I'm working on a T-34 wing model after an in flight failure. At ultimate flight loads the upper wing skin is buckled so I used CShear elements that will not take normal force and used rod elements to model the effective skin. Even using permanent constraits 45&6 and Auto SPC on, the deformed...
Thanks for your response. If I use a single tappered beam element to model a tappered wing spar cap, is there a way to use "mesh / refine" so that discrete properties are created by FEMAP for each new element or do I still have to write a separate property for each element?
I want to use rod elements to model a tapered wing spar cap. There will be over 100 elements over the length or the spar cap. Writting a separate property for each element is very time consuming. I don't see a mesh command that will auto create the elements with varying cross-sectional area.
