In recent years, natural fibers have begun to replace synthetic fibers in automotive, building, and marine applications because of their sustainability, renewability, low cost, and availability of raw materials. However, because of their low strength, biocomposites are strengthened by hybridization with stronger synthetic fibers or adding fillers. This study reinforced high‐cellulose jute fiber composites with cellulose‐based almond (Prunus amygdalus) shell filler (ASF). Natural waste almond shells were ground to microparticle size. Hybrid composites were prepared by adding microparticulate ASF to the jute fiber composites at 0%, 1.5%, 3%, 4.5%, and 6% by weight. A comprehensive experimental study included tensile, flexural, Charpy impact (flat and edgewise), and shear tests. The addition of ASF significantly improved the mechanical properties of the jute fiber composites, and the best values were obtained with 3 wt.% ASF addition. Tensile, flexural, impact, and shear properties increased by 48.2%, 63.5%, 24.4%, and 52.2%, respectively. Scanning Electron microscopy (SEM) micrographs used in morphological structural analysis prove that the high mechanical values are achieved by ASF strengthening the interlaminar adhesion. This study contributed to developing a hybrid natural composite material reinforced with natural fillers that is stronger, environmentally friendly, and sustainable.HighlightsThe organic structure of Almond Shell Filler (ASF) ensured the sustainability of natural composites.Cellulosic ASF significantly contributed to the structural stiffness and strength of jute fiber composites.ASF reduced voids, improved fiber‐matrix bonding, and prevented debonding and delamination.ASF optimized the mechanical performance of jute fiber composites at 3%.
{"title":"Utilizing almond shell filler to improve strength and sustainability of jute fiber composites","authors":"Ahmet Çetin","doi":"10.1002/pc.28999","DOIUrl":"https://doi.org/10.1002/pc.28999","url":null,"abstract":"<jats:label/>In recent years, natural fibers have begun to replace synthetic fibers in automotive, building, and marine applications because of their sustainability, renewability, low cost, and availability of raw materials. However, because of their low strength, biocomposites are strengthened by hybridization with stronger synthetic fibers or adding fillers. This study reinforced high‐cellulose jute fiber composites with cellulose‐based almond (<jats:italic>Prunus amygdalus</jats:italic>) shell filler (ASF). Natural waste almond shells were ground to microparticle size. Hybrid composites were prepared by adding microparticulate ASF to the jute fiber composites at 0%, 1.5%, 3%, 4.5%, and 6% by weight. A comprehensive experimental study included tensile, flexural, Charpy impact (flat and edgewise), and shear tests. The addition of ASF significantly improved the mechanical properties of the jute fiber composites, and the best values were obtained with 3 wt.% ASF addition. Tensile, flexural, impact, and shear properties increased by 48.2%, 63.5%, 24.4%, and 52.2%, respectively. Scanning Electron microscopy (SEM) micrographs used in morphological structural analysis prove that the high mechanical values are achieved by ASF strengthening the interlaminar adhesion. This study contributed to developing a hybrid natural composite material reinforced with natural fillers that is stronger, environmentally friendly, and sustainable.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>The organic structure of Almond Shell Filler (ASF) ensured the sustainability of natural composites.</jats:list-item> <jats:list-item>Cellulosic ASF significantly contributed to the structural stiffness and strength of jute fiber composites.</jats:list-item> <jats:list-item>ASF reduced voids, improved fiber‐matrix bonding, and prevented debonding and delamination.</jats:list-item> <jats:list-item>ASF optimized the mechanical performance of jute fiber composites at 3%.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"15 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214649","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Ju Lu‐yan, Li Xing‐kai, Zhang Xue‐ni, Zhang Zhao‐yuan, Zhang Yao‐wu, Ai Kang
Thermal expansion of materials is a critical factor influencing their dimensional stability. This study explores the regulation of thermal expansion in composite materials through the incorporation of carbon fibers and zirconium tungstate particles. The influence of fiber length on the thermal expansion behavior of these composites was investigated. The investigation reveal that the variation in the relative elongation ratio (dl/L0) of the carbon fiber‐reinforced zirconium tungstate composites is nonlinear, characterized by an initial increase, subsequent decrease, and a final resurgence. Notably, an increase in fiber length results in a mitigated rate of increase in the (dl/L0) ratio. Furthermore, composites fabricated with shorter fibers exhibit a higher coefficient of thermal expansion (CTE). Upon elevating the temperature to 250°C, the CTE for composites reinforced with 100 and 500 mesh carbon fibers escalate to 24.5 × 10−6/K and 74.6 × 10−6/K, respectively. These values represent an 8% and 116% enhancement relative to those measured at 50°C.HighlightsThe thermal expansion properties are improved by adding carbon fiber and ZrW2O8 nanoparticles.Utilizing fiber lengths ranging from 100 to 500 mesh effectively diminishes the CTE.The Cf‐ZrW2O8/9621 composite exhibits non‐linear behavior in its dl/L0 ratio.Within the range, longer fibers are more beneficial for reducing the CTE.
