Found a solution. Apparently, a distributed force (in N/mm) is not acceptable in this case. I changed the load to a force (in N) acting on the same edge, and the solver works without problems.
Hello all,
I have started working with Inventor Nastran just recently (I have only little previous experience in FEM) and I am facing problems in setting up a load case for a cylindrical structure. I constructed the structure as a cylindrical surface and generated a shell mesh with a laminate...
"Calling all Six Sigma Black Belts!"
Hi everyone,
I am trying to evaluate testing results using Minitab. I would like to use the graphical method "Normal Plot of Standardized Effects" to vizualize how the test result is affected by a number of factors. Here's an example of what this plot looks...
thread825-222534
"To whom it may concern"
Hi all,
I am referring to the above thread titled "Plotting Strength ratio of composite with param SRCOMPS" from 2008/2009. It has helped me calculate strength ratios (SRs) in Nastran 2018.2 while using Hypermesh and HyperView 2017.3 as pre and post...
Hi everyone,
I have found a solution. In HyperMesh, I set PARAM,POST,-1 and GLOBAL_OUTPUT_REQUEST,STRESS(SORT1,PUNCH,REAL,VONMISES) and GLOBAL_OUTPUT_REQUEST,STRAIN(SORT1,PUNCH,REAL), so that .op2-file is created.
To make sure that all Nastran results are kept, I entered "scratch=no" when...
Update:
I got the Failure Indices to appear in the F06-File. The reason for them not appearing was that under "Load Steps > Subcase Options > DISPLACEMENT" and "Load Steps > Subcase Options > STRESS" I had "FORMAT" set to "PLOT" instead of "PRINT".
However, I am still unable to view the failure...
Hi all,
I am new to this forum and have a question concerning composite failure analysis. I wasn't able to solve my problem with the existing threads, hence this new one.
I am currently working on a sandwich structure which is made from an aluminium honeycomb core and carbon fibre UD/epoxy...
