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hi, i perform a sandwich plate with shell 91. I solve the analysis and i want use the Von mises resut as scalar parameters. but the value of the result is doesn't the same that the result given by the model. let me explain my procedure the result of the model for the von mises stress...

yes, i try with the hydrostatique pression, idem

hi, Thanks, I will clarify my question. I do that and this is also on the tuto. But the magnitude used the time as variable and i want that the pressure vary with the distance (function x, y) and no with the time. It's possible with workbench?

Hi, I think my question is very simple but i don't found the answer. I want put a distributed load on the surface, it's not a problem for the other load or support. I say the ansys classic can do it but I'm not the time to learn ansys and the workbench interface is simplest for me. I don't find...

Thanks, I try your solutions, Kellnerp, but the overlaping and using the rigid element don't work in my model. Solidwords get across the surfacic model through the other part. It's very strange and i don't understand. I have prefered to re-make the simulation under ANSYS v11 and that's run...

Thanks for accuratly, I work with solidworks 2009 simulation. Exaltly, the model composite shell is not available in old version of solidworks. I phoned at the hotline and they said the problem is onthe contact between the surface shell and the surface solid. I put the contact manually...

Hi, I have a problem with simulation, i modelise a sandwich with a solid part for the nida and surfacic part for the skins. I precise that the part is the composite tank. I made the kind of model because I want to differ the plies in the skins and the existing module in solid simulation can't...

Thanks for your help regards

Hi all I look for a general formula to calculate the critical buckling of the sandwich beam. What do you recommend? Thanks

Hi all, I ask me how calculate the max deflection of the sandwich plate with skin orthotropic (with a simple expression, please, not with the KL plate theorie). Methods can i have seen in the hexcel catalog, structure composite daniel gay, the bruhn or other books taking the assumption that...

Hello (sorry for the mistakes) I begin in composite analysis and i have a problem. I don't found the formulation to calculate the bending stiffness of the sandwich panel,with two orthotrope skins (0°,45°,0) and nomex hexagonal core. here are the data of the materiel for the skin (carbone...

Hi, "first,Sorry for the mistakes" I begin in analysis composite and i want calculate the equivalent modulus of the plate composite(carbone/epoxy) (sequence.0°,45°,0°). I calculate the global stiffness matrix (A, B, and C) i found a formul in composite stress manuel to calculate the...

Hi, "Sorry, I'm not a god in english" I'm agree with wktaylor May be with a endoscopic material.Endoscopic could allow to access in a blocked vent hole by inlet and outlet connections. You can local manufacture a little knife or attach a scapel or razor blade. I already use this method...

Thank you for your solutions, I think I understand the process, the module E1, E2 and the poisson ratio V12 and V23 which does very little about the final result.So, a little value is acceptable,they allow just the feasibility of the analysis by the solveur. You're right, the FE forum is more...

Hi, First, sorry for the mistakes, I'm not a god in english. I begin in the composite structure. Actually, i try modelling a equivalent sandwich model with Cosmos software. I get on the equivalent modulus for the skins (carbone,epoxy: 6 layers) but,for the honeycomb (nomex), i don't go the...