{"title":"The effect of carbon fiber length on the thermal expansion of fiber‐reinforced particulate hybrid composites","authors":"Ju Lu‐yan, Li Xing‐kai, Zhang Xue‐ni, Zhang Zhao‐yuan, Zhang Yao‐wu, Ai Kang","doi":"10.1002/pc.29024","DOIUrl":"https://doi.org/10.1002/pc.29024","url":null,"abstract":"<jats:label/>Thermal expansion of materials is a critical factor influencing their dimensional stability. This study explores the regulation of thermal expansion in composite materials through the incorporation of carbon fibers and zirconium tungstate particles. The influence of fiber length on the thermal expansion behavior of these composites was investigated. The investigation reveal that the variation in the relative elongation ratio (dl/L0) of the carbon fiber‐reinforced zirconium tungstate composites is nonlinear, characterized by an initial increase, subsequent decrease, and a final resurgence. Notably, an increase in fiber length results in a mitigated rate of increase in the (dl/L0) ratio. Furthermore, composites fabricated with shorter fibers exhibit a higher coefficient of thermal expansion (CTE). Upon elevating the temperature to 250°C, the CTE for composites reinforced with 100 and 500 mesh carbon fibers escalate to 24.5 × 10<jats:sup>−6</jats:sup>/K and 74.6 × 10<jats:sup>−6</jats:sup>/K, respectively. These values represent an 8% and 116% enhancement relative to those measured at 50°C.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>The thermal expansion properties are improved by adding carbon fiber and ZrW<jats:sub>2</jats:sub>O<jats:sub>8</jats:sub> nanoparticles.</jats:list-item> <jats:list-item>Utilizing fiber lengths ranging from 100 to 500 mesh effectively diminishes the CTE.</jats:list-item> <jats:list-item>The C<jats:sub>f</jats:sub>‐ZrW<jats:sub>2</jats:sub>O<jats:sub>8</jats:sub>/9621 composite exhibits non‐linear behavior in its dl/L0 ratio.</jats:list-item> <jats:list-item>Within the range, longer fibers are more beneficial for reducing the CTE.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"2 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214652","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The elastic fiber prestressing (EFP) technique has been developed to balance the thermal residual stress generated during curing of a polymeric composite, where continuous fibers were prestretched under either constant stress or constant strain throughout the curing process. The tension was only removed after the resin was fully cured. It has been demonstrated that EFP is able to enhance the shear properties of the composite, while the underlying mechanics is still unknown. Here, we investigated the multiscale shear failure mechanisms induced by the EFP within a carbon composite. A bespoke biaxial fiber prestressing rig was developed to apply biaxial tension to a plain‐weave carbon prepreg, where the constant strain‐based EFP method was employed to produce prestrained composites with different prestrain levels. Effects of EFP on macro‐scale shear failure were subsequently characterized through mechanical tests and micro‐morphological analysis. Both the micro‐ and meso‐scale representative volume element (RVE) finite element models were established and experimentally verified. These were then employed to reveal the underlying stress evolution mechanics induced by EFP. It is found that EFP would improve the shear performance of a composite by enhancing the fiber/matrix interfacial bonding strength. This attributes to the elastic strain recoveries of the prestrained fibers locked within a polymeric composite, which generate compressive stresses to counterbalance the external loading. The multiscale shear failure mechanisms were then proposed. These findings are expected to facilitate structural design and application of the EFP for aerospace composites.HighlightsBiaxial tension is applied to produce prestrained woven composite.Prestrain effects on microstructural stress evolution mechanics are revealed.Multiscale shear failure mechanisms are proposed for prestrained composites.
