Pub Date : 1900-01-01DOI: 10.23967/composites.2021.013
S. Miot, L. Barrière, J. Casero, M. Lozzo
Reducing uncertainties and therefore risks in structural design implies determining accurate statistically-based properties of the material. IRT Saint-Exupéry has been developing a software solution called VIMS that uses the GEMS open source python library [1] to generate material allowables. VIMS offers a framework to integrate, evaluate and use advanced composites models in association with experimental data post-processing, decision-making support and an innovation-friendly environment that facilitates the deployment within design offices. Fig.1 illustrates the strategies implemented in VIMS.
减少结构设计中的不确定性和风险意味着确定准确的基于统计的材料特性。IRT saint - exupsamry一直在开发一个名为VIMS的软件解决方案，该解决方案使用GEMS开源python库[1]来生成材料允许值。VIMS提供了一个框架，可以集成、评估和使用先进的复合材料模型，并结合实验数据后处理、决策支持和创新环境，促进设计办公室的部署。图1说明了在VIMS中实现的策略。
{"title":"Virtual Testing Integration and Material Allowables Generation","authors":"S. Miot, L. Barrière, J. Casero, M. Lozzo","doi":"10.23967/composites.2021.013","DOIUrl":"https://doi.org/10.23967/composites.2021.013","url":null,"abstract":"Reducing uncertainties and therefore risks in structural design implies determining accurate statistically-based properties of the material. IRT Saint-Exupéry has been developing a software solution called VIMS that uses the GEMS open source python library [1] to generate material allowables. VIMS offers a framework to integrate, evaluate and use advanced composites models in association with experimental data post-processing, decision-making support and an innovation-friendly environment that facilitates the deployment within design offices. Fig.1 illustrates the strategies implemented in VIMS.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117319193","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.081
S. Hermansen, E. Lund
Structural design against fatigue failure is typically a comprehensive exercise. This is particularly the case for laminated composite structures due to the added complexity associated with their multi-directional behavior, resulting in materialand load-dependent failure modes. In fatigue analysis, these factors materialize as a non-linear relationship between reversals to failure and mean stress, load sequence effects as well as stiffness and strength degradation that also have to be taken into account. To minimize the material use in composite structures, it is desirable to apply structural optimization. In this work, a methodology for gradient-based high-cycle fatigue optimization of general laminated composite structures is presented. An efficient approach for fatigue topology optimization was demonstrated in [1] by the use of an aggregation function to reduce the amount of fatigue damage measures from local finite element quantities to a single global measure. This is utilized with the adjoint method to efficiently compute gradients by solving only an extra set of linear equations where the factored stiffness matrix is reused. This same approach is adopted for solving the present problem. Parametrization of the structure is done by Discrete Material and Thickness Optimization (DMTO) approach [2], such that an optimized combination of material, fiber orientation, layup sequence, and layer thickness is sought. The fatigue analysis approach used in this work is typically employed in the wind turbine industry for blade design, see e.g. [3]. Offset is taken in variable amplitude loading, which is quantified by Rainflow counting yielding a set of scaling factors for determining amplitude and mean stress. Proportional loading is assumed, meaning the computationally expensive Rainflow counting only has to be performed once during the optimization. A constant life diagram approach is used to calculate an equivalent stress from the amplitude and mean components, taking into account mean stress of various magnitudes by interpolating between their respective SN curves. Reversals to failure are then computed from the SN curves, which are constructed using a data-fitted power law. Damages are then summed using cumulative methods such as linear and non-linear Palmgren-Miner sum. A number of structural optimization examples including fatigue constraints will demonstrate the potential of this approach.
