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Simcenter 3D Laminate Composites Exchange to Communicate with Randomly Oriented Short Fibers, Enables You to Attach Your Laminates Composites Designers

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Simcenter 3D Laminate Composites Exchange to Communicate with Randomly Oriented Short Fibers, Enables You to Attach Your Laminates Composites Designers Simcenter 3D Laminate Composites You can quickly define complex layups by importing them from Microsoft Excel or by using shorthand notation. Ply-based modeling You can use Simcenter 3D Laminate Modeling and simulating composite structures Composites to create global plies, assign them to polygon faces and/or 2D elements and define ply orientations by Benefits Summary projection of the material orientation or • Reduce laminate model creation time Simcenter™ 3D Laminate Composites by using one of the draping algorithms. by choosing between zone-based software is a modular Simcenter 3D Simcenter 3D automatically computes modeling, ply-based modeling or a simulation toolset for laminate compos- element zones for solver export. You mixture of both approaches ite structures. Easy-to-use ply and can assign different layup offsets on laminate definition tools enable you to different faces and view the fiber orien- • Leverage Simcenter 3D‘s open solver quickly create finite element models tations on the 2D meshes. architecture to perform state-of-the- representing your laminate composite art dynamic, nonlinear, progressive design. Simcenter 3D Laminate failure and delamination simulations Composites helps you create, optimize • Keep your model up-to-date with and validate composite structures using the latest design through geometry Simcenter™ Nastran®, Simcenter associativity Samcef™, MSC Nastran, ANSYS, Abaqus or LS-DYNA as your solver. Laminate • Interact with CAD-based composites Post Reporting generates graphical and definitions from Fibersim™ software, spreadsheet ply results from shell stress CATIA and others resultants and envelopes ply stresses, • Use Simcenter Nastran standard strains and failure metrics on elements materials, or create ply materials and over multiple loads cases. from the constituent fiber and Fibersim interaction matrix material properties to simulate Zone-based modeling Use the bi-directional Fibersim ply plies made of woven, unidirectional, Simcenter 3D Laminate Composites exchange to communicate with randomly oriented short fibers, enables you to attach your laminates composites designers. Plies can be particulates, and to represent cores directly to 2D or 3D mesh collectors. imported directly from the Simcenter An interactive graphical modeler helps • Conveniently assign laminates and .prt file, or via an HDF5 file. You can you to create and stack laminated plies to your choice of geometry, also exchange zone and laminate defini- composite plies efficiently. You can meshes and/or elements tions via the zone interfaces. use standard pre-defined stacking • Improve finite element modeling sequences and/or ply groups to mini- Interface with other tools accuracy by accounting for distorted mize the effort required to create and Import ply definitions from third-party fiber orientations modify complex, multi-ply laminates. tools such as CATIA, Patran Laminate • Post-processing tools allow you to Modeler and Simulayt Laminate Tools. quickly identify critical plies and load cases using classical and user-defined failure theories, and to create reports siemens.com/plm/simcenter3d SIMCENTER Simcenter 3D Laminate Composites Draping Simcenter 3D Laminate Composites draping algo rithms predict the fiber orientations and shear of unidirectional and woven plies as they drape around doubly-curved or undevelopable sur- faces. Simcenter 3D enables you to specify a draping start point and an initial draping direction, or to pick a seed curve. You can then coarsen or refine the drape mesh size and view the ply flat pattern. Ply materials You can combine fiber and matrix properties to create ply materials, which can be used in the laminate stack just like standard Simcenter 3D materials. Microme chanics theories allow you to create ply materials with the following types of fibers: • Unidirectional • Woven (you can specify the angle between the warp and weft fibers) • Particulate • Randomly oriented short fiber A core ply material allows you to define 3D layup inflation Dynamic simulation thickness-dependent shear stress limits. Simcenter 3D Laminate Composites’ Use Simcenter Nastran, Simcenter 3D 3D Inflation tool automatically creates Response Dynamics and the Simcenter detailed, solid laminate models that 3D Laminate Composites dynamics were previously too tedious to attempt. meta-solution to generate ply results for You can extrude normal to a 2D mesh dynamic events. The dynamics metaso- or by filling the volume between 2D lution uses advanced algorithms and a dependent meshes. You can taper core parallelized solver to efficiently com- or filler plies. A dedicated sandwich pute ply stresses, strains, failure indices, panel capability allows the automatic strength ratios and margins of safety for generation of 2D or 3D facesheet plies