{"title":"Multiscale shear failure mechanisms within a prestrained composite","authors":"Chenmin Zhao, Bing Wang, Chenglong Guan, Shihan Jiang, Jianfeng Zhong, Shuncong Zhong","doi":"10.1002/pc.29049","DOIUrl":"https://doi.org/10.1002/pc.29049","url":null,"abstract":"<jats:label/>The elastic fiber prestressing (EFP) technique has been developed to balance the thermal residual stress generated during curing of a polymeric composite, where continuous fibers were prestretched under either constant stress or constant strain throughout the curing process. The tension was only removed after the resin was fully cured. It has been demonstrated that EFP is able to enhance the shear properties of the composite, while the underlying mechanics is still unknown. Here, we investigated the multiscale shear failure mechanisms induced by the EFP within a carbon composite. A bespoke biaxial fiber prestressing rig was developed to apply biaxial tension to a plain‐weave carbon prepreg, where the constant strain‐based EFP method was employed to produce prestrained composites with different prestrain levels. Effects of EFP on macro‐scale shear failure were subsequently characterized through mechanical tests and micro‐morphological analysis. Both the micro‐ and meso‐scale representative volume element (RVE) finite element models were established and experimentally verified. These were then employed to reveal the underlying stress evolution mechanics induced by EFP. It is found that EFP would improve the shear performance of a composite by enhancing the fiber/matrix interfacial bonding strength. This attributes to the elastic strain recoveries of the prestrained fibers locked within a polymeric composite, which generate compressive stresses to counterbalance the external loading. The multiscale shear failure mechanisms were then proposed. These findings are expected to facilitate structural design and application of the EFP for aerospace composites.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>Biaxial tension is applied to produce prestrained woven composite.</jats:list-item> <jats:list-item>Prestrain effects on microstructural stress evolution mechanics are revealed.</jats:list-item> <jats:list-item>Multiscale shear failure mechanisms are proposed for prestrained composites.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"274 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214647","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
V. Sánchez‐Alarcos, D. L. R. Khanna, P. La Roca, V. Recarte, F. D. Lambri, F. G. Bonifacich, O. A. Lambri, I. Royo‐Silvestre, A. Urbina, J. I. Pérez‐Landazábal
A high filling load (62% weight) printable magnetic composite has been elaborated from the dispersion of magnetocaloric Ni45Mn36.7In13.3Co5 metamagnetic shape memory alloy microparticles into a PCL polymer matrix. The composite material has been prepared by solution method, resulting in a very homogeneous particles dispersion into the matrix. The structural transitions in the polymer are not affected by the addition of the metallic microparticles, which in turn results in a significant increase of the mechanical consistency. The good ductility of the elaborated composite allows its extrusion in flexible printable filaments, from which 3D pieces with complex geometries have been grown. The heat transfer of the composite material has been assessed from finite element simulation. In spite of the achievable magnetocaloric values are moderated with respect to the bulk, numerical simulations confirm that, in terms of heat transference, a PCL/Ni‐Mn‐In‐Co wire is more efficient than a bulk Ni‐Mn‐In‐Co cubic piece containing the same amount of magnetic active material. The quite good magnetocaloric response of the composite and the possibility to print high surface/volume ratio geometries make this material a promising candidate for the development of heat exchangers for clean and efficient magnetic refrigeration applications.Highlights3D printable magnetic composites developed from dispersion of MSMA in PCL.High filling factor and uniform dispersion characterized by SEM.Inclusion of microparticles does not affect polymeric structural transitions.Metallic fillers improve DMA response of 3D printed pieces.FEM simulations endorse PCL/MSMA composites for magnetic refrigeration.
将具有磁性的 Ni45Mn36.7In13.3Co5 元磁性形状记忆合金微粒分散到 PCL 聚合物基体中，制成了一种高填充负荷（62% 重量）的可打印磁性复合材料。这种复合材料是通过溶液法制备的，因此微粒在基体中的分散非常均匀。聚合物的结构转变不受金属微粒添加的影响，这反过来又显著提高了机械稠度。精心制作的复合材料具有良好的延展性，因此可以将其挤压成柔性可打印长丝，并从中生长出具有复杂几何形状的三维部件。复合材料的热传导已通过有限元模拟进行了评估。尽管与块状材料相比，所能达到的磁ocaloric 值有所降低，但数值模拟证实，就热传递而言，PCL/Ni-Mn-In-Co 金属丝比含有相同数量磁性活性材料的块状 Ni-Mn-In-Co 立方体材料更有效。这种复合材料具有相当好的磁致冷响应，而且可以打印出高表面/体积比的几何形状，因此有望开发出用于清洁高效磁制冷应用的热交换器。高填充系数和均匀分散是 SEM 的特点。微粒子的加入不会影响聚合物结构的转变。金属填料改善了 3D 打印件的 DMA 响应。有限元模拟支持 PCL/MSMA 复合材料用于磁制冷。
