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Found 10 results

  1. Hello, for my Formula Student Team I am trying to simulate the deformation of the Anti Intrusion Plate. To replicate the real test I've tried to implement the Honeycomb Impact Attenuator Tutorial(https://altairuniversity.com/wp-content/uploads/2016/11/Crash_Box_1.pdf). I've attached the file. When I try to run the simulation the Energy Errror starts at 0% and then rockets up to 99.9%. Then the Simulation stops. ROOT: SteelDummy RESTART: 0001 NUMBER OF HMPP PROCESSES 4 02/12/2019 NC= 0 T= 0.0000E+00 DT= 2.1400E-04 ERR= 0.0% DM/M= 1.7748E-05 ANIMATION FILE: SteelDummyA001 WRITTEN NC= 100 T= 2.1400E-02 DT= 2.1400E-04 ERR= -0.0% DM/M= 1.7748E-05 ELAPSED TIME= 54.23 s REMAINING TIME= 126646.67 s NC= 200 T= 3.5753E-02 DT= 1.2229E-04 ERR= -0.0% DM/M= 1.7748E-05 ELAPSED TIME= 54.82 s REMAINING TIME= 76607.94 s NC= 300 T= 4.7072E-02 DT= 1.0479E-04 ERR= -0.0% DM/M= 1.7748E-05 ELAPSED TIME= 55.35 s REMAINING TIME= 58738.95 s NC= 400 T= 5.6878E-02 DT= 9.1867E-05 ERR= -0.0% DM/M= 1.7748E-05 ELAPSED TIME= 55.87 s REMAINING TIME= 49054.49 s MESSAGE ID : 259 ** WARNING ZERO OR NEGATIVE VOLUME : 3D-ELEMENT ID : 700 ELEMENT IS SWITCHED TO SMALL STRAIN OPTION MESSAGE ID : 259 ** WARNING ZERO OR NEGATIVE VOLUME : 3D-ELEMENT ID : 1940 ELEMENT IS SWITCHED TO SMALL STRAIN OPTION MESSAGE ID : 259 ** WARNING ZERO OR NEGATIVE VOLUME : 3D-ELEMENT ID : 3120 ELEMENT IS SWITCHED TO SMALL STRAIN OPTION MESSAGE ID : 259 ** WARNING ZERO OR NEGATIVE VOLUME : 3D-ELEMENT ID : 4080 ELEMENT IS SWITCHED TO SMALL STRAIN OPTION NC= 500 T= 6.2841E-02 DT= 1.1098E-13 ERR= 99.9% DM/M= 1.7748E-05 ELAPSED TIME= 56.40 s REMAINING TIME= 44815.82 s NC= 600 T= 6.2841E-02 DT= 1.1098E-13 ERR= 99.9% DM/M= 1.7748E-05 ELAPSED TIME= 56.93 s REMAINING TIME= 45237.79 s NC= 700 T= 6.2841E-02 DT= 1.1098E-13 ERR= 99.9% DM/M= 1.7748E-05 ELAPSED TIME= 57.43 s REMAINING TIME= 45635.91 s NC= 800 T= 6.2841E-02 DT= 1.1098E-13 ERR= 99.9% DM/M= 1.7748E-05 ELAPSED TIME= 57.99 s REMAINING TIME= 46084.90 s NC= 900 T= 6.2841E-02 DT= 1.1099E-13 ERR= 99.9% DM/M= 1.7748E-05 ELAPSED TIME= 58.58 s REMAINING TIME= 46552.16 s MESSAGE ID : 205 ** RUN KILLED : ENERGY ERROR LIMIT REACHED NC= 1000 T= 6.2841E-02 DT= 5.1022E-18 ERR= 99.9% DM/M= 1.7748E-05 ELAPSED TIME= 59.22 s REMAINING TIME= 47060.74 s ANIMATION FILE: SteelDummyA002 WRITTEN Thanks upfront, Konrad SteelDummy.hm
  2. Hi, I have some questions I was hoping someone could answer. I am trying to model a sandwhich structure with carbon fibre skins and aluminium honeycomb core and then perform a 3 point bending test in the software if possible. 1. Could someone please explain what the reason is for selecting PCOMPP, PSOLID etc, what are the reasons for choosing one of them over another? 2. Which compersite property: PCOMPP, PSOLID, PSHELL, etc, do I need to select for the task I want to achieve (3-point bending simulation)? 3. Another question relates to my understanding of the MAT 8 card....would I be correct in saying that as MAT8 only asks for the in-plane properties, it would not be possible to get proper results for a 3-point bending test in the software? (Or does the software still work this out?) 4. Would I need to use the MAT9 card for what I am trying to do and in that case what composite property do I select, PCOMPP, PSOLID, PSHELL, etc? 4. If I select for example PCOMPP for the honeycomb properties, do I have to select PCOMPP for the carbon fibre skin properties? Regards
  3. Hi Im doing a project on aluminum energy absorbers and i need to do a quasi static analysis on my designed aluminum honeycomb. Basically a compression test. Im trying to do it in RADIOSS but have a few doubts. 1. Since it is a metal that is aluminum what mat law to choose is it 36 or 1 or 28(for honeycomb but i dont have the required curves, it is for foam right?mine is metal). 2. I have to give contact between the honeycomb and the two anvils that is top and bottom. What type of contact should i give? 3. I have created one rigid body body that is is the top anvil to give it imposed displacement. The bottom anvil i fixed. 4. And my total displacement is 23mm and the time taken was 46 mins at a rate of 0.5mm/min in the physical test in the utm. 5. Im trying to replicate this compression to get Force vs deflection graph and energy absorbed. Im attaching the pictures of my model and also my hm file. honeymesh2_5.hm
