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Found 83 results

  1. Dear forum members! I am new member of Altair community and I am trying to model composite laminate. I created some plies with difference patches and the visualization of the different layers made me little anxious. You can see the mentioned composite layers on the attached images. The plies are symmetric in the laminate nonetheless the 3D visualization of the composite showed differences between the upper and the lower side of the composite plate. I am afraid that this kind of modeling will lead poor results. I tried to change the type of the laminate from stack to symmetric but the result was the same. How can I model the composite properly if I want to "mirror" the top half of the composite plate to the mid-plane? Somewhere I read about sub-laminates but at first look seemed complicated. I would be happy if I could solve this modeling problem easier. Thanks your answers in advance! Have a nice day! Imre.F
  2. Hello there! At the moment i am modelling composite structure using solid elements (has to be solid elements only in my case), would like to know how could i define material orientation to my laminate layers, for example 0/60degree. There is some limitation on my model, since my model is in circular shape (please find the attachment) which means i need to define cylindrical co-ordinate system. I could not define material orientation directly by changing CORDM to be user and then add coordinate system in particular direction of angled ply as i used to do with rectangular plate (since i need to define 2 co-ordinate systems: cylindrical + 60 degree material orientation). I have tried with PCOMPLS-solid-shell approach but seems like not working in my case as i am performing thermal analysis using temperature card. Can someone suggest me how could i model this component in the way that 1. I need to model using solid elements only 2. There are 4 layers of plies -> 0/60/60/0
  3. Good morning, I'm trying to change the material orientation in a component. I tried in different way to do the 3D mesh and I tried to use different properties. The geometry is a simple hollow cylinder. I'm using Hypermesh 2017.3. The material is defined as MAT9ORT. To check the material orientation I used Analysis->Systems->Material Orientation. Mesh methods: Method 1: 3D mesh done by using Drag elements along the cylinder axis. The material orientation is along the plane perpendicular to the cylinder axis; Method 2: 3D mesh by using 3D->Element Offset->Solid Layers. The material orientation is along the cylinder axis; Method 3: 3d mesh by converting a ply laminates using the Aerospace tool "Shell to Solid". The material orientation respected the orientation angle given during the plies creation. These material orientations remain valid only without any property assigned. When I assign a property, the orientation changes without an apparent logic. Properties: Prop. 1: PCOMPLS: modifying the THETA angle in the property card didn't cause any modification in the material orientation; Prop. 2: PSOLID: when assigned to the component, the material orientation change the direction randomly and doesn't respond to any modifications with material orientation tool.
  4. Hey Guys! I've just wondering, it is useful to apply second order element for composite in Hypermesh using Optistruct as a solver? I think the composite theories use pretty much linear approximation between layers that's why I'm asking this "silly" question. Thanks for answers in advance! Have a nice day, Imre ps.: if you have any good tutorial, books etc. for composite modeling I would be grateful if you can share with me! :)
  5. 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
  6. 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?
  7. 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).
  8. 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
  9. 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
  10. 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
  11. 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)
  12. For thick-walled composite pressure vessels, solid modelling has been added to ESAComp's existing shell analysis module for thin-walled CPVs. The videos in this playlist form a tutorial that describes the modelling approach and workflow in detail. Check-out "Solid CPV Modelling with ESAComp & ComposicaD" now available here -> http://www.altair.com/ResourceLibrary.aspx?translation_id=7541
  13. 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.
  14. 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
  15. 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?
  16. Hi, I am a new user to Hyperworks. I am trying to analyse and optimize a composite monocoque chassis. I haven't gotten to the optimization part yet as I'm stuck trying to even run the analysis. Every time I try to run the analysis I get the following error: *** ERROR 14: Missing MAT # 3 referenced by PLY # 3, (existing MAT with this ID is of incorrect type). *** ERROR 14: Missing MAT # 3 referenced by PLY # 8, (existing MAT with this ID is of incorrect type). What I have done is that I have a symmetric stack of 2 layers of carbon fiber, aluminium honeycomb and 2 layers of carbon fiber. I have defined carbon fiber as MAT 8 and the honeycomb as MAT9ORT. The property I have specified for the geometry is PCOMPP. I have added pin joints to the rear suspension and a torsional load at the front suspension. I understand that another thread has been posted about this but I don't understand what the replies are telling me to do. Any help would be appreciated.
  17. Hello, currently i am writing Master Thesis about homogenization of composite material and i would like to make a simulation of behaviour of RVE in HyperMesh (solver OptiStruct). In this forum i found information that i should use PERBC card but i can't find this card in student version (i have 2017 and 14 version). Does somebody have tutorial how to use PERBC card or is it possible to apply periodic boundary condition in student edition without this card? I make dof=0 in normal direction on three face and i want to make opposite faces flat and parallel to blocked faces. I have 3d model with tetra mesh. model.tif
  18. Hey there , Thanks for your helpful answers in my previous topic and i really appreciate it . Now i should make the torsion stiffness test on my monocoque sandwich structure but as its an stp assembly file i have problems with the meshes and the contacts so if i make a solid map mesh some errors occur (as it says that parts of the assembly can't accept solid meshing) and when i applied tetra mesh the load doesn't be distributed to the other parts of the assembly so whats your advice concerning the type of the mesh that is should be applied to identify the contacts , i heard about RBE3 elements also but i don't find a tutorial on it and if it could be helpful in that case ?! Thanks
  19. Hi, I created a study where I want to analyse the effects of varying plythickness and plyangle of a carbon plate. I defined plythickness and plyangle of every ply as design variable (parameterized file) and then created a DoE. Now i got problems with the response. I dont want to see the composite stress for each Element as itself, but for each ply to have a better overview of the effects. Is there a possibility of filtering my response? By defining my response, I can select the element which is evaluated regarding composite stress. I exactly need the same for selecting a whole ply. Thanks for your support. Regards
  20. 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
  21. 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
  22. 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
  23. Hi there, i ran an composite optimization in Optistruct and now i want to analyse if the Geometry fails in RADIOSS because the Failure Criterion (PUCK) isn't available in optistruct. Anybody knows how to do that?
  24. 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
  25. hello community i want to simulate composite Forming with independent layers modeling with resin. i found in the forum this training support ,but i don't found the other parts of the training. the training support refers to the file " bwrap_independant_layers_resin_initial.hf" as in the picture i would be very grateful if you could help me to find this file it well be agerat help . Best regards. SAIDI Amine HF_Training_Composite_Forming_EN.pdf
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