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Found 79 results

  1. Hello, I attached the .FEM file of the optimization I want tot run. I don't know what's going wrong, anyone can help me out? Meshed+Laminated.fem
  2. Hello, As far as I know its only possible to assign a single direction to a composite ply. However, lots of plies used in the composite industry are not unidirectional. For example a 0-90 ply. In this ply half of the fibres has direction 0 and the other half 90 degrees. How can I mimic this in Hyperworks/optistruct for an FEA?
  3. Im trying to model a simple plate structure with Carbon fiber reinforced epoxy (CFRE) as the material. This is the first time Im modelling composite so Im trying to get the idea. As far as I know, I need to use MAT8 for material properties. What are the properties that are crucially needed to key in the MAT8 card for normal mode analysis? For modelling, Im going to use 16 layers of carbon fibre fabric and epoxy as the matrix. When modelling the ply, each ply will be model as the composite of CFRE (16 plys of CFRE) or the ply need to be model seperately like carbon fiber and the matrix (16 plys carbon fiber and ply between the fiber for epoxy).
  4. Hi For composite free size optimization, does it matter what thickness we use for initial ply definition, i.e. when we first define the ply in hypermesh, does it matter what thickness we put there? or we should have to use the actual ply thickness we want to manufacture. I am not talking about manufacturing constraints.
  5. Hello all , I have created a laminate with around 28 plys and now I want to reflect the laminate and also the plys, what is the best way to do it? Thanks
  6. Hi. I want to be compare the composite analysis and contact surface (freeze) the example is above picture. And I want to check the ERP between 0~3000Hz. and I can get the follow this. (damping material density is 1856.07kg/m^3) The blue line is contact surface(freeze) model, The black line is composite model. why the blue line is more big value than black line abouy twice. why the blue line is more big value than black line. I want to know why two lines are different exactly. contact_al_dam.fem contact_al_dam.pch compostie_test_revised.fem compostie_test_revised.pch
  7. AlessandroC

    Composite sandwich panel

    Hi to everyone, I would like to produce a crash between a composite sandwich panel and a fixed cylindrical rigid wall. The first one is made of three different materials defined as LAW25 (COMPSH), plies as Type19 and laminate panel as P17_stack. Unfortunately something do not work properly. Can anyone help me to understand where I made mistakes? composite_panel_radioss_0000.rad result.mvw
  8. All three solid (visualization) laminates are overlapping each other. Is that a problem if we do analysis as per below laminates design? please tell me the possible step to make it good? below model is a metal composite sandwich......... what connection we have to made to join it?
  9. Hello, I’ve the task to build a ply-based solid composite model. The tricky part is, I have to build the model out of plies, which are drawn in Catia Shape Design (see picture 1). Why do I want to model each layer as a solid (ply-based solid composite model)? First reason, the composite part is used in a load introduction area. From the literature, a solid design is recommended. Second reason, I want to make use of Altair MultiScale Designer (MSD). In Optistruct only solid elements are currently supported with user materials. Therefore I use MAT9ORT as material. In the last step I replace the material information with an user defined material (woven 5 harness satin), which I get from the MultiScale Designer (MSD). Why is the composite part drawn in Catia Shape Design? Since the design of the composite part is complex at many points, Catia Composite Design (CPD) couldn’t be used for that. Instead the whole composite part is drawn in Catia Shape Design. Each layer (=ply) is drawn individually. So the geometrical informations I get from the CAD model are correct. But I have to work with this model and cannot rebuild it in CPD. What I've tried so far: I loaded each layer into Hypermesh and meshed the components (automesh, quads only). Then I created the materials (MAT9ORT), the plies (PLY01, ...), a laminat stacking and properties. Last I would do a shell to solid conversion. (see picture 2) Problems and questions: The layers don’t know each other. So the mesh of each layer is different. (see picture 3) Moreover in the thickness direction of the plies, they are not really connected. (see picture 3) Can you help me to find a strategy to build up the laminate out of the shapes I have from Catia? Since I’m an unexperianced HM user, I kindly ask you to explain your help and instructions in detail. Thanks a lot! My software: Hypermesh 2017.2 OptiStruct as Solver Multiscale Desinger 3.4 for the user material Catia V5
  10. Does anyone know how composite and aluminum connects each other with hi-lock? I try to connect by choosing spots>>type>>Hilock, but it cannot realized. For aluminum- aluminum connection with hilock, there is no problem. There is a problem when composite-aluminum connection with hilock. When composite connect with RBE2 element to aluminum, it works. However, I need modelling the connections as hilock etc. I also try rbe3-cbush-rbe3 connectors, but it doesn't work, doesn't connect composite&aluminum. What kind of connector( similar hilock) can I use for composite-aluminum connection?
  11. Dario Alonso