{"title":"High-cycle Fatigue Optimization of Laminated Composite Structures","authors":"S. Hermansen, E. Lund","doi":"10.23967/composites.2021.081","DOIUrl":"https://doi.org/10.23967/composites.2021.081","url":null,"abstract":"Structural design against fatigue failure is typically a comprehensive exercise. This is particularly the case for laminated composite structures due to the added complexity associated with their multi-directional behavior, resulting in materialand load-dependent failure modes. In fatigue analysis, these factors materialize as a non-linear relationship between reversals to failure and mean stress, load sequence effects as well as stiffness and strength degradation that also have to be taken into account. To minimize the material use in composite structures, it is desirable to apply structural optimization. In this work, a methodology for gradient-based high-cycle fatigue optimization of general laminated composite structures is presented. An efficient approach for fatigue topology optimization was demonstrated in [1] by the use of an aggregation function to reduce the amount of fatigue damage measures from local finite element quantities to a single global measure. This is utilized with the adjoint method to efficiently compute gradients by solving only an extra set of linear equations where the factored stiffness matrix is reused. This same approach is adopted for solving the present problem. Parametrization of the structure is done by Discrete Material and Thickness Optimization (DMTO) approach [2], such that an optimized combination of material, fiber orientation, layup sequence, and layer thickness is sought. The fatigue analysis approach used in this work is typically employed in the wind turbine industry for blade design, see e.g. [3]. Offset is taken in variable amplitude loading, which is quantified by Rainflow counting yielding a set of scaling factors for determining amplitude and mean stress. Proportional loading is assumed, meaning the computationally expensive Rainflow counting only has to be performed once during the optimization. A constant life diagram approach is used to calculate an equivalent stress from the amplitude and mean components, taking into account mean stress of various magnitudes by interpolating between their respective SN curves. Reversals to failure are then computed from the SN curves, which are constructed using a data-fitted power law. Damages are then summed using cumulative methods such as linear and non-linear Palmgren-Miner sum. A number of structural optimization examples including fatigue constraints will demonstrate the potential of this approach.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131174615","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.092
E. Zappino, M. Petrolo, N. Zobeiry, E. Carrera
The manufacturing process of composite materials leads to residual stresses and process-induced deformations. These defects originate from the thermoset resin’s curing process, and the thermo-elastic loads originated by the curing cycle [1]. The extent of residual stresses and deformations can be affected by many parameters, e.g., stacking sequence, part geometry, curing cycle, tool-part interaction, tool material. Curved parts, such as L-shaped components, undergo severe residual deformations, referred to as spring-in angle. The prediction of these phenomena requires the use of refined numerical models. The three-dimensional nature of the problem and the multiple physical fields involved make classical models ineffective. The use of solid elements leads to accurate results but requires a very high computational cost. An efficient numerical approach for predicting the spring-in angle of composite parts has been presented recently [2]. The use of higher-order finite elements has been demonstrated to be as accurate as a three-dimensional model with a fraction of the computational cost. The present work exploits the computational efficiency of this model [3] to investigate the effects of many parameters on residual stresses and process-induced deformations of L-shaped composite parts. A large simulation matrix has been considered, including a combination of different stacking sequences, tool materials, curing cycles, and part geometries. The effects of each of those parameters on the spring-in angle have been evaluated. The use of a layer-wise model has allowed the effects of each parameter on the residual stresses to be investigated. The
{"title":"Process Induced Deformations and Residual Stresses in Curved Composite Parts: A Parametric Analysis","authors":"E. Zappino, M. Petrolo, N. Zobeiry, E. Carrera","doi":"10.23967/composites.2021.092","DOIUrl":"https://doi.org/10.23967/composites.2021.092","url":null,"abstract":"The manufacturing process of composite materials leads to residual stresses and process-induced deformations. These defects originate from the thermoset resin’s curing process, and the thermo-elastic loads originated by the curing cycle [1]. The extent of residual stresses and deformations can be affected by many parameters, e.g., stacking sequence, part geometry, curing cycle, tool-part interaction, tool material. Curved parts, such as L-shaped components, undergo severe residual deformations, referred to as spring-in angle. The prediction of these phenomena requires the use of refined numerical models. The three-dimensional nature of the problem and the multiple physical fields involved make classical models ineffective. The use of solid elements leads to accurate results but requires a very high computational cost. An efficient numerical approach for predicting the spring-in angle of composite parts has been presented recently [2]. The use of higher-order finite elements has been demonstrated to be as accurate as a three-dimensional model with a fraction of the computational cost. The present work exploits the computational efficiency of this model [3] to investigate the effects of many parameters on residual stresses and process-induced deformations of L-shaped composite parts. A large simulation matrix has been considered, including a combination of different stacking sequences, tool materials, curing cycles, and part geometries. The effects of each of those parameters on the spring-in angle have been evaluated. The use of a layer-wise model has allowed the effects of each parameter on the residual stresses to be investigated. The","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133217117","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.064
