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    • Rahul Ponginan

      Please click here for a short but important announcement   03/26/17

      Dear Users Our Commercial and Academic users around the world can use these same forums here as before i.e. the Altair Support Forum , Commercial users from India with solver queries can go to the Solver Forum for India Commercial Users , Academic Users from India and AOC India Participants are requested to go to the Forum for India Academic Users and AOC India Participants , We will be tending to all queries in all the forums promptly as before, thank you for your understanding. 

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Found 33 results

  1. Im trying to model a solid honeycomb core with MAT28 and PROP6. I'm using a local coordinate System (/SKEW/FIX with Ip=0) to define material orientation. I tried to Change the local coordinate System but the solver always refers to the global coordinate System. A change of the local coordinate System does not affect a change of the material orientation therefore i'm not able to define the material orientation with a local coordinate system. Can anyone help me with this issue? Best regards
  2. Contact Forces split up

    Hi guys, I am currently trying to solve a problem with my 3 point bending setup. I designed a hybrid composite structure with 3D elemtents as core and 2D elems as Laminate. To apply the load I have modelled a 2D Impactor which moves down and translates the forces into the laminate via contacts. (MORIENT: Norm, S2S, TRACK: finite) Everything works fine exept my results... if I view the contact forces Optistruct would give me the result as shown in the picture. Has anyone had this problem before? I have already tried using CNTSTB and defining the SRCHDIS. Changing Master and Slave or N2S and S2S did not help either. At some values the two lines of contact forces would move closer to each other but never close enough. Greetings from Germany Lars
  3. Hello guys! I would like to find a possible method for simulating composites with non-linear material model. It's important for me to know the behavior of the material in the degradation phase, so after reaching the displacement in point A on the picture. I have to model the composite as shell, and have to use an implicit method. My question is that which solver with which property and material card combination is suitable for this analysis in Hyperworks? It is possible to use Optistruct to solve this matter? Thanks for your help in advance! Best regards, Tüki
  4. Error ID: 55

    Hello, I've been trying to set up a simple simulation of a carbon fiber cylinder crashing into a rigid wall. I've been getting an error (error ID 55) in input format that is related to either the property or loadcase. I believe the error lies with the property as I changed the loadcase multiple times (initial velocity to concentrated force etc.) and the error persists. The property being used is property 10: composite shell. The material being used is material 25: orthotropic shell. The 0000.out file is attached. Any ideas what I'm doing wrong? Any help would be much appreciated. Cylinder2_m_Try11_0000.out
  5. unable to solve ERROR # 605

    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
  6. 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
  7. 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
  8. 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
  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. KTex LayUp is dedicated to representing one of the composite materials manufacturing processes: the molding or RTM process. Its main objective is to automatically set-up a ready-to-run finite element model simulating this process. To do so, two input parameters are needed: the fabric and the mold. Some molds and fabrics are included in the tool database, but bespoke ones can also be created. A video regarding mold creation will come later. When selecting a fabric, two options are available: REV or Size/Shape. The REV option only needs the Representative Elementary Volume of the fabric. This REV is then duplicated and translated as many times as needed to be bigger than the mold. But the final geometry of the fabric to be molded will always be a square. The Size/Shape option needs the geometry of the fabric to be molded. This fabric can be a stack of several plies. It can feature several plies of different geometries, thicknesses or patterns... Anything is possible in order to represent the real plies that are to be molded. The user is free to define the fabric, but the user has to be careful as mistakes will not be detected. The attached video gives an example of the difference between the two options. KTexLayUp_REVvsSHAPE.mp4
  11. KTex Pattern overview

    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
  12. Composite structures all have joints, so their design and analysis is paramount to determining their overall performance. Therefore, ESAComp has comprehensive capabilities for both bonded and mechanical joints which are very efficient in the preliminary design of various joint configurations. Read more -> http://innovationintelligence.com/dont-come-unstuck-designing-structural-adhesive-bonds/ www.esacomp.com
  13. CSTRESS vs ELSTRESS

    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.
  14. 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.
  15. 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,
  16. Hi Optistruct users, I am currently working on a Formula Student Composites Chassis. My chief designer asks me to extract the CAD file from my composites optimization, in order to have right thicknesses everywhere in the chassis, and starting to place other elements around the chassis according to the FSAE rules. But I know that i'm working in 2D, and the only way to see my final laminate is to click on Element Representation. So basically, I am asking for advice on how to export my simulation into 3D CAD. Thanks for helping, Nicolas RICHTER
  17. Throughout JEC World show, come and see ESAComp in action with our engineers. With the launch of ESAComp 4.6, we'll show you the new capabilities, including Python scripting; enhanced panel analysis with shell modelled stiffeners... ESAComp now provides structural analysis of thick-walled pressure vessels from winding patterns imported from Composicad filament winding simulation. For HyperWorks users, ESAComp provides fully integrated solution for pre- and post-processing of composite structures, allowing ply-by-ply investigation of failure modes using advanced failure criteria. We're an active member of Altair Partner Alliance, find us together with Altair Engineering in Hall 5A on Stand N68
  18. Composites Optimization - FSTOSZ

    Hi, I am currently working on a composites optimization for the Formula Student Competition. Thanks to great tutorials for creating my model, I am now using the FSTOSZ output for my first optimization. When I open my new .fem file (which was created after my fstosz), I have 92 plies in total, and the most of it is under 0.05mm thick.... As far as I know, I have to reshape every plies, but what about thicknesses ? I tried to enter a TMANUF value (0.4mm for each carbon fiber ply), but I still observe that my plies are <0.05mm thick. For information, my laminate is the following : - 4 plies of 0.4mm carbon fiber (90,-45,45,0 orientation) - 1 ply of 20mm aramid honeycomb - 4 plies of 0.4mm carbon fiber (90,-45,45,0 orientation) --> Symmetric What am I supposed to do to complete the process of composites optimization ? Thanks for enlightening me. Best Regards, Nicolas RICHTER
  19. What is ESAComp ?

    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
  20. 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
  21. 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
  22. Hi, I am currently modelling a truss structure made up of carbon fiber composite tubes with the thickness of 1mm. I have created 1D CBAR elements as the input properties. Now the problem is with the creation of material properties. Any one have modeled previously composite tubes? Any inputs or suggestions would be helpful for me.. Thank you.
  23. Rim well optimization problems

    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
  24. 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
  25. Sandwich Analysis

    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
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