Pub Date : 1900-01-01DOI: 10.23967/composites.2021.053
M. Fagerström, G.Catalanotti, C. Krogh, Jørgen A. Kepler, Johnny Jakobsen
Wind turbine blades are manufactured from light and strong composite materials. The fiber material, predominantly glass fiber non-crimp fabric (NCF), is rolled out in the blade mold in courses and subsequently infused with the resin. The blade designers will typically specify e.g. the fiber orientations and thicknesses in various regions of the blade. These instructions must be translated into what courses to be placed where in the mold while at the same time paying attention to draping effects, i.e. shearing arising from double mold curvatures. Draping on a double-curved mold can be analyzed with a kinematic draping algorithm [1], e.g. commercially available with programs such as Composites Modeler for Abaqus/CAE, Ansys ACP and Fibersim. Although simple and kinematic, the draping model can predict the draped pattern with reasonable accuracy with a low computational effort. To this end, the applicability of optimization techniques is attractive, see e.g. ref. [2] in which a Genetic Algorithm (GA) is employed. Figure 1 shows the first results of the present study on course optimization, obtained by draping a single course along the right edge of a blade section and letting a GA determine the optimal starting point, i.e. a point of zero shear, to minimize the aggregated shear angles. As it can be seen, the maximum shear angle can be decreased from 10.8 ˚ to 2.7˚ if the starting point is moved from the lower right corner to a position in the center of the course.
风力涡轮机的叶片由轻质和坚固的复合材料制成。纤维材料，主要是玻璃纤维无卷曲织物(NCF)，在叶片模具中轧制成课程，随后注入树脂。叶片设计者通常会指定叶片不同区域的纤维方向和厚度。这些说明必须翻译成在模具中放置什么课程，同时注意悬垂效果，即由双模具曲率引起的剪切。双曲线模具上的悬垂可以使用运动学悬垂算法进行分析[1]，例如，可通过复合材料建模器(Composites Modeler for Abaqus/CAE)、Ansys ACP和Fibersim等商用程序进行分析。该模型虽然简单且具有运动学特征，但能以较低的计算量以合理的精度预测织物的垂型。为此，优化技术的适用性是有吸引力的，例如参考文献[2]，其中采用了遗传算法(GA)。图1显示了本研究的航向优化的第一个结果，通过沿叶片截面的右边缘悬垂单个航向，并让遗传算法确定最佳起点，即零剪切点，以最小化聚合剪切角。从图中可以看出，如果将起始点从右下角移动到赛道中心位置，最大剪切角可以从10.8˚减小到2.7˚。
{"title":"It‘s on a Roll: Draping Courses of Glass Fiber Fabric in a Wind Turbine Blade Mold by Means of Optimization","authors":"M. Fagerström, G.Catalanotti, C. Krogh, Jørgen A. Kepler, Johnny Jakobsen","doi":"10.23967/composites.2021.053","DOIUrl":"https://doi.org/10.23967/composites.2021.053","url":null,"abstract":"Wind turbine blades are manufactured from light and strong composite materials. The fiber material, predominantly glass fiber non-crimp fabric (NCF), is rolled out in the blade mold in courses and subsequently infused with the resin. The blade designers will typically specify e.g. the fiber orientations and thicknesses in various regions of the blade. These instructions must be translated into what courses to be placed where in the mold while at the same time paying attention to draping effects, i.e. shearing arising from double mold curvatures. Draping on a double-curved mold can be analyzed with a kinematic draping algorithm [1], e.g. commercially available with programs such as Composites Modeler for Abaqus/CAE, Ansys ACP and Fibersim. Although simple and kinematic, the draping model can predict the draped pattern with reasonable accuracy with a low computational effort. To this end, the applicability of optimization techniques is attractive, see e.g. ref. [2] in which a Genetic Algorithm (GA) is employed. Figure 1 shows the first results of the present study on course optimization, obtained by draping a single course along the right edge of a blade section and letting a GA determine the optimal starting point, i.e. a point of zero shear, to minimize the aggregated shear angles. As it can be seen, the maximum shear angle can be decreased from 10.8 ˚ to 2.7˚ if the starting point is moved from the lower right corner to a position in the center of the course.","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":"129018575","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.2021.108
M. Fagerström, G.Catalanotti, Oliver Dorn, Christian Rolffs, Sven Scheffler, Raimund Rolfes
Due to their superior lightweight potential, composites are used in a wide variety of large and slender structures such as gliders, rotor blades of wind turbines or vertical tails of transportation aircrafts. The numerical analysis of these laminated materials typically follows a layer-based approach which describes the stress-strain response of an unidirectional layer within the laminate. Advantages of this method are low experimental characterization costs. The material parameters for an unidirectional layer allow the analysis of arbitrary laminate stackings. In addition, since the position of each layer in the stacking sequence is available, the kinematic behavior of the laminate due to failure of single plies can be predicted accurately in terms of a progressive damage analysis. On the other hand taking material nonlinearities as failure modes, softening, viscoelasticity or plasticity in a
