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Found 81 results

  1. 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.
  2. 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! :)
  3. 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
  4. 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?
  5. 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).
  6. 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.
  7. 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
  8. 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
  9. 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
  10. 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?
  11. 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
  12. 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?
  13. 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
  14. 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
  15. 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
  16. 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
  17. 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.
  18. 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
  19. 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
  20. 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
  21. 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)
  22. 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
  23. 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.
  24. 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.
  25. 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
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