Laminate post process
Laminate post process
(OP)
I had tried the laminate elements in NX/NASTRAN for Windows (FEMAP). How can I analyse any failure criteria value in this software? How can I plot it?
Irwin
Irwin
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RE: Laminate post process
When l use NASTRAN with laminates l get the forces and moments for the elements where l want to check. NASTRAN gives you directly N/m for the forces and N.m/m for the moments.
These values corresponds to the forces and moments of the laminate.
In order to check the lamina you can use the values of the forces and moments obtained with any software for laminates (the laminator gives good results).
Good luck,
Esteban
RE: Laminate post process
Ervin
RE: Laminate post process
I'm running an older version of NASTRAN (CSA), and here is some guidance from the User's Manual, Vol 1, Section 1.3.15, "Composite Material Structural Analysis".
"The action required on the part of the user to access layered composite analysis capability is very minimal. The user must insert the appropriate PCOMP and MAT8 data which describ e the composite laminate into the bulk data deck. Ply data recovery options are automatically performed in static analysis based on case control keywords of STRESS and FORCE. Stresses in individual lamina of the laminate, forces on the laminate and failure index tables for composite laminates will be provided in static analysis if STRESS and FORCE case control keywords are present."
In using CSA NASTRAN, I have found that you need to write the output to the .f06 file in order to recover the ply data. This means using STRESS = ALL and FORCE = ALL in the case control, instead of STRESS(corner,plot) = ALL. Then you have to import the analysis results into FEMAP by reading the resulting .f06 file. Once you read the .f06 file in, you will have the option to plot the ply failure criteria.
Another suggestion is that if your laminate has a core, you should model the core with brick elements, and the face sheets as composite laminates. That way, you can recover the XZ and YZ core stresses to compare with core shear allowables.
Regarding the ply failure criteria, you select the failure type on the property card in FEMAP.
Good Luck
J. Vorwald
P.S. I'd be interested in knowing more about the problem / application you are working on.
RE: Laminate post process
You mentioned that "Another suggestion is that if your laminate has a core, you should model the core with brick elements, and the face sheets as composite laminates. That way, you can recover the XZ and YZ core stresses to compare with core shear allowables."
I'd be very intersted to learn more about this - what would you suggest if core is honeycomb material?
Thanks
RE: Laminate post process
Garland E. Borowski, PE
RE: Laminate post process
RE: Laminate post process
RE: Laminate post process