thermosetting (CFRTS) composites. This study evaluated the mode I (opening) interlaminar fracture toughness of two non-crimp fabric (NCF) biaxial (0/90°) carbon/thermoplastic composite systems: T700/polyamide 6.6 and T700/polyphenylene sulphide. The mode I delamination resistance was determined using the double cantilever beam (DCB) specimen. The results were analysed and the Mode I interlaminar fracture toughness was compared. Additionally, the fractographic analysis (microstructure characterisation) was conducted using a scanning electron microscope (SEM) to examine the failure surface of the specimens.

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Mohsin, Muhammad Ameerul Atrash, Lorenzo Iannucci, and Emile S. Greenhalgh. "Experimental and Numerical Analysis of Low-Velocity Impact of Carbon Fibre-Based Non-Crimp Fabric Reinforced Thermoplastic Composites." Polymers 13, no. 21 (October 22, 2021): 3642. http://dx.doi.org/10.3390/polym13213642.

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There has been a lot of interest in understanding the low-velocity impact (LVI) response of thermoplastic composites. However, little research has focussed on studying the impact behaviour of non-crimp fabric (NCF)-based fibre reinforced thermoplastic composites. The purpose of this study was to evaluate the LVI responses of two types of non-crimp fabric (NCF) carbon fibre reinforced thermoplastic laminated composites that have been considered attractive in the automotive and aerospace industry: (i) T700/polyamide 6.6 (PA6.6) and (ii) T700/polyphenylene sulphide (PPS). Each carbon/thermoplastic type was impacted at three different energy levels (40, 100 and 160 J), which were determined to achieve three degrees of penetrability, i.e., no penetration, partial penetration and full penetration, respectively. Two distinct non-destructive evaluation (NDE) techniques ((i) ultrasonic C-scanning and (ii) X-ray tomography) were used to assess the extent of damage after impact. The laminated composite plates were subjected to an out-of-plane, localised impact using an INSTRON® drop-weight tower with a hemispherical impactor measuring 16 mm in diameter. The time histories of force, deflection and velocity are reported and discussed. A nonlinear finite element model of the LVI phenomenon was developed using a finite element (FE) solver LS-DYNA® and validated against the experimental observations. The extent of damage observed and level of impact energy absorption calculated on both the experiment and FE analysis are compared and discussed.

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Kunze, Eckart, Siegfried Galkin, Robert Böhm, Maik Gude, and Luise Kärger. "The Impact of Draping Effects on the Stiffness and Failure Behavior of Unidirectional Non-Crimp Fabric Fiber Reinforced Composites." Materials 13, no. 13 (July 2, 2020): 2959. http://dx.doi.org/10.3390/ma13132959.

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Unidirectional non-crimp fabrics (UD-NCF) are often used to exploit the lightweight potential of continuous fiber reinforced plastics (CoFRP). During the draping process, the UD-NCF fabric can undergo large deformations that alter the local fiber orientation, the local fiber volume content (FVC) and create local fiber waviness. Especially the FVC is affected and has a large impact on the mechanical properties. This impact, resulting from different deformation modes during draping, is in general not considered in composite design processes. To analyze the impact of different draping effects on the mechanical properties and the failure behavior of UD-NCF composites, experimental results of reference laminates are compared to the results of laminates with specifically induced draping effects, such as non-constant FVC and fiber waviness. Furthermore, an analytical model to predict the failure strengths of UD laminates with in-plane waviness is introduced. The resulting stiffness and strength values for different FVC or amplitude to wavelength configurations are presented and discussed. In addition, failure envelopes based on the PUCK failure criterion for each draping effect are derived, which show a clear specific impact on the mechanical properties. The findings suggest that each draping effect leads to a “new fabric” type. Additionally, analytical models are introduced and the experimental results are compared to the predictions. Results indicate that the models provide reliable predictions for each draping effect. Recommendations regarding necessary tests to consider each draping effect are presented. As a further prospect the resulting stiffness and strength values for each draping effect can be used for a more accurate prediction of the structural performance of CoFRP parts.

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İnal, Oğuzcan, Fatih Balıkoğlu, and Akın Ataş. "Bolted joints in quasi-unidirectional glass-fibre NCF composite laminates." Composite Structures 183 (January 2018): 536–44. http://dx.doi.org/10.1016/j.compstruct.2017.05.075.

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Govindasamy, Mahendran, Gopalakrishnan Kamalakannan, Chandrasekaran Kesavan, and Ganesh Kumar Meenashisundaram. "Damage Detection in Glass/Epoxy Laminated Composite Plates Using Modal Curvature for Structural Health Monitoring Applications." Journal of Composites Science 4, no. 4 (December 14, 2020): 185. http://dx.doi.org/10.3390/jcs4040185.