base-driven random and harmonic along with a user-defined number of events. solid element layers for the core. Cohesive elements can be introduced between selected plies, for assessment of delamination using Samcef. SIMCENTER You can apply loads and temperatures Optimization to your laminate and review the ply Simcenter 3D laminate optimization stresses, strains, failure indices and allows you to improve the fundamental margins of safety. properties of your laminate. You can optimize a laminate physical property to Failure theories meet stiffness, stability, strength or Simcenter 3D Laminate Composites mass objectives. A genetic optimizer computes failure metrics from ply handles continuous variables such as an stresses and strains, using the following orientation angle and ply thickness, as failure theories: well as discrete variables such as the existence of a ply, ply material, thick- • Maximum stress ness and orientation. The software • Maximum strain provides five laminate definitions that • Hill come the closest to meeting the objec- • Hoffman tives. You can select one of the five to Laminate validation replace the original laminate. • Tsai-Wu To visually validate your laminate, you In addition, your continuous thickness can view the thickness and the offsets • Puck and orientation design variables can be (both nodal and reference plane • LaRC02 exported as modeling objects and used location) of your laminate physical • Von Mises to define Simcenter Nastran Solution properties and your layups. Contour • Core shear 200 design optimization studies. plots of laminate thickness are also possible, helping you visually under- • User-defined first ply failure stand your model. • User-defined progressive You also can view the element zones failure with Abaqus and assigned laminate property, as well as create element groups from those zones to more easily manage your FE model. Laminate stiffness matrices (A, B, D and S) can be displayed in both Microsoft Excel and text formats. Similarly, equivalent engineering con- stants can also be displayed, enabling you to assess the characteristics of your laminate prior to solution. SIMCENTER Solver support Postprocessing You can assign laminates to shell or Simcenter 3D postprocessing allows solid elements, which then can be used you to view shell stress resultants, ply for the following supported solvers. stresses, ply strains, ply failure indices (ply and bond) and ply strength ratios Nastran (ply and bond). • PCOMP/PCOMPG/PSHELL Simcenter 3D Laminate Composites • PCOMPS/PSOLID provides enveloping, filtering and sorting tools that enable you to quickly • 2D: CQUAD4/R/8, CTRIA3/R/6 identify the critical element and ply • 3D: CHEXA, CPENTA over many solutions, including imported results. Simcenter 3D reads Samcef solver shell stress resultants and/or ply • 2D: Mindlin Shell (T28, T29), stresses, and computes ply strains, Heterosis Shell (T155,T156), stresses, ply failure indices and margins Membrane (T57, T58), Membrane of safety. It then graphically displays Shell (T53), Thermal membrane the critical ply ID for each element. (T34, T35) Simcenter 3D Laminate Composites also • 3D: Solid (T8, T46), Solid Shell computes core ply transverse shear (T153, T154), Cohesive Element failure indices, strength ratios and (T145, T147), Non local element margins of safety using allowable shear (T182, T183), Thermal solid (T039) stresses in the 23 and 13 directions. Simcenter 3D graphical post reporting ANSYS uses the laminate properties in your • 2D: SHELL181, SHELL281, SHELL99, active FEM, so that you can switch SHELL91, SOLSH190 failure theories and even modify your • 3D: SOLID186, SOLID191, SOLSH190 laminates after the solution to perform what-if analyses. Reporting will update Abaqus draping and zones if required, prior to • 2D: S8R, S8R5, S4, S4R, S4R5, STRI65, accessing results. S3, S3R, STRI3 To speed reporting for multiple or large • 3D: SC6R, SC8R, C3D8, C3D8H, solution files, you can use Quick Post Siemens Digital Industries Software C3D8R, C3D8RH, C3D8I, C3D8IH, reporting, which does not query the siemens.com/plm C3D20, C3D20H, C3D20R and active FE model. C3D20RH Americas +1 314 264 8499 Europe +44 (0) 1276 413200 LS-DYNA Asia-Pacific +852 2230 3333 • 2D: ELEMENT_SHELL, PART_COMPOSITE • 3D: ELEMENT_TSHELL Restricted © Siemens 2019. Siemens and the Siemens logo are registered trademarks of Siemens AG. Femap, Fibersim, HEEDS, Simcenter, Simcenter 3D, Simcenter Amesim, Simcenter FLOEFD, Simcenter Flomaster, Simcenter Flotherm, Simcenter MAGNET, Simcenter Motorsolve, Simcenter Samcef, Simcenter SCADAS, Simcenter STAR- CCM+, Simcenter Soundbrush, Simcenter Sound Camera, Simcenter Testlab, Simcenter Testxpress and STAR-CD are trademarks or registered trademarks of Siemens Product Lifecycle Management Software Inc. or its subsidiaries or affiliates in the United States and in other countries.Nastran is a registered trademark of the National Aeronautics and Space Administration. Microsoft and Microsoft Excel are registered trademarks of Microsoft Corporation. All other trademarks, registered trademarks or service marks belong to their respective holders. 10651-C10 5/19 C.
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