    DYREL CARD and MODEL VALIDATION

    Good evening, I am making a Formula SAE impact attenuator simulation. It is make with carbon fiber prepreg. For the model we are using material LAW 25 (CRASURV) and property 17 (stack). To calibrate material parameters and boundary conditions we are simulating an small plate. During the impact we obserb a shock wave that brakes the plate wherever and not row by row. We are trying to include something to damp or relax the material avoiding the shock wave. However, when we use the control cad /DYREL the model stops and kinectic energy evolve to cero. Parameters used on /DYREL are relaxation factor = 1 (default) and period (6e-5). We obtain period following indications of this text (https://insider.altairhyperworks.com/wp-content/uploads/2012/01/DynamicRelaxation_1201.docx). Where is our mistake? What can we try to solve it? Moreover, we create a model to compare with a test made in our center 2 years ago. Real part have a maximum of 10 plies. To obtain the same results on our hypermesh model we have to use more than 70 plies. We have asked Altair Spain and they don't see any mistake on the model (Attached you can find the model) and recomend us to ask on the forum. Real test results were positive and the impact attenuator resist impact and there was 16 cm without brake. On the model the impact totaly brakes and can't stop the 300 Kg rigid body used to simulate the car. Thank you for your help modelo ingenia SI.hm
  12. Amasker

    Composite Failure

    Hi, I made a simple optimization - about composite optimization and steel plate size optimization, the following is the input file, the result shows FEASIBLE DESIGN (ALL CONSTRAINTS SATISFIED). But when viewing the contour image, it is found that the partial area of the composite is invalid, the composite failure index greater than 1,does it mean that Optimizing the design is not feasible, Can someone give some advice?Thanks in advance。 B.FS.355.fem
  13. Hey everybody! I've just tried HyperLaminate modul in HyperMesh and found that it can calculate the stiffness of a composite laminate, the [A] [D] matrices etc. as you can see on the attached images. Is there any tool which represent the stiffness of the laminate in polar chart? I think Ansys is capable of doing it, but I could not find this function in HyperWorks. Thank you for your answers! Kind regards, Imre
  14. Hi, 1. Is the material orientation of each ply the same? I assigned different material orientations to each ply, but I cannot get the expected material orientations. 2. How to assign material orientation to elements with ply (fiber) direction? I try to assign the material orientation to plies with the cooridinate systems each ply used in drapping operations. But I found the obtained material orientation is not coincident with the ply direction. The attached pictures are the results of this test (for example, the directions in face A). I want to get the same directions, but I don't know how to do. Material_Direction_of_Ply.hm
  15. I'm planning to use PSOLID element for a 3D composite model, but I'm stuck with how to put thickness, orientation and Failure theory. Please tell me how to go about this. Thanks.
  16. marta

    Radioss - Fabric

    Hi everyone, could someone help me with composites simulation? I'd like to understand the difference between material law 25 and 58 to make the better choice for my simulation: in attach the data sheet of the material. If someone have theoretical and pratical (tutorial) material could shear it? Many thanks in advance Marta Tepex_Dynalite __102RG600__PA.pdf
  17. Dear Experts, I'm new to Hypermesh and need some advice on the meshing in it. I'm trying to model a composite unit cell. I have the yarns and their geometry from an external software in an *.stp format but I need to fill the domain with 3D elements which can act as a matrix of the composite. How can I perform this action in Hypermesh? I have tried booleans but they fail due to contact between the yarns at intersections. If booleans can be used, can you please tell me how can I improve it. Kind Regards 3S.stp
  18. Sascha Pazour