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This paper deals with detection of macro-level crack type damage in rectangular E-Glass fiber/Epoxy resin (LY556) laminated composite plates using modal analysis. Composite plate-like structures are widely found in aerospace and automotive structural applications which are susceptible to damages. The formation of cracks in a structure that undergoes vibration may lead to catastrophic events such as structural failure, thus detection of such occurrences is considered necessary. In this research, a novel technique called as node-releasing technique in Finite Element Analysis (FEA), which was not attempted by the earlier researchers, is used to model the perpendicular cracks (the type of damage mostly considered in all the pioneering research works) and also slant cracks (a new type of damage considered in the present work) of various depths and lengths for Unidirectional Laminate (UDL) ([0]S and [45]S) composite layered configurations using commercial FE code Ansys, thus simulating the actual damage scenario. Another novelty of the present work is that the crack is modeled with partial depth along the thickness of the plate, instead of the through the thickness crack which has been of major focus in the literature so far, in order to include the possibility of existence of the crack up to certain layers in the laminated composite structures. The experimental modal analysis is carried out to validate the numerical model. Using central difference approximation method, the modal curvature is determined from the displacement mode shapes which are obtained via finite element analysis. The damage indicators investigated in this paper are Normalized Curvature Damage Factor (NCDF) and modal strain energy-based methods such as Strain Energy Difference (SED) and Damage Index (DI). It is concluded that, all the three damage detection algorithms detect the transverse crack clearly. In addition, the damage indicator NCDF seems to be more effective than the other two, particularly when the detection is for damage inclined to the longitudinal axis of the plate. The proposed method will provide the base data for implementing online structural health monitoring of structures using technologies such as Machine Learning, Artificial Intelligence, etc.

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Byeon, Ki-Seok, Yu-Jeong Shin, Han-Kyu Jeung, Si-Woo Park, Chun-Su Roh, Jin-Soo Je, and Ki-Chul Kwon. "Tensile Property Analysis of NCF Composite Laminated Structure for HP-CRTM Forming Process." Korean Society of Manufacturing Process Engineers 18, no. 1 (January 31, 2019): 59–64. http://dx.doi.org/10.14775/ksmpe.2019.18.1.059.

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Grauers, L., R. Olsson, and R. Gutkin. "Energy absorption and damage mechanisms in progressive crushing of corrugated NCF laminates: Fractographic analysis." Composite Structures 110 (April 2014): 110–17. http://dx.doi.org/10.1016/j.compstruct.2013.11.001.

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Pinto, Thiago Henrique Lara, Waseem Gul, Libardo Andrés González Torres, Carlos Alberto Cimini, and Sung Kyu Ha. "Experimental and Numerical Comparison of Impact Behavior between Thermoplastic and Thermoset Composite for Wind Turbine Blades." Materials 14, no. 21 (October 25, 2021): 6377. http://dx.doi.org/10.3390/ma14216377.

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Damage generated due to low velocity impact in composite plates was evaluated focusing on the design and structural integrity of wind turbine blades. Impact properties of composite plates manufactured with thermoplastic and thermoset resins for different energy levels were measured and compared. Specimens were fabricated using VARTM (vacuum assisted resin transfer molding), using both matrix systems in conjunction with carbon, glass and carbon/glass hybrid fibers in the NCF (non-crimp fabric) architecture. Resin systems used were ELIUM 188O (thermoplastic) from Arkema Co., Ltd. and a standard epoxy reference, EPR-L20 from Hexion Co., Ltd. (thermoset). Auxiliary numerical finite element analyses were performed to better understand the tests physics. These models were then compared with the experimental results to verify their predictive capacity, given the intrinsic limitations due to their simplicity. Based in the presented results, it is possible to observe that ELIUM is capable to replace a conventional thermoset matrix. The thermoplastic panels presented similar results compared to its thermoset counterparts, with even a trend of less impact damage. Additionally, for both thermoplastic and thermoset resin systems, glass layups showed the lowest levels of damage while carbon panels presented the highest damage levels. Hybrid laminates can be applied as a compromise solution.

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Heß, H., and N. Himmel. "Structurally stitched NCF CFRP laminates. Part 2: Finite element unit cell based prediction of in-plane strength." Composites Science and Technology 71, no. 5 (March 2011): 569–85. http://dx.doi.org/10.1016/j.compscitech.2010.11.011.

