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NX Nastran Buckling Analysis with Manual Inertia Relief

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Burner2k

Aerospace
Jun 13, 2015
193
Hello,
I am trying to learn on how to do Buckling Analysis using Inertia relief in MSC/NX Nastran. Trying to learn on a simple plate and progress in to more complex problems. Currently, I using Femap and I am able to run Static Solution successfully but in 105, I am getting Fatal errors.

I am attaching a bunch of screenshots and hopefully, someone with more experience can point out where I am going wrong.
Problem Setup: Simple Al Plate of 5mm thickness subjected to 100 units of transverse load
01_igy6m4.png


Set up a Constrain on Node 96 (center node of free edge curve) in all DOF
02_lsluib.png


03_hvwrh1.png


04_icgckq.png


05_tzojm2.png


06_mkpg1m.png


F06 Error:
07_zme80l.png

I have a feeling it has to do with support definition but I don't know what to do since the same setup ran successfully in SOL101.
 
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That loading will not result in buckling, rather bending. Why not apply in-plane compression load and fix the entire edge, not one point.
It appears you requested a modal analysis not buckling.
Do you have mass properties defined?
Try running without inertia relief.
 
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