{"title":"On a Reduced Order Fe-Model to Simulate Nonlinear Material Response in Large Composite Structures","authors":"M. Fagerström, G.Catalanotti, Oliver Dorn, Christian Rolffs, Sven Scheffler, Raimund Rolfes","doi":"10.23967/composites.2021.108","DOIUrl":"https://doi.org/10.23967/composites.2021.108","url":null,"abstract":"Due to their superior lightweight potential, composites are used in a wide variety of large and slender structures such as gliders, rotor blades of wind turbines or vertical tails of transportation aircrafts. The numerical analysis of these laminated materials typically follows a layer-based approach which describes the stress-strain response of an unidirectional layer within the laminate. Advantages of this method are low experimental characterization costs. The material parameters for an unidirectional layer allow the analysis of arbitrary laminate stackings. In addition, since the position of each layer in the stacking sequence is available, the kinematic behavior of the laminate due to failure of single plies can be predicted accurately in terms of a progressive damage analysis. On the other hand taking material nonlinearities as failure modes, softening, viscoelasticity or plasticity in a","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"3 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":"131222519","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.2021.071
B. El Said, S. Hallett
{"title":"Non-Periodicity Challenges in Modelling and Experimental Testing of 3D Woven Composites","authors":"B. El Said, S. Hallett","doi":"10.23967/composites.2021.071","DOIUrl":"https://doi.org/10.23967/composites.2021.071","url":null,"abstract":"","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"47 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":"127087745","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.2021.017
M. Pham, M. Vorhof, T. Gereke, G. Hoffmann, C. Cherif
A new type of panels is developed that is based on spacer woven fabrics. A stable composite tape made of glass fiber rovings and a thermoplastic matrix is used as input material. These composite tapes are first formed with a pair of gears at elevated temperature to give them a three dimensional shape for weft insertion. The geometries of the gears depend on the configuration of the final panels. Secondly, the composite tapes prepared in this way are further processed on the weaving machine and spacer fabrics are fabricated. Finally, the spacer fabric is consolidated with a thermoset or thermoplastic matrix to form the final panel. A meso-scale finite element model based on shell elements is developed and used for the simulation of the panel manufacturing process and the structural behavior of the panels.
{"title":"Simulation Supported Development of Lightweight Panels with High Delamination Resistance","authors":"M. Pham, M. Vorhof, T. Gereke, G. Hoffmann, C. Cherif","doi":"10.23967/composites.2021.017","DOIUrl":"https://doi.org/10.23967/composites.2021.017","url":null,"abstract":"A new type of panels is developed that is based on spacer woven fabrics. A stable composite tape made of glass fiber rovings and a thermoplastic matrix is used as input material. These composite tapes are first formed with a pair of gears at elevated temperature to give them a three dimensional shape for weft insertion. The geometries of the gears depend on the configuration of the final panels. Secondly, the composite tapes prepared in this way are further processed on the weaving machine and spacer fabrics are fabricated. Finally, the spacer fabric is consolidated with a thermoset or thermoplastic matrix to form the final panel. A meso-scale finite element model based on shell elements is developed and used for the simulation of the panel manufacturing process and the structural behavior of the panels.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"17 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120992264","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.2021.042
Pieter Hofman, Lu Ke, Frans P. van der Meer
A common choice for multiscale modelling of the mechanical response of composites is to use periodic boundary conditions (PBCs) on square representative volume elements (RVEs). these PBCs over-constrain the response when strain localization takes place in bands that are not compatible with the imposed periodic constraints. PBCs periodicity the mapping matrix-fiber RVEs, of fibers cross edges, the of localization of circular RVEs with PBCs to obtain a micromodel with transversely isotropic response. the original formulation proposed in to the full softening response due to over-constraining when cracks reach the boundary. we propose a modification to the PBCs which allows for cracks to cross the edges.
