Dear Members,
Because I am using UMAT, I need to define the transverse
shear stiffness for shell elements. I read the documentation couple times but I
could not figure it out.
For linear elastic material ABAQUS automatically compute these
values K11, K22 and K12. For homogeneous
material it can be approximated by
K11=5/6*G13*t, K22=5/6*G23*t and K12=0.
However for composite it would be different, how to
calculate it?
My laminate is not symmetric and I have the following
material properties: E1, E2, G12, G23, V12 and the lamina thickness t.
I tried to use the elastic option with type=lamina and let
abaqus compute the number (which it did) but I could not find it in the data
file even when I request the model definition in preprint option.
Any help is appreciated,
Fahad
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