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Found 89 results

  1. Hi, I'm trying to build a model in order to simulate a shear test on a composite panel with honeycomb core. I've been trying with non-linear static load-step but I get a non-convergent results and the error you can read in the .out file attached here. One possible solution I've tried, could be tuning the NCUT parameter in the NLADAPT collector, but this couldn't solve the problem and I get the same error. I'm also not sure about the type of analysis I've chosen and how I have modeled the physics of the problem, do you think a non-linear transient or explicit simulation could be more suitable for this kind of problem? I attach here my model and the .out file of the run, I'll really appreciate your help! Thank you. solver_deck_s1_e.out Model_1.hm
  2. Hello CAE Enthusiasts, Im currently trying to do a Free Size optimization on a composite model which is built on a ply based approach. After all, it seems that the Optimization is running fine. I got a feasible design after 7 Iterations and all constraints are satisfied. However, if i import my optimized FreeSize.fem into HyperWorks again the weight is off by 22.5 %. My optimization constraint is a weight of 600 grams. As a result I got roughly 735 gramms. The objective of this optimization is to minimize weightedCompliance. I tried several attempts to figure out what is wrong but i don`t get it. I would be glad if someone would get a hint or could take a look at the attached model. Thanks in advance. StaySafe and greeting from Germany. RW_SwanNec_SizeModel.hm RW_SwanNec_SizeModel.out
  3. Hi, by browsing the reference guide, i found that the CFAILURE card also theoretically should support solid elements referencing PCOMPLS or PSOLID with MAT9 for linear static analysis. However, i cant find any way of specifying additional material parameters e.g. yield limits for MAT9. The reason i would like to use this is that i'm modeling a part wich has a transition area from a thin shell, modeled with PCOMPP to a area that can't be modeled this way due to it's thickness. Therefore i would like to model this area as solid, either by using PCOMPLS or even preferrably PSOLID with MAT9. Is it even possible to calculate composite failure for those PSOLID elements, as specified in the reference guide The version i'm using is Hyperworks 2019 student edition. A sample of what i'm trying to acchieve (yellow: PCOMPP, red: PSOLID):
  4. Hello everyone, We are working on a car chassis for a University Project Team. Chassis is made from carbonfibre composites. We put together support parts and main chassis with using adhesives (like Pleksus). We are running structural analysis by using Hypermesh-Obtistruct. So here is the question, what is the proper way to model composite - adhesive - composite connections? I have tried adhesive connector, but it is just filling the gaps with rbe3s. I want to connect composite parts with adhesive that i have the mechanical properties. For better understanding, i am attaching two pictures, our past car chassis and a composite model to try adhesive connection. Thanks for your supports. Have a nice day.
  5. Hi all, I've got myself into a bit of a problem meshing a 'composite' part. I'm investigating the use of continuous fiber reinforced 3D printing as part of a project at Uni, where I'm using the Markforged 3D printer to specify fiber orientation etc for max stiffness/minimum weight. I have successfully simulated my basic tensile tests in ABAQUS but I'm now looking to use OptiStruct to optimise the lay-up of my design, which is a printed joint connecting two tubes at 90-deg angle with a flanged base for mounting. The design is unconventional for composites, ie not a thin shell where 2D elements can be used. I've done a few of the Hyperworks composites tutorials but none are representative of my problem so I'm looking for guidance on the meshing of the part. Being 3D printed, it is manufactured layer by layer, meaning the fibers are all parallel to the base plane, but the part has a complex geometry with different wall thicknesses, tapers etc. I reviewed using midsurfaces but I couldn't make any real progress with it. I know you can use the MAT9 for 3D composites but will this still enable me to optimise the laminate layups? I was maybe thinking of breaking down my model into each part i.e. base, stiffener and joint? I'm looking forward to hearing what people say - I'm fairly new to Hyperworks but I'm really enjoying learning it!!
  6. 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
  7. Dear everyone! I want to export my ply-based shell composite laminate from HyperMesh to a STEP or PARASOLID file. I used the following option: File>Export>Geometry Model My composite laminate can not be imported properly into Solidworks 2019. Tried a lot of options but I could not reach that the shell elements (and plies) had the proper thickness. In Solidworks there was only a surface without thickness. I would like to design a tool for manufacturing and I need the proper geometry of my composite part. Thanks for your answer in advance! Imre
  8. 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
  9. 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
  10. 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)
  11. 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
  12. 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.
  13. 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
  14. 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?
  15. 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.
  16. 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
  17. 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
  18. 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
  19. 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
  20. 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
  21. 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
  22. 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?
  23. 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
  24. 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
  25. 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
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