{"title":"Polycaprolactone/MSMA composites for magnetic refrigeration applications","authors":"V. Sánchez‐Alarcos, D. L. R. Khanna, P. La Roca, V. Recarte, F. D. Lambri, F. G. Bonifacich, O. A. Lambri, I. Royo‐Silvestre, A. Urbina, J. I. Pérez‐Landazábal","doi":"10.1002/pc.28997","DOIUrl":"https://doi.org/10.1002/pc.28997","url":null,"abstract":"<jats:label/>A high filling load (62% weight) printable magnetic composite has been elaborated from the dispersion of magnetocaloric Ni<jats:sub>45</jats:sub>Mn<jats:sub>36.7</jats:sub>In<jats:sub>13.3</jats:sub>Co<jats:sub>5</jats:sub> metamagnetic shape memory alloy microparticles into a PCL polymer matrix. The composite material has been prepared by solution method, resulting in a very homogeneous particles dispersion into the matrix. The structural transitions in the polymer are not affected by the addition of the metallic microparticles, which in turn results in a significant increase of the mechanical consistency. The good ductility of the elaborated composite allows its extrusion in flexible printable filaments, from which 3D pieces with complex geometries have been grown. The heat transfer of the composite material has been assessed from finite element simulation. In spite of the achievable magnetocaloric values are moderated with respect to the bulk, numerical simulations confirm that, in terms of heat transference, a PCL/Ni‐Mn‐In‐Co wire is more efficient than a bulk Ni‐Mn‐In‐Co cubic piece containing the same amount of magnetic active material. The quite good magnetocaloric response of the composite and the possibility to print high surface/volume ratio geometries make this material a promising candidate for the development of heat exchangers for clean and efficient magnetic refrigeration applications.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>3D printable magnetic composites developed from dispersion of MSMA in PCL.</jats:list-item> <jats:list-item>High filling factor and uniform dispersion characterized by SEM.</jats:list-item> <jats:list-item>Inclusion of microparticles does not affect polymeric structural transitions.</jats:list-item> <jats:list-item>Metallic fillers improve DMA response of 3D printed pieces.</jats:list-item> <jats:list-item>FEM simulations endorse PCL/MSMA composites for magnetic refrigeration.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"5 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214650","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Di Lei, Jie Wang, Yakun Qiao, Shuyan Nie, Zhen Wei, Liangfei Gong, Jianmin Wang, Zhanfang Liu
Glass fiber reinforced plastics (GFRPs) is a key material for the outer protecting layer of ships as well as for energy storage tanks. Its ballistic and blast resistance is closely related to the inclusion structure of its glass fiber and polyester matrix, however, the related detailed studies have not been reported. In this paper, ballistic shooting tests and finite element simulations are both employed to investigate the ballistic limit velocities (V50) of GFRPs and reveal the effects of glass fiber layers and the polyester matrix thickness on the V50. The results show that the V50 of GFRPs is essentially linearly related to the thickness of the target plate for a given number of glass fiber layers. An increase in the number of glass fiber layers enhances the overall V50 value of GFRPs, but the linear relationship with the thickness remains unchanged. The target plate with more layers of glass fiber interacts with the projectile for a longer time, resulting in the debonding of the fiber and the resin matrix. The resin around the crater loses its support and then produces irregular cracks. Based on energy conservation, a theoretical model for predicting the V50 of GFRPs with considering the effects of glass fiber and polyester matrix is proposed. After comparing the results of theoretical calculations with experimental and simulation data, the relationship equations between the key parameters (ballistic strength) in the model and the number of fiber layers and target plate thickness are finally given. These findings can provide support for the design of ballistic GFRPs.HighlightsBallistic velocity limit (V50) of glass fiber reinforced plastics (GFRPs) obtained by experiment and finite element simulationTuning the V50 of GFRPs by designing the number of glass fiber and polyester thickness.Proposed a theoretical model for predicting the V50 of GFRPs.
{"title":"Effect of glass fiber and polyester thickness on the ballistic velocity limit of glass fiber reinforced plastics","authors":"Di Lei, Jie Wang, Yakun Qiao, Shuyan Nie, Zhen Wei, Liangfei Gong, Jianmin Wang, Zhanfang Liu","doi":"10.1002/pc.29018","DOIUrl":"https://doi.org/10.1002/pc.29018","url":null,"abstract":"<jats:label/>Glass fiber reinforced plastics (GFRPs) is a key material for the outer protecting layer of ships as well as for energy storage tanks. Its ballistic and blast resistance is closely related to the inclusion structure of its glass fiber and polyester matrix, however, the related detailed studies have not been reported. In this paper, ballistic shooting tests and finite element simulations are both employed to investigate the ballistic limit velocities (V50) of GFRPs and reveal the effects of glass fiber layers and the polyester matrix thickness on the V50. The results show that the V50 of GFRPs is essentially linearly related to the thickness of the target plate for a given number of glass fiber layers. An increase in the number of glass fiber layers enhances the overall V50 value of GFRPs, but the linear relationship with the thickness remains unchanged. The target plate with more layers of glass fiber interacts with the projectile for a longer time, resulting in the debonding of the fiber and the resin matrix. The resin around the crater loses its support and then produces irregular cracks. Based on energy conservation, a theoretical model for predicting the V50 of GFRPs with considering the effects of glass fiber and polyester matrix is proposed. After comparing the results of theoretical calculations with experimental and simulation data, the relationship equations between the key parameters (ballistic strength) in the model and the number of fiber layers and target plate thickness are finally given. These findings can provide support for the design of ballistic GFRPs.