    Top Use Cases

    Saving Material Without Performance Loss Challenge Reducing the weight without loss of usability and strength Optimizing the manufacturing process Solution Injection molding simulation to optimize the part production and to create the fiber orientation for the new designed part Taking into account these results to perform most realistic mechanical simulation Results Significant material and cost savings due to optimized geometry Faster and more economic production process
  19. akshay325

    *** ERROR # 1807 ***

    Im getting the following error when i tried to put composite shaft with constrains Mass, and Composite Failure Upperbound 1. The Objective Function is Min Compliance. *** ERROR # 1807 *** Composite failure responses are applied to ply 9 which belongs to a topology or free-size domain. Help needed, Thank you
  20. Hi, I am currently trying to do composite optimisation of a carbon fibre sandwich structure monocoque. I have been following the "composite optimisation of a formula student monocoque" tutorial on the Altair university training website and am up to the shuffling stage however am not getting any results and getting this message: *** WARNING # 1569 for element id = -70001. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70002. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70003. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70004. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70005. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70006. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70007. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70008. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70009. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** WARNING # 1569 for element id = -70010. Thickness is zero for this composite. This will produce meaningless stress results and may cause singularity of the global stiffness matrix. *** More of WARNING messages # 1569 were suppressed... thanks in advance for any advice. Toby
  21. Hello,Forums I am doing analysis of a unique CFRP pipe by Optistruct. I am receiving this following error message: *** ERROR # 605 *** Element 1 is referenced by STACK 1 (on PLY 1) and by STACK 2 (on PLY 5) simultaneously. Different stacks are created by dividing the upper and lower areas of the pipe into sets. There seems to be an error because it refers to the same element Is there any good way to do it? (Modeling is possible but analysis is error) CFRP-PIPE-Asymmetric laminated.hm
  22. We are trying to analyze composite PIPE. When creating a cylinder surface and simply creating Piles and Laminates, it is stacked with the surface as an intermediate plane as shown in the attached image. (Cylindrical surface is white line) For example, are there methods such as stacking layers from the outermost layer toward the inside? (I do not want to change the diameter of the cylinder)
  23. Hi, I must model a tensile sample of composite material which consist of 3 layers of aluminium and 2 layers of fiberglass and each layer is linked by an adhesive. My problem is to model interfaces between layers, I have been advised to use gap elements to do it. Thus, on my geometry, even if layers are actually in contact, I let a small distance between them so that when I do my 2D-meshing the software does not consider them as one body and generate common grids between the two. Then I generated gap elements with the "nodes-elems" option, it creates gaps between the nodes of each mesh and also 1D-elements on 2D-elements I selected. These gaps are stocked in a new component with a PGAP property where I set U0=0.0 (initial gap opening); KA_opts selected option : auto; and MU1_opts selected option : Stick. The analysis I want to do is about a tensile test so I fixed one extremity of the sample and I applied a force along y-direction on the other. When I run the solver and observe results on Hyperview, these are not satisfying : it seems that gaps are useless and I obtain the exact same results when I delete them completely, all layers react independently from each other. As I did my analysis without a huge number of elements, I tried to redefine gaps using the "node-node" option and link all the nodes with each other, but the results are even worse : there are huge displacement along z-direction (near 30mm with a sample length of 200mm) while the force is along y-direction, plus displacement along x-direction is not consistent either. However gaps seem to keep layers stuck with each other. Could you tell me if gap elements are really adapted to my case please. And what do I have to do to implement them well. Thank you
  24. Hi there, my problem is as followes: i built up a squarish composite plate (carbon) with orthotropic material property. I edited the laminate with "symmetric" option to realize the orthotropic material behave. Now my problem is that I want to check the material behave varying ply direction and ply thickness. So the plate should obtain 10 mm height on the left edge and 9 mm on the right edge to simulate an angular load initiation, Now the symmetric laminate option causes a result which I dont want to realize (see attachment). Can you tell me how to realize that? Maybe with shell to solid conversion (how do i get there?)? Regards
  25. Hello, I have a laminate with 3 plies. I want to optimise the orientation of these plies such that the deflection of the laminate is minimum under the applied load. I can only perform composite shuffle, but I'm not able to optimise the ply angles. Please advice as to how to proceed to solve this issue Thanks, Kushal.
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