Error #144

Dani_20

Hello,

 

I have been trying to simulate a sandwich panel with aluminium core, insert and carbon fiber laminate. I have introduced the following values for carbon fiber and core:

 

       

 

I have also defined the failure criteria in properties as TSAI. I believe everything is correctly defined, however when I run the simulation the following error appears:

 

 *** ERROR # 144 ***
 CPYRA element 155981 has singular strain functions.
 Please check material data.
 

Anybody could help me please?

 

Robert Lawson

Looks like you need to define the G's in your materials which are currently blank. 

 

In the case of the core, G23 and G31 are the key stiffness values relevant for honeycomb core.  Typically, these would be grabbed from a Hexcel datasheet.

 

For the carbon fiber material, you can estimate G1Z and G2Z to be the same as G12.

 

- Robert