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>Ballistic velocity limit (V50) of glass fiber reinforced plastics (GFRPs) obtained by experiment and finite element simulation</jats:list-item> <jats:list-item>Tuning the V50 of GFRPs by designing the number of glass fiber and polyester thickness.</jats:list-item> <jats:list-item>Proposed a theoretical model for predicting the V50 of GFRPs.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"97 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214648","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This work aims to study the effects of bionic spiral stacking sequence, impact energy and impactor shape on the impact resistance of laminates. The finite element model is established based on the stress failure criterion, progressive damage evolution, and the triangle traction‐separation law. The reliability of the finite element model is validated through rigorous comparison with experimental data. The study investigates the influence of laminate layup sequence, impact energy, and impactor shape on the impact resistance of laminates. The results show that during low‐speed impacts, laminate damage is primarily characterized by fiber breakage, matrix cracking, and delamination. Matrix cracking and delamination become more pronounced as the impact energy increases. The design of linear spiral ply and power function spiral ply has a positive effect on the impact resistance of laminates. The impact resistance of laminates is sensitive to the sharpness of the impactor and the level of impact energy. Higher impact energy and sharper impactor shapes lead to increased energy absorption in the laminate, resulting in more pronounced damage failure.HighlightsThe impact resistance of bionic spiral composite laminates is studied.Three biologically inspired stacking sequences were designed.A numerical simulation method is proposed and verified.The low‐velocity impact characteristics of bionic laminates are revealed.
{"title":"Low‐velocity impact behavior of composite laminates based on bio‐inspired stacking sequence","authors":"Tian Zhou, Hongyuan Yang, Chaoyi Peng, Yiru Ren","doi":"10.1002/pc.29013","DOIUrl":"https://doi.org/10.1002/pc.29013","url":null,"abstract":"<jats:label/>This work aims to study the effects of bionic spiral stacking sequence, impact energy and impactor shape on the impact resistance of laminates. The finite element model is established based on the stress failure criterion, progressive damage evolution, and the triangle traction‐separation law. The reliability of the finite element model is validated through rigorous comparison with experimental data. The study investigates the influence of laminate layup sequence, impact energy, and impactor shape on the impact resistance of laminates. The results show that during low‐speed impacts, laminate damage is primarily characterized by fiber breakage, matrix cracking, and delamination. Matrix cracking and delamination become more pronounced as the impact energy increases. The design of linear spiral ply and power function spiral ply has a positive effect on the impact resistance of laminates. The impact resistance of laminates is sensitive to the sharpness of the impactor and the level of impact energy. Higher impact energy and sharper impactor shapes lead to increased energy absorption in the laminate, resulting in more pronounced damage failure.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>The impact resistance of bionic spiral composite laminates is studied.</jats:list-item> <jats:list-item>Three biologically inspired stacking sequences were designed.</jats:list-item> <jats:list-item>A numerical simulation method is proposed and verified.</jats:list-item> <jats:list-item>The low‐velocity impact characteristics of bionic laminates are revealed.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"6 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214671","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In this work, the behavior of carbon fiber reinforced polymer composites (CFRPs) interleaved with electrospun veils under low velocity impact (LVI) conditions and extreme environmental temperatures was investigated. 2/2 twill carbon fiber/epoxy laminates were subjected to LVI at three energy levels (10, 20, and 30 J), and three temperatures (−50°C, room temperature, and 100°C). Two interleaved configurations were explored (six veils placed symmetrically with respect to the middle plane of the laminate and with respect to the external layers of the laminate). Particularly at room temperature and up to 20 J, nanofibrous interlayers effectively reduced localized deformation (by about 13.0%) and delamination (by about 12.2%) when positioned in the outer ply interleaved configuration compared to the reference laminate. At 100°C, this effect is maintained at 10 J, preventing an increase in the delaminated area. At −50°C and 10 J, the promotion of delamination prevented back surface fiber failure. Regarding post‐impact flexural properties, the presence of nanoveils ensured superior mechanical properties compared to the corresponding reference laminate impacted at the same conditions, demonstrating their efficacy in enhancing the damage tolerance of the overall laminate.HighlightsElectrospun veils were interleaved in 20 layers of 2/2 twill carbon/epoxy laminate.Three configurations were tested under LVI at 10 J, 20 J, 30 J, and −50°C, RT, and 100°C.Observed damage modes include delamination, indentation, and back surface fiber cracks.Veils symmetrically placed in external layers limit delamination at 20 J (RT) and 10 J (100°C).Electrospun veils enhanced CFRP bending and residual post‐impact properties at RT and 100°C.