M. Fagerström, G.Catalanotti, Campos Daniel, Maimí Pere, López Sergi, Martín Alberto
This paper describes the experimental work carried out to characterize the interlaminar friction phenomena during dynamic forming processes for thermoplastic composites materials. First, Differential Scanning Calorimetry (DSC) and Dynamic Mechanical Analysis (DMA) were conducted to study the microstructural behaviours of both target materials: UD PEEK (Polyetheretherketone) and UD PAEK (Polyaryletherketone) prepregs. Second, a set of experiments inspired by the work of Murtagh [1], Vanclooster [2], and Sachs [3] was performed to obtain the dependency of the different parameters, such as temperature, pressure, and pulling rate on the interlaminar friction coefficient and shear stress. The proposed experimental process was a horizontal pull-out fixed-plies test. This rig consisted of pulling out a ply that lays in between two fixed plies. A machine applied a relative sliding motion between the middle ply and the fixed ones by loading the system in tension while a normal force was applied. A load cell was placed between the clamping and the pulling machine to measure the friction force. Temperatures
{"title":"Characterization of Interlaminar Friction During Forming Processes of Thermoplastic CFRP Materials","authors":"M. Fagerström, G.Catalanotti, Campos Daniel, Maimí Pere, López Sergi, Martín Alberto","doi":"10.23967/composites.2021.064","DOIUrl":"https://doi.org/10.23967/composites.2021.064","url":null,"abstract":"This paper describes the experimental work carried out to characterize the interlaminar friction phenomena during dynamic forming processes for thermoplastic composites materials. First, Differential Scanning Calorimetry (DSC) and Dynamic Mechanical Analysis (DMA) were conducted to study the microstructural behaviours of both target materials: UD PEEK (Polyetheretherketone) and UD PAEK (Polyaryletherketone) prepregs. Second, a set of experiments inspired by the work of Murtagh [1], Vanclooster [2], and Sachs [3] was performed to obtain the dependency of the different parameters, such as temperature, pressure, and pulling rate on the interlaminar friction coefficient and shear stress. The proposed experimental process was a horizontal pull-out fixed-plies test. This rig consisted of pulling out a ply that lays in between two fixed plies. A machine applied a relative sliding motion between the middle ply and the fixed ones by loading the system in tension while a normal force was applied. A load cell was placed between the clamping and the pulling machine to measure the friction force. Temperatures","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115402607","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.120
Elias I. B¨orjesson, Martin Fagerstr¨om, J. Remmers
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{"title":"An Arc-Length Solver with Dissipation Path-Following for Complex Analysis of Brittle Failure and Stability of Composite Structures","authors":"Elias I. B¨orjesson, Martin Fagerstr¨om, J. Remmers","doi":"10.23967/composites.2021.120","DOIUrl":"https://doi.org/10.23967/composites.2021.120","url":null,"abstract":".","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"345 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123321473","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.099
S. O. Ojo, C. Luan, Trinh, P. M. Weaver
Modelling of laminated structures requires adequate computational frameworks which can accurately estimate displacement and stress fields resulting from systems of high-order partial differential equations [1]. The recently developed inverse differential quadrature method (iDQM) [2] shows promising outcomes for obtaining solution of high-order systems of equation. In this study, we perform static analysis of composite structures based on the theory of Unified Formulation (UF) and mixed methods, comprising of a combination of high-order Finite Element (FE) Method and the new iDQM. According to the theory of UF, a 3D structure is geometrically reconfigured by separating the kinematics governing the 2D cross-section from the 1D axial deformation. In this context, the so-called Serendipity Lagrange Element [3] is employed in a FE framework to capture the cross-sectional deformation with enhanced accuracy without the need for remeshing or loss of numerical stability. On the other hand, the deformation of the refined 1D structure is captured by a new iDQM-based beam element which is either characterised by approximation of derivatives of intermediate order (in a mixed iDQM framework) or highest derivatives (in a full iDQM framework) of the 1D displacement fields. By invoking plane strain and simple support conditions, FE-iDQM predictions of stresses for different lami-nate configurations show good agreement with Pagano’s exact solution and compare well with DQM solutions with the same level of discretisation as shown in Figure 1.
