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Found 18 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, 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
  3. 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
  4. Hi, i built a model with Laminates, so how can i see my stresses in the plies. I want to know my stress in the facesheets and the honeycomb plie. Thanks for answering, hubéry10
  5. Hi, i built my model in hypermesch with shell elements, this elements have a PCOMP property with three layers. So how can I simulate wheter the Shell elements are safe or fail? I found a Website http://altairatc.com/europe/EHTC2011-Abstracts/EHTC-Presentations-2011/Session_12/AgustaWestland_presentation.pdf and there they talk about a Skript called HM_PE.tcl. So where can i find this Skript or is there any other Analysis i can make? Kind regards
  6. Hi, i have a problem regarding the correct visualization and therefore results of my model. I have a wheel model which is going to be made of carbon fiber. It is kind of an T-shape, but not really, see following screenshots. After creating the laminate, the curved surfaces intersect even though I am using the interface laminate feature with two sublaminates. The element normals of the blue surface face in the y-direction, the element normals of the yellow surface and vertical surface face in the -y-direction. The interface laminate feature works on the middle, vertical surface of the wheel, but you can also see that the laminates of the shells intersect while the vertical surface works properly. This is why I have a sharp step in the front of the wheel and a less sharp step in the back of the wheel and it looks like the plies are interrupted. So I would like not to have those steps or intersection plies but instead a smooth transition from the shells to the vertical surface as it is in the 2D model. I attached many pictures so it is better to explain and imaginable. Also I considered that i have to choose the interface plies with regard to the element normals: Pleas let me know if you have further questions to this problem. I also found different forum posts but they do not help me because they are more like real T shapes where as mine is not. Thanks in advance!
  7. Hello again, since I have not received any answer, I have to repost this. I got a problem with my plies. I got a flange in my model where two face meet each other and combine to one. I want to use only one laminate, but I don't know how I can realize it. As you see in the picture, the plies are stacked only in direction of the normal. I got three faces, which I combined to sets: Inside (left side of the picture), outside (right side of the picture) and the flange. As elements for the plies I chose inside + flange on one hand, on the otherside I chose outside + flange meaning the flange should have the exact same structure as the inside and outside face, there should only be a 90 degree ply (dark blue) dividing them. I only want to use one laminate and one property. Is there any possibility to realize that? I tried to change it with the normals and z0 options, but it did not work. I hope I could explain it in an understandable way. If you need any other informations, please ask. Kind regards, Konstantin Heiss
  8. Hello all, I had a look in the forum but I could locate anything specifying the contents or the form of the excel file required in order to import (not export!) the ply layup when creating a laminate in Hypermesh. Could you please provide an example file? Thank you.
  9. Attached are 2 Hypermesh models. The Aim is to minimize mass. I have used 2 composite plies to model the structure. 2 PCOMPG properties have been assigned to the plies respectively. Only 1 out of these 2 plies needs to be optimized topographically to obtain stiffener patterns. The other ply must continue to remain in its original shape In the “volume_feasible.hm” file , I have minimized volume as the objective. The optimization run gives a feasible design. However, when I check the results, there is no change in the shape of the ply and no bead patterns are obtained. Next, I changed the objective to minimize mass just to see if I get the desired result. Again, I obtain a feasible design but there is no change in the shape of the ply and no bead patterns are obtained. In this model, no contact has been defined between the plies. In the “stick_contact.hm” file, I’ve defined a stick contact between the two plies and run the optimization. Here again, I obtain a feasible design but there are no bead patterns obtained in the result. if anyone has tried a similar problem before please help me out. stick_contact.hm volume_feasible.hm
  10. Hello, I got a problem with my plies. I got a flange in my model where two face meet each other and combine to one. I want only one laminate, but I don't know how I can realize it. As you see in the picture, the plies are stacked only in direction of the normal. I got three faces, which I combined to sets: Inside (left side of the picture), outside (right side of the picture) and the flange. As elements for the plies I chose inside + flange on one hand, on the otherside I chose outside + flange meaning the flange should have the exact same structure as the inside and outside face, there should only be a 90 degree ply (dark blue) dividing them. I only want to use one laminate and one property. Is there any possibility to realize that? I tried to change it with the normals and z0 options, but it did not work. I hope I could explain it in an understandable way. Kind regards, Konstantin
  11. Hi, How can I export the laminate to an Excel file? Or if it is not possible, exporting the plies would be also helpful. Thank you, aecyd
  12. 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?
