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.2021.010
J. Bénézech, L. Seelinger, T. Dodwell, P. Bastian, Robert Scheichl, R. Butler
The CerTest project aims at developing a new design/certification process, adapted to composites for aerospace application. The quantification of uncertainties, arising from material variability and experimental measurements for example, forms a critical challenge. When applied to large scale composite parts, the primary challenge is the cost of the associated numerical simulation required to evaluate the material response for a (typically large) set of parameters. To this end, a GMsFEM [1] type method has been chosen to efficiently simulate large parts (up to a billion dofs) without scale separation, illustrated on Figure 1. Variants of GMsFEM differ in their choice of local basis: a suitable choice for structural mechanics is the one derived from the Generalized Eigenvalue problem for Overlapping subdomains (GenEO) [2]. To be integrated in a stochastic framework the computational cost is divided into two phases: offline and online. In the offline phase, the GenEO coarse space is generated using a parallel setting for a given set of parameters (i.e. a pristine part). During this phase, information is stored; a database is hence initiated. The online phase is dedicated to assess the effect of one or multiple changes in the parameters (such as a defect). This offers huge computational savings for large components, since the majority of basis functions are simply loaded from the database. Thus, online phases can be carried out on single processors, freeing parallel
{"title":"Scalable Localized Model Order Reduction Applied to Composite Aero-Structures","authors":"J. Bénézech, L. Seelinger, T. Dodwell, P. Bastian, Robert Scheichl, R. Butler","doi":"10.23967/composites.2021.010","DOIUrl":"https://doi.org/10.23967/composites.2021.010","url":null,"abstract":"The CerTest project aims at developing a new design/certification process, adapted to composites for aerospace application. The quantification of uncertainties, arising from material variability and experimental measurements for example, forms a critical challenge. When applied to large scale composite parts, the primary challenge is the cost of the associated numerical simulation required to evaluate the material response for a (typically large) set of parameters. To this end, a GMsFEM [1] type method has been chosen to efficiently simulate large parts (up to a billion dofs) without scale separation, illustrated on Figure 1. Variants of GMsFEM differ in their choice of local basis: a suitable choice for structural mechanics is the one derived from the Generalized Eigenvalue problem for Overlapping subdomains (GenEO) [2]. To be integrated in a stochastic framework the computational cost is divided into two phases: offline and online. In the offline phase, the GenEO coarse space is generated using a parallel setting for a given set of parameters (i.e. a pristine part). During this phase, information is stored; a database is hence initiated. The online phase is dedicated to assess the effect of one or multiple changes in the parameters (such as a defect). This offers huge computational savings for large components, since the majority of basis functions are simply loaded from the database. Thus, online phases can be carried out on single processors, freeing parallel","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"46 11","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114119627","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.2021.008
A. Mikhaylenko, N. Bellam-Muralidhar, N. Rauter, D. Lorenz, R. Lammering
Fiber metal laminates (FML) combine the ductile properties of metal with the high specific stiffness of fiber reinforced plastics. FML also offer substantial reduction in weight along with excellent fatigue strength. These features of FML lead to a dramatic rise of interest in such ma-terials for aeronautical structures lately. However, one of the most vulnerable failures for FML is impact-related delamination which is not detectable with the naked eye. Such damage has to be detected in time to enable a possible repair. Structural health monitoring with the guided ultrasonic waves (GUW) could potentially serve the purpose of damage detection in thin structures by using the physical phenomena of wave propagation interacting with structure defects [1]. The focus this work is on the numerical simulation of GUW propagation in FML structures. The investigation of this subject follows as forward and inverse problem analysis. Based on an already existing 2D model a 3D finite element model is developed using COMSOL Multiphysics® Software involving the excitation of waves and observing its propagation in the structure. One crucial aspect here is the model discretization and hence, the corresponding element size. To validate the numerical model the wave propagation and the resulting displacement field are compared to the analytical solution derived from the dispersion relation. In this context a mode selective excitation is used in order to have a clear observation and to be able to separate different wave modes.