{"title":"Inverse Differential Quadrature Method for 3d Static Analysis of Composite Beam Structures","authors":"S. O. Ojo, C. Luan, Trinh, P. M. Weaver","doi":"10.23967/composites.2021.099","DOIUrl":"https://doi.org/10.23967/composites.2021.099","url":null,"abstract":"Modelling of laminated structures requires adequate computational frameworks which can accurately estimate displacement and stress fields resulting from systems of high-order partial differential equations [1]. The recently developed inverse differential quadrature method (iDQM) [2] shows promising outcomes for obtaining solution of high-order systems of equation. In this study, we perform static analysis of composite structures based on the theory of Unified Formulation (UF) and mixed methods, comprising of a combination of high-order Finite Element (FE) Method and the new iDQM. According to the theory of UF, a 3D structure is geometrically reconfigured by separating the kinematics governing the 2D cross-section from the 1D axial deformation. In this context, the so-called Serendipity Lagrange Element [3] is employed in a FE framework to capture the cross-sectional deformation with enhanced accuracy without the need for remeshing or loss of numerical stability. On the other hand, the deformation of the refined 1D structure is captured by a new iDQM-based beam element which is either characterised by approximation of derivatives of intermediate order (in a mixed iDQM framework) or highest derivatives (in a full iDQM framework) of the 1D displacement fields. By invoking plane strain and simple support conditions, FE-iDQM predictions of stresses for different lami-nate configurations show good agreement with Pagano’s exact solution and compare well with DQM solutions with the same level of discretisation as shown in Figure 1.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123859005","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.095
S. AhmadvashAghbash, C. Breite, M. Mehdikhani, Y. Swolfs
Fibre-matrix longitudinal debonding, governed by the interfacial shear strength and fracture toughness, alters the stress transfer mechanism in the composite by changing the stress field around the broken fiber [1]. In a majority of the fibre-matrix debonding finite element models in the literature, as in [2], the debonded length has been imposed based on the experimentally measured lengths. The simplified models typically treat the matrix as a linear elastic material and/or exclude the effects of interfacial friction and thermal residual stresses on the stress behavior of the constituents. The current work develops high-fidelity debonding models, which include the main relevant phenomena occurring in reality to perform a numerical parametric study of the interfacial properties in carbon fibre/epoxy systems in single-fiber (Figure 1a) and multi-fibre composites (Figure 1b-c). Numerical results show that the thermal residual stresses constrain the debond propagation and the interfacial friction has a significant influence on how the axial load in the broken fibre recovers (Figure 1d). Figure 1e shows the effect of fracture toughness on the stress profile for the broken fibre in the single-fibre model. It is concluded that, within the range of reported interfacial properties, for large friction coefficients (μ > 0.4) or high interfacial fracture toughnesses (GII c > 0.1 N/mm) no debonding will be developed.
纤维-基体纵向剥离受界面剪切强度和断裂韧性的支配，通过改变断裂纤维周围的应力场改变复合材料中的应力传递机制[1]。在文献中的大多数纤维矩阵脱粘有限元模型中，如[2]，脱粘长度是根据实验测量的长度施加的。简化模型通常将基体视为线弹性材料，并且/或排除了界面摩擦和热残余应力对组分应力行为的影响。目前的工作开发了高保真的脱粘模型，其中包括现实中发生的主要相关现象，以对单纤维(图1a)和多纤维复合材料(图1b-c)中碳纤维/环氧树脂体系的界面特性进行数值参数研究。数值结果表明，热残余应力约束了剥离扩展，界面摩擦对断裂纤维中轴向载荷的恢复有显著影响(图1d)。图1e显示了单纤维模型中断裂韧性对断裂纤维应力分布的影响。结果表明，在所报道的界面性能范围内，大摩擦系数(μ > 0.4)或高界面断裂韧性(GII c > 0.1 N/mm)不会发生脱粘。
{"title":"Longitudinal Debonding in Unidirectional Composites: A Numerical Study of the Effect of Interfacial Properties","authors":"S. AhmadvashAghbash, C. Breite, M. Mehdikhani, Y. Swolfs","doi":"10.23967/composites.2021.095","DOIUrl":"https://doi.org/10.23967/composites.2021.095","url":null,"abstract":"Fibre-matrix longitudinal debonding, governed by the interfacial shear strength and fracture toughness, alters the stress transfer mechanism in the composite by changing the stress field around the broken fiber [1]. In a majority of the fibre-matrix debonding finite element models in the literature, as in [2], the debonded length has been imposed based on the experimentally measured lengths. The simplified models typically treat the matrix as a linear elastic material and/or exclude the effects of interfacial friction and thermal residual stresses on the stress behavior of the constituents. The