{"title":"Extreme temperature influence on low velocity impact damage and residual flexural properties of CFRP","authors":"Irene Bavasso, Claudia Sergi, Luca Ferrante, Marzena Pawlik, Yiling Lu, Luca Lampani, Jacopo Tirillò, Fabrizio Sarasini","doi":"10.1002/pc.29029","DOIUrl":"https://doi.org/10.1002/pc.29029","url":null,"abstract":"<jats:label/>In this work, the behavior of carbon fiber reinforced polymer composites (CFRPs) interleaved with electrospun veils under low velocity impact (LVI) conditions and extreme environmental temperatures was investigated. 2/2 twill carbon fiber/epoxy laminates were subjected to LVI at three energy levels (10, 20, and 30 J), and three temperatures (−50°C, room temperature, and 100°C). Two interleaved configurations were explored (six veils placed symmetrically with respect to the middle plane of the laminate and with respect to the external layers of the laminate). Particularly at room temperature and up to 20 J, nanofibrous interlayers effectively reduced localized deformation (by about 13.0%) and delamination (by about 12.2%) when positioned in the outer ply interleaved configuration compared to the reference laminate. At 100°C, this effect is maintained at 10 J, preventing an increase in the delaminated area. At −50°C and 10 J, the promotion of delamination prevented back surface fiber failure. Regarding post‐impact flexural properties, the presence of nanoveils ensured superior mechanical properties compared to the corresponding reference laminate impacted at the same conditions, demonstrating their efficacy in enhancing the damage tolerance of the overall laminate.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>Electrospun veils were interleaved in 20 layers of 2/2 twill carbon/epoxy laminate.</jats:list-item> <jats:list-item>Three configurations were tested under LVI at 10 J, 20 J, 30 J, and −50°C, RT, and 100°C.</jats:list-item> <jats:list-item>Observed damage modes include delamination, indentation, and back surface fiber cracks.</jats:list-item> <jats:list-item>Veils symmetrically placed in external layers limit delamination at 20 J (RT) and 10 J (100°C).</jats:list-item> <jats:list-item>Electrospun veils enhanced CFRP bending and residual post‐impact properties at RT and 100°C.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"63 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214651","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In this study, the post‐buckling damage behavior of cylindrical composite tubes was examined experimentally. The samples were reinforced with glass, carbon, and kevlar fibers to obtain glass‐reinforced fiber polymer (GRFP), carbon‐reinforced fiber polymer (CRFP), and Kevlar‐reinforced fiber polymer (KRFP) cylindrical tubes. The samples were produced using 4 stacking layers with filament winding technology. In producing all composite tubes, the outer diameter was kept constant at 17 mm, and two inner diameters of 12 and 13 mm, two wall thicknesses, 5 winding angles, and two lengths were used as parameters. The load was applied to the samples until completely damaged, and the maximum post‐buckling load values obtained were measured on the testing device. The effect of different reinforcement materials, winding angle, wall thickness, and length on the load‐carrying capacity was analyzed and it was understood that they had a significant effect. It was observed that the load‐carrying capacity of GFRP samples was the highest compared to the others, followed by CFRP and KFRP samples, respectively. In all samples, it was observed that a 0.5 mm wall thickness increase increased the load‐carrying capacity, while a 50 mm length increase decreased it. The energy absorption (EA) values of GFRP, CFRP, and KFRP samples were 46.99, 25.22, and 15.48 Joules, respectively. It was understood that the energy absorption of GFRP samples was 1.86 times better than CFRP and 3 times better than KFRP.HighlightsThe samples were produced using the fiber winding method, which is one of the most common production methods in the manufacture of tubes.Three different polymer reinforcement materials were used in the production of the samples.The effects of polymer reinforcement material, winding angle, length, and wall thickness on the maximum post‐buckling load were investigated.Wall thickness was found to have a significant effect on the maximum post‐buckling load.It was observed that GFRP samples had the highest energy absorption feature.