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Uhlig, K., A. Spickenheuer, K. Gliesche, and I. Karb. "Strength of CFRP open hole laminates made from NCF, TFP and braided preforms under cyclic tensile loading." Plastics, Rubber and Composites 39, no. 6 (July 2010): 247–55. http://dx.doi.org/10.1179/174328910x12647080902772.

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Zhang, Yuxuan, Shi Yan, Lili Jiang, Tiancong Fan, Junjun Zhai, and Hanhua Li. "Couple effects of multi-impact damage and CAI capability on NCF composites." REVIEWS ON ADVANCED MATERIALS SCIENCE 63, no. 1 (January 1, 2024). http://dx.doi.org/10.1515/rams-2024-0003.

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Abstract In this study, the mechanical properties of non-crimp fabric (NCF) composite laminates under low-velocity impact and compression after impact (CAI) tests were studied by Scanning electron microscopy (SEM) and Digital image correlation (DIC) techniques. The impact response under different impact times, impact angles, and impact distance is studied. Similarly, in CAI test, DIC technique is used to reveal the whole process of NCF composite compression failure, and SEM is used to reveal the microscopic failure form. The experimental results show that the impact damage process of NCF composites has strong directivity. The concrete manifestation is that the internal failure will extend along the paving direction at the failure layer. The peak load generated under 20 J impact energy is about 1/2 of that under 40 J impact energy. The impact distance is one of the important factors affecting the coupling effect of multiple impacts, and the impact angle has little effect on the internal damage extension. The proportion of internal damage area also supports the relevant view, that is, the average difference in the proportion of internal damage area under different impact distance is about 5%, while the average difference in the proportion of internal damage area under different impact angles is about 3%. During the compression process, the main failure mode is shear failure and the failure mode is brittle fracture. The oblique fracture occurs only when the oblique is 45° and the impact distance is large (50 mm). The impact angle has little effect on the residual compression performance of NCF.

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Tang, Juan, Zhiping Zhou, Yuan Tan, Hao Chen, Shiyou Wang, and Asier Gutiérrez. "Research on NCF fabric CFRP pultrusion beam mechanical performance and laminate design for railway vehicle application." Journal of Composite Materials, April 27, 2022, 002199832210946. http://dx.doi.org/10.1177/00219983221094657.

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This paper presents the conducted research on an innovative pultrusion beam made of NCF carbon fabric for an enhanced flexural behavior. This includes laminate design and optimization. By changing the ply thickness of each 0°-, ±45°- and 90°- orientations (while fixing the others), their influence on the strength and stiffness of the pultrusion beam was studied by the finite element method. 7 different combinations of layups were designed to analyze mechanical performance. The simulation results show the layup of 4/5/1 ply ratio is the best one for strength and stiffness; therefore, the carbon fabric pultrusion beam samples were manufactured according to this layup. Bending experimental testing was conducted for both CFRP pultrusion beam and aluminum beam under the design case of equal thickness to compare their strength and stiffness. The testing results show the strength of fabric pultrusion beam is 82.5% of that of aluminum beam, weight is 60% of the aluminum one, and the stiffness is 75% of it. From the results obtained from FEA and physical testing, it is shown the pultrusion beam with complex multi-cavities shapes possess high mechanical performance. This research concludes the CFRP NCF pultrusion beam entails great advantages for railway structure parts and other industries.

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Schreiter, Michael, Daniel Nebel, Enrico Körner, Arham Saleem, and Manuel Schlegel. "Application of load-adapted hybrid textiles for a thermoplastic seat pass-through." Technologies for Lightweight Structures (TLS) 3, no. 1 (April 20, 2021). http://dx.doi.org/10.21935/tls.v3i1.134.

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The potential of a continuous non-crimp fabric (NCF) process with implemented offset technologies is demonstrated by a case study of a seat pass-through. Topology optimization with the relevant load cases and the construction of a load-adapted composite design with a weight saving of up to 18 percent is presented. Inverse draping identifies a two-dimensional development of the construction and prepares it for production based on the restrictions of textile technology. The downstream process capability of textiles produced in this way was investigated by impregnating heavy tows with polypropylene on laboratory scale and subsequent material characterization of the resulting laminates. The impregnation and consolidation of the seat pass-through is performed with load path adapted semi-finished products using novel variothermal, fluid-based pressing. This allows better control over the dynamic impregnation and unwanted fiber washing due to the large gradient of the areal weight. The final processing in injection molding tool of the reference component shows the applicability of the technology also in existing process chains and illustrates the potential of the consistent consideration of a load-adapted composite design in the development process.

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Journal articles on the topic 'Laminate composite NCF'

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