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Found 47 results

  1. Hi all, I'm facing a problem I can't fix. When I want to perform my dynamic analysis, I get 8769 errors like below : ERROR ID: 197 REFERENCE DIRECTION IS ALMOST NORMAL TO SHELL ID=54115 Could you please help me to fix it ? For confidential issues, I can't illustrate my model... Best regards, Raphael
  2. Dear colleagues, I am writting to you regarding an issue in the results i optained from a model of Composite Tensile specimens. I have model the specimens in hypermesh as a Composite based plate model and i applied the fully clamped BC in one side and a load in Y direction (with respect to global coredinate) in the other side. the model is run uner Optistruct solver with nonlinear static analysis without Problem but the results I optained are an unerealistic. The displacements are with very large Amplitude and in Z direction(the load is in Y direction ) ????. I have atteched the model with this request. can kindly check it and tell me what is wrong ??? Regards Kouider Model_Tensile.hm
  3. Hi, I've a problem with my 3PB model of a sandwich structure (honeycomb core). Contact between sandwich structure and supports isn't realistic. I set contact in "SLIDE" but the result is wrong. So I obtained a displacement of 177 mm with a force of about 15000N, not real. I can't also view the results of CFAILURE, but I've set it in output requests. Can you take a look to my model? Thanks in advance. Hearing from you. Regards. 3PB_1.hm
  4. Hello, I am currently working on a project where I have to optimize the monocoque structure of a lightweight vehicle. The materials used are carbon fiber reinforced polymer and aramid fort the core. In some places, there have to be inserts so that for example the belt or the seating can be fixed. The goal of my task is to make a composite optimisation with Hypermesh/Optistruct for the monocoque and particularly the insert zones. On the picture below you can see the structure of the insert zone. First there is a sandwich-structure with layers of CFRP (A and C) and aramid (B), which forms the monocoque structure. Then I have the insert (E) which is glued on the top of the CFRP-layers (C). Another CFRP-Layers (D) are laminated on the top of the insert zone, except the threaded rod of the insert. I have some difficulties to simulate this structure on Hypermesh. Insofar as I have several layers (C) of CFRP between the aramid and the insert, the insert is merged in the CFRP layers (in the 2D detailled element representation). I want to have the insert (E) on the top of the last CFRP layer. Do I have to create a contact between the last CFRP layer and the insert? On the picture below you can see my problem (the D-Layers are not shown in this view). I have the same problem to put the CFRP layers (D) on the layers (E) at the places where there is no insert (around the insert). Thank you for any help, Eric
  5. Hi! I am trying to simulate, using hypermesh (optistruct), a 3 point bending test of a composite sandwich panel made of carbon fiber and aramid honeycomb. I have modelled the core using PSOLID property and MAT9ORT material and the skin where modelled using the tool "find faces", and then creating four CFK plies that form a laminate which is associated to the property PCOMPP that the skins have. I used MAT8 to define CFK plies. The Optistruct solver doesn't output any errors at all; however, when visualising the deformed shape, it represents an absolutely wrong and wierd shape for the sandwich panel where the supports are as shown in the attached picture (right and left side of the photo). I've tried to model it several times and even change some properties in case there was material failure in such points, but didn't work. I need help as soon as possible. Thank you!
  6. ESAComp is software for analysis and design of composites. Its scope ranges from conceptual and preliminary design of layered composite structures to analyses of details. ESAComp is a stand-alone software tool, but thanks to its ability to interface with widely used finite element software packages, ESAComp fits seamlessly into the design process. The comprehensive material database of ESAComp forms the basis for design studies. ESAComp has a vast set of analysis capabilities for solid/sandwich laminates and for micromechanical analyses. It further includes analysis tools for structural elements: flat and curved panels, stiffened panels, beams and columns, bonded and mechanical joints. ESAComp is developed and supported by Componeering Inc., Finland. www.esacomp.com or check out our Altair Partner page http://www.altairhyperworks.com/partner/ESAComp ESAComp-Intro.pdf
  7. Join us on either April 5th/6th/11th 2017 Presenters: Harri Katajisto & André Mönicke, Componeering Inc. To get an overview to the new capabilities of ESAComp 4.6, sign-up here to join our free webinars: http://www.esacomp.com/webinars/live Python scripting for batch runs and for creating user extensions Enhanced panel analysis with shell modelled stiffeners Structural analysis of thick-walled pressure vessels with solid FE modelling from winding patterns imported from ComposicaD filament winding simulation For HyperWorks users, an integrated solution for pre- and post-processing of composite structures, allowing ply-by-ply investigation of failure modes using advanced failure criteria The webinar takes appr. 45 minutes including a Questions & Answers session at the end.