{"title":"The post‐buckling analysis of cylindrical polymer fiber‐reinforced composite tubes subjected to axial loading fabricated by filament winding technology","authors":"Hayri Yıldırım","doi":"10.1002/pc.28960","DOIUrl":"https://doi.org/10.1002/pc.28960","url":null,"abstract":"<jats:label/>In this study, the post‐buckling damage behavior of cylindrical composite tubes was examined experimentally. The samples were reinforced with glass, carbon, and kevlar fibers to obtain glass‐reinforced fiber polymer (GRFP), carbon‐reinforced fiber polymer (CRFP), and Kevlar‐reinforced fiber polymer (KRFP) cylindrical tubes. The samples were produced using 4 stacking layers with filament winding technology. In producing all composite tubes, the outer diameter was kept constant at 17 mm, and two inner diameters of 12 and 13 mm, two wall thicknesses, 5 winding angles, and two lengths were used as parameters. The load was applied to the samples until completely damaged, and the maximum post‐buckling load values obtained were measured on the testing device. The effect of different reinforcement materials, winding angle, wall thickness, and length on the load‐carrying capacity was analyzed and it was understood that they had a significant effect. It was observed that the load‐carrying capacity of GFRP samples was the highest compared to the others, followed by CFRP and KFRP samples, respectively. In all samples, it was observed that a 0.5 mm wall thickness increase increased the load‐carrying capacity, while a 50 mm length increase decreased it. The energy absorption (EA) values of GFRP, CFRP, and KFRP samples were 46.99, 25.22, and 15.48 Joules, respectively. It was understood that the energy absorption of GFRP samples was 1.86 times better than CFRP and 3 times better than KFRP.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>The samples were produced using the fiber winding method, which is one of the most common production methods in the manufacture of tubes.</jats:list-item> <jats:list-item>Three different polymer reinforcement materials were used in the production of the samples.</jats:list-item> <jats:list-item>The effects of polymer reinforcement material, winding angle, length, and wall thickness on the maximum post‐buckling load were investigated.</jats:list-item> <jats:list-item>Wall thickness was found to have a significant effect on the maximum post‐buckling load.</jats:list-item> <jats:list-item>It was observed that GFRP samples had the highest energy absorption feature.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"15 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214653","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This work proposes three Bouligand‐inspired layups to enhance low velocity impact (LVI) damage resistance and tolerance of convectional aircraft composite laminates. Two Bouligand‐like (HL and HL_S) and one hybrid design layup, merging conventional and Bouligand architecture (HYB), were produced by vacuum bag infusion. Their performance under LVI, at 13.5, 25 and 40 (J), and compression after impact (CAI) tests were evaluated and compared with a conventional aircraft multidirectional layup (LS) produced under identical conditions. Results demonstrated that, especially for the higher impact energy levels, both Bouligand‐like laminates consistently outperformed all the other configurations, exhibiting higher load bearing capacity (peak load) and energy absorption. Additionally, the rough and poorly defined interlaminar region of Bouligand‐like layups have showed to delay severe damage for higher loads and energies, dissipating all (at 13.5 J) or most of the impact energy (more than 50%) through subcritical damage mechanisms. Compared with LS laminate, Bouligand‐inspired layups postponed the onset of severe damage thresholds by up to 120% in load and 66% in energy (HL laminate) while developing smaller and more localized damages. The high number of fibers aligned in the loading direction of LS laminate led to better damage tolerance.HighlightsVacuum bag infused Bouligand‐like laminates consistently demonstrated superior performance than the conventional aircraft multidirectional layup, exhibiting higher load bearing capacity and energy absorption, particularly at higher impact energy levels;The rough and poorly defined interlaminar region observed in both Bouligand‐like layups demonstrated to play an essential role in the efficiency of damage mechanisms, dissipating all (at low impact energy levels) or more than 50% of impact energy on subcritical damages, such as translaminar matrix cracking;Compared with the conventional layup, HL Bouligand‐like laminate postponed 120% and 66% load and energy severe damage onset thresholds;The high number of fibers aligned in the loading direction of LS laminate led to better damage tolerance, despite the larger damaged areas observed.