{"title":"Numerical Analisys of Guided Ultrasonic Wave Propagation in Fiber Metal Laminates","authors":"A. Mikhaylenko, N. Bellam-Muralidhar, N. Rauter, D. Lorenz, R. Lammering","doi":"10.23967/composites.2021.008","DOIUrl":"https://doi.org/10.23967/composites.2021.008","url":null,"abstract":"Fiber metal laminates (FML) combine the ductile properties of metal with the high specific stiffness of fiber reinforced plastics. FML also offer substantial reduction in weight along with excellent fatigue strength. These features of FML lead to a dramatic rise of interest in such ma-terials for aeronautical structures lately. However, one of the most vulnerable failures for FML is impact-related delamination which is not detectable with the naked eye. Such damage has to be detected in time to enable a possible repair. Structural health monitoring with the guided ultrasonic waves (GUW) could potentially serve the purpose of damage detection in thin structures by using the physical phenomena of wave propagation interacting with structure defects [1]. The focus this work is on the numerical simulation of GUW propagation in FML structures. The investigation of this subject follows as forward and inverse problem analysis. Based on an already existing 2D model a 3D finite element model is developed using COMSOL Multiphysics® Software involving the excitation of waves and observing its propagation in the structure. One crucial aspect here is the model discretization and hence, the corresponding element size. To validate the numerical model the wave propagation and the resulting displacement field are compared to the analytical solution derived from the dispersion relation. In this context a mode selective excitation is used in order to have a clear observation and to be able to separate different wave modes.","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":"114279827","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.2021.032
C. Fougerouse, C. Fagiano, M. Hirsekorn, F. Laurin, M. Desailloud, M. Herman
Composite laminates with thermoplastic matrices are potential candidates for structural applications in aerospace. As a new material, investigations are needed to support parts quality definition. Indeed, manufacturing defects, such as out-of-plane waviness, may be accepted in composite structures if they do not significantly affect the performances of the part. Waviness defects are known for having an impact on the longitudinal compressive strength [1, 2]; but they were mainly studied in thermoset matrix components. The objective of this study is to numerically assess the effects of out-of-plane waviness within laminates with unidirectional plies (made of carbon fibres and a thermoplastic matrix), on the elastic properties and, damage onset and kinetics. An experimental campaign was performed at ONERA to calibrate and validate the numerical results. First, an analytical description of defect geometries is proposed based on experimental observations of specimens of industrial interest. The extracted parameters have a physical meaning, e.g. the defect extent or the amplitude. The parametrised description
{"title":"Numerical Determination of the Effects of Out-of-Plane Waviness in Thermoplastic Matrix Laminates","authors":"C. Fougerouse, C. Fagiano, M. Hirsekorn, F. Laurin, M. Desailloud, M. Herman","doi":"10.23967/composites.2021.032","DOIUrl":"https://doi.org/10.23967/composites.2021.032","url":null,"abstract":"Composite laminates with thermoplastic matrices are potential candidates for structural applications in aerospace. As a new material, investigations are needed to support parts quality definition. Indeed, manufacturing defects, such as out-of-plane waviness, may be accepted in composite structures if they do not significantly affect the performances of the part. Waviness defects are known for having an impact on the longitudinal compressive strength [1, 2]; but they were mainly studied in thermoset matrix components. The objective of this study is to numerically assess the effects of out-of-plane waviness within laminates with unidirectional plies (made of carbon fibres and a thermoplastic matrix), on the elastic properties and, damage onset and kinetics. An experimental campaign was performed at ONERA to calibrate and validate the numerical results. First, an analytical description of defect geometries is proposed based on experimental observations of specimens of industrial interest. The extracted parameters have a physical meaning, e.g. the defect extent or the amplitude. The parametrised description","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"69 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":"114429119","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}
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