  8. Hello guys, I am working on an Formula Student chassis. After my composites optimization, I have now a fully optimized thickness in my chassis. But now, I want to export my 2D meshing in CAD file. I saw previously the module "Shell to Solid Conversion", and tried to create a solid and an assigned PSOLID property. What should I do now ? Because when I tried to export my solid, an error occurs : "No supported entities present for Export". I also tried with OSSmooth, but I have no .sh file associated with my solid model... Thanks for helping ! Best Regards,
  9. The 4th European Altair Academic User Day on June 26th (during the European Altair Technology Conference, June 26th - 28th in Frankenthal Germany) provides students, teachers, professors and researchers across Europe to network and share their experiences with Altair’s CAE solutions. Join us to hear how ESAComp assists schools and universities offering composite engineering courses, both in the class room and for post-grad research. Register here -> http://www.altairatc.com/EventPage.aspx?event_id=89&name=Academic+Day+2017 ESAComp-EDU-06-2014.pdf
  10. Hello, I am trying to insert manually a drape table and then have it mapped into the elements. So far I have tried to make a SET of nodes (SET_GRID), and point the drape table to this SET, but it is only modifying the direction of one element. Actually, this is a simplyfied example, what I really need is, in a more complex surface, import points (with coordinates) and directions(with vectors) to indicate the plies' orientations. Is it possible? Drape_import.hm Thanks in advance, Rosa
  11. Hello, when I do my optimization now, I get strange results. I really don't know where my fault is. Another problem is, that I don't want to lose the no-material plies (see also: http://forum.altairhyperworks.com/index.php?/topic/18205-interface-laminate-error-640/#comment-35811 Because, when I optimize now, I only can constrain the balance between 45°- and -45°-plies. But it is important, that the plies with no real material and the ones with CFK-Material have the same thickness, so that it doesn't change the midsurface. How can I realize that? Because in the picture above, I have hidden the no-material plies. the plies changed their midsurf and the diameter of my model went bigger, which is not allowed. My other question is, how can I realize the plies to be continuously around the cylinder? I tried it with cyclic pattern grouping, but I am not sure if I used it right. For further explanations please ask. Thank you, Konstantin Felgenbett_Heiss1.hm
  12. I wish to do an impact analysis of the CRPF tube, I was just not able to understand how to do it in RADIOSS. I have used Hypermesh - Optistruct and I know about properties like PCOMP, PCOMPP. But I'm not sure what model setup should I use in RADIOSS. IMPACT_ANALYSIS_OF_CRPF_tube.pdf
  13. Dear, I am trying to preform a buckling analysis of a composite sandwich material. But the Auto-SPC limits the DOF's of the composite skins, so that buckling can not happen in correct way. When the Auto-SPC is dissabled, the solver gives the error which states that the DOF's of these elements should be limited, because they have no stiffness in that direction. This is true, due to the material and property assignment (Mat 8, and PCOMPP) which does not provide stiffness in the 3th direction. Is there a work around? I also did a dynamic test (Radioss) where the specimen does not buckle according to the first mode. Test to be replicated: Optistruct First mode Faulty result due to Auto SPC RADIOSS Result Model : Eigenvalue_Bucke_2.hm
  14. ESAComp has a proven track record as a useful resource to many educational establishments worldwide providing courses in composite materials. Here's what the professors have to say: http://www.esacomp.com/articles/57-talking-to-professors ESAComp-EDU-06-2014.pdf
  15. I can see layers option for Element stress and Composite Stress. But the values I get for both of them are completely different. Is it possible to know how the element stress and composite stress is calculated in Optistruct and in which coordinate system the results will be. I am looking for ply level stress in a given element. For ex: the extreme ply stress in a given element of 30 plies. I am trying to correlate the hypermesh results to results from my FEA numerical calculation.
