Recent content by jargon5

Has anyone used the THERMOD program from NIAR's Website? Reviews and/or comments? We are thinking of using it as a trial run...and would like some unofficial comments. Since it is essentially "use at your own peril", we are seeking some advice...

Thanks Dr. Daniel Samborsky. One question though-the nomenclature of the materials used in the report, i.e., DDW, are not clearly identified. Where can this information be found?

I need to calculate the q-factor for an airplane part. Does anyone have any good references to calculate the q-factor for a composite structure?

My company is trying to build a good composite library, and I was wondering if anyone has some good references for graphite/epoxy fatigue data?

I have an assembly that I set "Global Contact", and have produced results that are marginally what I expected. Does anyone have any experience with the accuracy of Cosmos contact elements? I am used to NE/Nastran, and know the difficulty of assessing the actual phenomena when using this approach.

Are you trying to get strain data, and haven't converted the strain to stress? Try running stress results, and that unrecognized bulk data entry may disappear.

My company has a hydraulic dampener for landing gear that uses a bleed hole in the cam. I need to evaluate how much actual pressure is formed within the chamber where the fluid is bleeding out of at impact loading. Does anyone have a good reference for this kind of analysis?

Thanks dcmax...I checked the log file, and below was the exact documentation. Any help would be always wanted. FATAL ERROR S1110: INSUFFICIENT MEMORY AVAILABLE TO CONTINUE VIRTUAL MEMORY = 512342015 WORDS 3908.9 MEGABYTES REAL MEMORY =...

Hello All- I have a huge file that has an excess of 220,000 nodes (200,000 elements), and each time I run the analysis, I get the Fatal Error S1110, which states the following solution options: Increase your virtual memory setting (see virtual memory in Windows Help). If this does not...

Anybody have general information on bearing allowables for graphite/ epoxy laminate with 60% uni-directional fibers and 40% +-45 fibers? I generally use half of the compressive strength, approximately 60 ksi, but I would like some good documentation.

Does anyone know how to allow the stresses to change with the part in animation mode in FEMAP post-processing? This would help demonstrate where the peak values are (compression, tension, etc.).

I used laminate plate elements, and the outer plies were designated as orthotropic carbon fiber, whereas the inner ply was isotropic rohacell core.

I have the panel modeled and I know the stresses from the FEA. I just don't know how to combine the dissimilar materials of the laminate to know the laminate allowables. Any suggestions?

Perhaps I haven't explained: we are the manufacturing company from the standpoint that my company has manufactured the sandwich panel, by laying up the carbon plies on the Rohacell. Now, I have the Rohacell material properties and I have the Carbon laminate properties. The question is: do I...

Thanks for the replies. How do you get approximations for the allowables without testing?