Recoving Composite Ply Stress After a DDAM Analysis
Recoving Composite Ply Stress After a DDAM Analysis
(OP)
Hello. I am trying to recover composite ply stresses after a DDAM run. DDAM does not support (or at least I don't think it does)laminate property cards, so my results are outputed as Shell stress. Does anyone know of a way that I can convert these shell stresses back to laminate stresses so I can get ply stresses in my composite.
Thanks in advance.
Thanks in advance.





RE: Recoving Composite Ply Stress After a DDAM Analysis
remember to keep one knot free (without imposed displacement) to obtain a solution else the solver do not have degree of freedom to solve.
Check the consistence of the system for a non layered model first, as I've never applied this method to a DDAM analysis.
regards
Onda
RE: Recoving Composite Ply Stress After a DDAM Analysis
RE: Recoving Composite Ply Stress After a DDAM Analysis
This seems like it would be perfect for a FEMAP API, since FEMAP has all the data available to it (shell loads, composite material properties etc) but I do not know how to take advantage of these things and create a program to automate the failure index calculations. If anyone can help in this area I would greatly appreciate it.
Thanks again.