  4. Hi, In a drop test, I simulating paper honeycomb behavior between the payload and platform. I tried with Mat Law 2,28 and 68. The strain reported as more than 1. Is it correct?
  5. Hi All, FYI, the model is a sandwich panel (with aluminium honeycomb at center and one layer of carbon on each side- top and bottom) used in monocoque. Well, I am stuck at meshing of honeycomb and unable to get consistency in results. While trying on the actual cut sample (LxW- 368mm x 176mm), I got 'volume analysis failed' and 'temp_2d_for_tetra' for many a times and so I thought I should try on a small pattern (70mmx35mm). After trying on a small pattern, the carbon layers are not attached while viewing in HyperView, i.e. honeycomb deforms individually and carbon layers deform separately at higher frequencies. I created the assembly in SolidWorks ('mate' in assembly file) at first, it gave the results as mentioned above (carbon layers not attached with honeycomb). Next I created lines on outer edges of honeycomb in HyperMesh (to develop carbon layer), assigned thickness (of carbon) and meshed it; but in both cases, the honeycomb is not attached to carbon (while viewing '.op2' file in HyperView). Can you please help me out with this? Much appreciated. Thanking You. Kind Regards, Shreerang
  6. Hi to all, i'm trying to simulate a plate (PCOMP) in which the central layer is a honeycomb layer. But... is there a way to insert a 3d orthotropic material in hypermesh with NASTRAN interface? or this option is not available yet? Does anyone have some idea how i can proceed?
  7. 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
  8. Hi, i want to create a Sandwich plate with a honeycomb core, like shown in the attachment. I want to do that with the tool hyperlaminate. My upper and lower plate is normal aluminum createt with the MAT1 Card. But how can to create the honeycomb core? I thought i could make it with the MAT8 Card, but I don´t find any properties for the Input. I took the MAT8 Card, because my moddel is built up with shell elements. Thanks for your help.
  9. Hi all!! I have a question, which might seem quite obvious but it is driving me crazy. I am modelling honeycomb panels with 2D surfaces. Until now I have always modelled this material as 2D orthotropic, so with MAT8. Now my materials have changed and the following question arises to me: For the core ply, information available from manufacturer data sheets is the following: E3, G13 and G23. However, if I want to treat my model as surface, it is not possible with MAT8, because material parameters that I can introduce there are E1, E2; G12, G23, G13 and Poissons ratios. Is there any estimation or any conversion possible in order to make it work with shells? Another possibility is to model it with solids and using the Optistruct Engineering Solutions tool, which enables me to create a solid out of shells; however, when using it all contacts between surfaces are lost. Has someone faced the same problems when modelling honeycomb panels? It would be of great help. Thanks in advance!! Regards, Andrea
  10. Guest

    HyperWorks Tutorials

    Dear Sir or Madam, For my work I am looking for introctory tutorials that can teach me the basics for using Hyperworks. My research issue will focus on the optimization of foams and lattice structures so I am also interested some Optistruct tutorials. If there is a way to handle threedimensional foams (I already discovered a honeycomb material) I am also keen to learn about this. Regards, Alexander
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