{"title":"Circular Microstructural Volume Elements With Periodic Boundary Conditions for Localization Problems","authors":"Pieter Hofman, Lu Ke, Frans P. van der Meer","doi":"10.23967/composites.2021.042","DOIUrl":"https://doi.org/10.23967/composites.2021.042","url":null,"abstract":"A common choice for multiscale modelling of the mechanical response of composites is to use periodic boundary conditions (PBCs) on square representative volume elements (RVEs). these PBCs over-constrain the response when strain localization takes place in bands that are not compatible with the imposed periodic constraints. PBCs periodicity the mapping matrix-fiber RVEs, of fibers cross edges, the of localization of circular RVEs with PBCs to obtain a micromodel with transversely isotropic response. the original formulation proposed in to the full softening response due to over-constraining when cracks reach the boundary. we propose a modification to the PBCs which allows for cracks to cross the edges.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"52 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":"127876903","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.2021.040
L. Ke, F. van den Meer
{"title":"Multiscale Modeling of Composite Laminates Delamination via Computational Homogenization","authors":"L. Ke, F. van den Meer","doi":"10.23967/composites.2021.040","DOIUrl":"https://doi.org/10.23967/composites.2021.040","url":null,"abstract":"","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":"129187838","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.2021.056
M. Fagerstr¨om, G. Catalanotti, Wuyang Zhao, S. Pfaller
Partitioned-domain particle-continuum coupling methods can find a compromise between accuracy and computational cost by only treating regions of specific interest at atomistic resolution while considering the remaining region at continuum resolution. Most partitioned-domain methods are designed for crystalline materials and cannot be applied to polymer-based nanocomposites (PNCs) due to their amorphous structures and inelastic mechanical behavior. We present the Capriccio method as a particle-continuum coupling technique for PNCs based on [1], which introduces artificial anchor points in the bridging domain to communicate between the particle domain and the continuum. The Capriccio method was initially limited to small deformations within the elastic regime and has been recently extended to inelastic deformation by employing a viscoelastic-viscoplastic constitutive model for the continuum [2]. This extended Capriccio method is validated by comparing its averaged stress-strain curves to coarse-grained molecular dynamics simulations of glassy polystyrene under different loading conditions. In this presentation, we further investigate the advantages and limitations of the Capriccio method in multiscale simulations of glassy silica-polystyrene nanocomposites. In addition to averaged mechanical properties, the local stress and deformation in the vicinity of silica particles are also taken into account and compared to pure coarse-grained molecular dynamics simulations.
{"title":"Partitioned-domain Particle-continuum Coupling Methods for Simulations of Inelastic Amorphous Polymer-Based Nanocomposites","authors":"M. Fagerstr¨om, G. Catalanotti, Wuyang Zhao, S. Pfaller","doi":"10.23967/composites.2021.056","DOIUrl":"https://doi.org/10.23967/composites.2021.056","url":null,"abstract":"Partitioned-domain particle-continuum coupling methods can find a compromise between accuracy and computational cost by only treating regions of specific interest at atomistic resolution while considering the remaining region at continuum resolution. Most partitioned-domain methods are designed for crystalline materials and cannot be applied to polymer-based nanocomposites (PNCs) due to their amorphous structures and inelastic mechanical behavior. We present the Capriccio method as a particle-continuum coupling technique for PNCs based on [1], which introduces artificial anchor points in the bridging domain to communicate between the particle domain and the continuum. The Capriccio method was initially limited to small deformations within the elastic regime and has been recently extended to inelastic deformation by employing a viscoelastic-viscoplastic constitutive model for the continuum [2]. This extended Capriccio method is validated by comparing its averaged stress-strain curves to coarse-grained molecular dynamics simulations of glassy polystyrene under different loading conditions. In this presentation, we further investigate the advantages and limitations of the Capriccio method in multiscale simulations of glassy silica-polystyrene nanocomposites. In addition to averaged mechanical properties, the local stress and deformation in the vicinity of silica particles are also taken into account and compared to pure coarse-grained molecular dynamics simulations.","PeriodicalId":392595,"journal":{"name":"VIII Conference on Mechanical Response of Composites","volume":"8 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":"117023199","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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