{"title":"Low velocity impact study of vacuum bag infused bouligand inspired composites","authors":"L. Amorim, A. Santos, J. P. Nunes, J. C. Viana","doi":"10.1002/pc.28982","DOIUrl":"https://doi.org/10.1002/pc.28982","url":null,"abstract":"<jats:label/>This work proposes three Bouligand‐inspired layups to enhance low velocity impact (LVI) damage resistance and tolerance of convectional aircraft composite laminates. Two Bouligand‐like (HL and HL_S) and one hybrid design layup, merging conventional and Bouligand architecture (HYB), were produced by vacuum bag infusion. Their performance under LVI, at 13.5, 25 and 40 (J), and compression after impact (CAI) tests were evaluated and compared with a conventional aircraft multidirectional layup (LS) produced under identical conditions. Results demonstrated that, especially for the higher impact energy levels, both Bouligand‐like laminates consistently outperformed all the other configurations, exhibiting higher load bearing capacity (peak load) and energy absorption. Additionally, the rough and poorly defined interlaminar region of Bouligand‐like layups have showed to delay severe damage for higher loads and energies, dissipating all (at 13.5 J) or most of the impact energy (more than 50%) through subcritical damage mechanisms. Compared with LS laminate, Bouligand‐inspired layups postponed the onset of severe damage thresholds by up to 120% in load and 66% in energy (HL laminate) while developing smaller and more localized damages. The high number of fibers aligned in the loading direction of LS laminate led to better damage tolerance.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>Vacuum bag infused Bouligand‐like laminates consistently demonstrated superior performance than the conventional aircraft multidirectional layup, exhibiting higher load bearing capacity and energy absorption, particularly at higher impact energy levels;</jats:list-item> <jats:list-item>The rough and poorly defined interlaminar region observed in both Bouligand‐like layups demonstrated to play an essential role in the efficiency of damage mechanisms, dissipating all (at low impact energy levels) or more than 50% of impact energy on subcritical damages, such as translaminar matrix cracking;</jats:list-item> <jats:list-item>Compared with the conventional layup, HL Bouligand‐like laminate postponed 120% and 66% load and energy severe damage onset thresholds;</jats:list-item> <jats:list-item>The high number of fibers aligned in the loading direction of LS laminate led to better damage tolerance, despite the larger damaged areas observed.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"97 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214664","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
A. Rafay, M. Irfan, S. R. Naqvi, M. A. Umer, M. A. Rehman, M. Saleem, M. S. Butt, A. U. Khan
Environmental hazards caused by the ever‐increasing end‐of‐life (EoL) glass fiber reinforced polymer (GFRPs) composite waste is of major concern for the sustainable development of the industry. Compared to land filling or incineration, pyrolysis is one of the most promising environmentally friendly methods of disposal of EoL GFRPs. Pyrolysis not only results in recovery of clean glass fibers but other valuable products, such as oils. However, long processing time at elevated temperature leads to aggravation of already existed surface flaws along with the structural changes. Therefore, thermal conditioning of glass fibers results in severe deterioration of the strength in recovered fibers and hence limiting the use of recovered fibers to low end‐products. In this study, a new strategy was adopted where instead of complete cleaning of the fibers at pyrolysis stage, the fibers were partially oxidized and the complete removal of char from the surface of glass was done during hot alkaline etching. This strategy was opted to enhance the quality of the required fibers while reducing the processing time. The results showed ~200% increase in strength of fibers after the combined treatment of pyrolysis and post etching compared to the just pyrolyzed samples with etching time of just 1 min.HighlightsEnd‐of‐life panels of GFRPs were pyrolyzed under inert environment of Argon.Residual char was partially removed through post oxidation under flowing air.Hot alkaline etching resulted in complete removal of char and surface defects.Partial oxidation and short etching cycles resulted in improved strength of recovered glass fibers.
{"title":"Recovery and restoration of glass fibers from end‐of‐life composite waste through pyrolysis and partial oxidation processes combined with hot alkaline surface treatments","authors":"A. Rafay, M. Irfan, S. R. Naqvi, M. A. Umer, M. A. Rehman, M. Saleem, M. S. Butt, A. U. Khan","doi":"10.1002/pc.28916","DOIUrl":"https://doi.org/10.1002/pc.28916","url":null,"abstract":"<jats:label/>Environmental hazards caused by the ever‐increasing end‐of‐life (EoL) glass fiber reinforced polymer (GFRPs) composite waste is of major concern for the sustainable development of the industry. Compared to land filling or incineration, pyrolysis is one of the most promising environmentally friendly methods of disposal of EoL GFRPs. Pyrolysis not only results in recovery of clean glass fibers but other valuable products, such as oils. However, long processing time at elevated temperature leads to aggravation of already existed surface flaws along with the structural changes. Therefore, thermal conditioning of glass fibers results in severe deterioration of the strength in recovered fibers and hence limiting the use of recovered fibers to low end‐products. In this study, a new strategy was adopted where instead of complete cleaning of the fibers at pyrolysis stage, the fibers were partially oxidized and the complete removal of char from the surface of glass was done during hot alkaline etching. This strategy was opted to enhance the quality of the required fibers while reducing the processing time. The results showed ~200% increase in strength of fibers after the combined treatment of pyrolysis and post etching compared to the just pyrolyzed samples with etching time of just 1 min.Highlights<jats:list list-type=\"bullet\"> <jats:list-item>End‐of‐life panels of GFRPs were pyrolyzed under inert environment of Argon.</jats:list-item> <jats:list-item>Residual char was partially removed through post oxidation under flowing air.</jats:list-item> <jats:list-item>Hot alkaline etching resulted in complete removal of char and surface defects.</jats:list-item> <jats:list-item>Partial oxidation and short etching cycles resulted in improved strength of recovered glass fibers.</jats:list-item> </jats:list>","PeriodicalId":20375,"journal":{"name":"Polymer Composites","volume":"5 1","pages":""},"PeriodicalIF":5.2,"publicationDate":"2024-09-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142214665","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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