current work develops high-fidelity debonding models, which include the main relevant phenomena occurring in reality to perform a numerical parametric study of the interfacial properties in carbon fibre/epoxy systems in single-fiber (Figure 1a) and multi-fibre composites (Figure 1b-c). Numerical results show that the thermal residual stresses constrain the debond propagation and the interfacial friction has a significant influence on how the axial load in the broken fibre recovers (Figure 1d). Figure 1e shows the effect of fracture toughness on the stress profile for the broken fibre in the single-fibre model. It is concluded that, within the range of reported interfacial properties, for large friction coefficients (μ > 0.4) or high interfacial fracture toughnesses (GII c > 0.1 N/mm) no debonding will be developed.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131686177","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.086
J. Friemann, B. Dashtbozorg, M. Fagerström, M. Mirkhalaf
mechanical modeling of Short Fiber Reinforced Composites (SFRC) is of anisotropy, discontinuity and orientation distribution of fibers. to accurately predict the behavior of SFRC with fiber orientations and fiber volume fractions is in the design and produc-tion of injection molded parts. constitutive
{"title":"Predicting the Elasto-Plastic Response of Short Fiber Composites Using Deep Neural Networks Trained on Micro-Mechanical Simulations","authors":"J. Friemann, B. Dashtbozorg, M. Fagerström, M. Mirkhalaf","doi":"10.23967/composites.2021.086","DOIUrl":"https://doi.org/10.23967/composites.2021.086","url":null,"abstract":"mechanical modeling of Short Fiber Reinforced Composites (SFRC) is of anisotropy, discontinuity and orientation distribution of fibers. to accurately predict the behavior of SFRC with fiber orientations and fiber volume fractions is in the design and produc-tion of injection molded parts. constitutive","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"57 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121461283","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.028
S. Sapozhnikov, M. Gundappa, S. Lomov, Y. Swolfs, V. Carvelli
{"title":"Quasi-Isotropic Carbon-Carbon Hybrid Laminate: Static and Low-Cyclic Performance","authors":"S. Sapozhnikov, M. Gundappa, S. Lomov, Y. Swolfs, V. Carvelli","doi":"10.23967/composites.2021.028","DOIUrl":"https://doi.org/10.23967/composites.2021.028","url":null,"abstract":"","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124219799","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.23967/composites.2021.002
M. Linke, T. Genco, R. Lammering
During the service life of all kinds of structures (e.g. aircrafts, wind turbines) the structural integrity is a key factor for safe performance. Due to the increasing use of fibre reinforced polymers (FRP) in various structures, there is a growing need for timely detection of non-visible damage. Since common scheduled maintenance is ineffective in terms of time and cost, the investigation of possibly viable structural health monitoring (SHM) concepts is a main research focus [1]. Integration of electrical sensors into these structures allows diagnosis about the existence and extent of damage by measuring of in-situ electrical characteristics. Nanojet printed sensors made of carbon nanotube (CNT) enriched composite materials can exhibit considerable electrical and mechanical properties for this task.
{"title":"On the Numerical Modeling and Validation of Fracture Mechanics for Printed Electronics Composites.","authors":"M. Linke, T. Genco, R. Lammering","doi":"10.23967/composites.2021.002","DOIUrl":"https://doi.org/10.23967/composites.2021.002","url":null,"abstract":"During the service life of all kinds of structures (e.g. aircrafts, wind turbines) the structural integrity is a key factor for safe performance. Due to the increasing use of fibre reinforced polymers (FRP) in various structures, there is a growing need for timely detection of non-visible damage. Since common scheduled maintenance is ineffective in terms of time and cost, the investigation of possibly viable structural health monitoring (SHM) concepts is a main research focus [1]. Integration of electrical sensors into these structures allows diagnosis about the existence and extent of damage by measuring of in-situ electrical characteristics. Nanojet printed sensors made of carbon nanotube (CNT) enriched composite materials can exhibit considerable electrical and mechanical properties for this task.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124123860","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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