  13. Hello, I am quite beginner in Hyperworks and I am currently modelling a laminate (HC panel) with different plies. Whenever I make a modification in the mesh, before running the calculation I need to re-open Ply card and specify elements that are included in each ply, because they are lost due to mesh (thus, element) modification. I am wondering if there is another way to specify plies, because it might be relatively annoying to update this part of the model each time a mesh modification is carried out; in this case, number of plies is not extrenely big, but it can happen that a model consists of many of them, leading to a high waste of time. For example, that instead of selecting elements which would be involved in a ply, surfaces could be selected. Any help would be helpful. Thanks in advance. Regards
  14. Hello, Currently I'm trying to optimize a composite laminate in optistruct. I have meshed the surface I use as shape. When I try to apply a pressure force on this surface the pressure is applied on both sides of the surface. This results in an displacement of 0 mm, ofcourse.... so: How can I apply a pressure force on a single side of a surface in Normal Direction?
  15. Hello everyone, quick question that Google did not give me an answer for and I am a Little pressed for time. I have surface an would like to apply a stacked Laminate on top of it, so that the surface is used as base for the Laminate. However, whatever Setting I use, the Laminate always turns out to be symmetric, to each side of the surface. I cannot possibly work with a symmetric Laminate as I have constraints regarding the size of my part. The surface marks the outermost surface of my part and thus cannot be exceeded by a Laminate. I have tried the STACK Option in the Laminate creation tool but this did not seem to help. Any help would be greatly apprechiated! Greetings, Lenny
  16. I have modelled a solid shaft in catia and imported igs file to hypermesh and mesh it , now i have add composite material to it and optimize it, please help me in detail
  17. Hallo everybody, I want to optimize a composite monocoque for a formula student car. For this I want to take a composite sandwich. But I still get errors, when I start the analysis. First I want to create a plate (275mm x 500mm) to look if it works like this. Here is what I have done so far: 1) load the CAD data in hyperworks 2) mesh the geometry with elementsize 4 3) create 2 materials. One for the cfk (MAT8) and one for the core (MAT9ORT) 4) create 2 properties. One PCOMPP for the laminates and one PSHELL for the core 5) create 5 plys. 2 for the inner layer, 2 for the outer layer and one for the core. Assign material, thickness and elements to the plys 6) create 3 sublaminate. One for the inner layer, one for the outer layer and one for the core 7) create a sublaminate with the 3 sublaminates 8) make a "solid to shell conversion" with laminate "core". Now there is a new component with an SOLID property. Assign material to the solid Property. (MAT9ORT) 9) assign PCOMPP property to the first component 10) create two loadcollectors for the force and for the constraint. Create a force in the middle of the plate and 4 constraints at the corners and then create a loadstep with these two loadcollectors. This is just a trial if the analysis works without failures 11) make a "GLOBAL_OUTPUT_REQUEST" with CSTRESS and CSRAIN 12) start analysis with Optistruct But everytime I start the analysis, I got an error. When I fix one error there comes another. Can you please help me to find my mistake? And can you tell whereon I have to pay attention on, when I want to make a Composite Sandwich with sublaminate and interface Laminate. Thank you for your responses. Regards
  18. Hi, I am working on a laminate optimization. I'd like to do the three phases: Free Size Optimization, Size Optimization and Shuffle Optimization mentioned in the composite manual. My question is how can I connect the element faces in the 3rd direction with other elements of different components. In the attached picture I would like to connect the yellow part with the different laminate layers. Are there any solutions available, I could not find equal problems in the composite manual. thank you in advance, Martin
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