  16. KTex Pattern is part of the KTex Family. It is launched from HyperMesh as a TCL script. It aims at building finite element (FE) models of any kind of weave (1D, 2D and 3D). To do so, some inputs are required, such as dimensions of the fibers, the desired weaving pattern, the material of the fibers, the type of elements to mesh the fibers and the desired size of weave. With all these parameters, a FE model of the weave is automatically generated and meshed. A database of many fiber cross sections is available, but bespoke cross sections can be generated. Fibers can be meshed with shell or solid elements. The user has the choice to generate only the Representative Elementary Volume of the weave, or to specify rectangular dimensions, or even to use a line created in HyperMesh in order to fill it with the described weave. A database of commercial weaves is available in the software but bespoke patterns can be generated. Several plies can be stacked on top of each other, mixing all the different possibilities of the software. An angle can be defined from one ply to the other. This gives the possibilityy to generate many kinds of stacks, potentially including patches. Attached is an overview video of the software capabilities. For more information, reply to this topic or contact support at : support_ktex@cedrem.fr KTexPattern_Overview_v2.mp4
  17. Hi everyone, I have to simulate an object made by thermoplastic composite laminate. I know that I have to do a model calibration with a fitting of experimental curves but I have a lot of doubts about the correct procedure. For exemple on the one element test I have to define laminate and plys or I have to use a single ply with laminate's thickness? Could anyone send me some material about composites model calibration? Thanks in advance. Marta
  18. Hello, I am receiving this following error message: ERROR # 605 Element 917177 is referenced by STACK 1 (on PLY 2) and by STACK 2 (on PLY 12) simultaneously. I looked at previous topics about this error message and checked the stacks to make sure the same ply is not used in both stack 1 and 2. But I am still having difficulty in finding and changing the ply property of the element in the error message. Does anyone know how I should proceed to solve this error? Thank you Muge
  19. Hi There , I'm engaged in the project of chassis design for a vehicle for the FSAE competition and i have to make the chassis with a sandwich (CFRP - Foam) material , since hyperworks (OPTISTRUCT) will help doing the analysis , i started making a plate and making plies with CFRP (MAT8) and PCOMPP card image then a Core(MAT1) with PSOLID property , also i make laminate with the plies . i applied the load with constrains then loadstep with both and i check CSTRAIN and CSTRESS Properties for the analysis but since i start the analysis there is no iterations made and only the one displacement result appear , i tried alot to change in the structure but still no iterations , Here is what i have and there is a copy of the hm file attached The Results Iteration Subcase Variable Grid/Elem ID Value --------------------------------------------------------- 0 1 MaxDisp 12205 -0.285887E-02 0 1 MaxStress 5725 -15.0120 The amount of memory allocated for the run is 331 MB. This run will use in-core processing in the solver. ANALYSIS COMPLETED. ==== End of solver screen output ==== ==== Job completed ==== Sandwich Foam.hm
  20. HI, I want to know what output request we need to call to see top and bottom stresses of each layer (PLY) of a laminate for composite plate simulation. Solver used is OPTISTRUCT Thanks,
  21. Dear, I am making a model of a carbon chassis in hypermesh. I apply my suspension loads at the suspension points. How can I make my model without using SPC's as my boundary condition? The only logic place to make use of the SPC is at the suspension pick up points. But I cannot fix these because then it becomes impossible to check if my laminate is strong enough. How can I apply boundary conditions without using SPC? Kind Regards,
  22. Good evening guys, I am trying to model a composite structure with delamination capabilities by using Prop/type17. Even though I am reading that it entails the capabilities of plyxfem and to determine interply material by the flag Mint_IDi . Those two flags are not visible. Does anyone has faced the same problem? Is there a chance that are not visible by my model setut of they should have been visible by default. I am attaching the respective file. Thx. plate_impactor_rigid_delamination.hm
  23. Dear All, I am trying to simulate a compression test of a composite ring. With NLQS analysis, the solution goes pretty good and somehow accurate, but with this type of analysis, I can't get the CSTRAI and CSTRESS and failure criteria (not supported using NLOUT). I tried with NLGEOM(implicit) analysis and is working but the results are not the expected ones (Although I can obtain the composite analysis that I wanted). I realize that there are some penetrations in the model that I thought was not there since I choose a z0 option = TOP. It could be possible, that the solver uses the real midsurface of the laminate and so he can detect some penetrations and affecting my simulation? See the attached pictures Pic 1. Z0 = TOP Pic2. Z0 = real (midsurface of laminate) Not sure if I consider the midsurface of the laminate (and leave the half thickness between the end surface of thickness and the blue plate) the results will not be correct ones. Thank you for your time
  24. Hi Everybody, I am trying to simulate the residual strain on different ply's of a laminate due to different rates of cooldown. I was planning to do this with a heat transfer analysis (transient) but I believe that composites are not supported in transient heat transfer. Is it possible to perform a sort of transient analysis applying a Delt Tº in the different time frame? I was thinking to do this with TLOAD1 with excited a TEMPD and a Table1 Is this approach correct? Thank you beforehand
  25. Attached is a Hypermesh deck of a structure whose mass I’m trying to minimize. The structure has a square shaped core covered on the top and bottom by composite facesheets. Shell elements have been used for modeling. The size of the square and the thickness of its wall determine the buckling characteristics of the facesheets. I’ve modeled using a square of side 6mm and its wall thickness is 1.5 mm (shown in the snapshot below). By varying the size of this square and changing the wall thickness, I’m looking to minimse the mass, the constraint being that the buckling factor must always be greater than 1. Could you please help me achieve my objective? Thanks, Kushal Agarwal. square_foam_opti.hm
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