Based on the laminate theory [1] i am able to calculate the reduced stiffness matrix Q´ / C´ of each layer (formula 13.12). Now i will calculate the stiffness matrix based on this formula K=∭(B^T C B)dV [2]. Is it now possible to implement this in the stiffness-routines for shell elements e.g. from the FEA-freeware Z88?
Maybe does anyone know how to handle this context other ways? Main task is to implement a stiffness routine for composites in finite element software.
[1] Berthelot, J.-M.: Composite Materials, Mechanical Behaviour and Structural Analysis. Springer. New York. 1999
[2] Rieg, F.; Hackenschmidt, R.; Alber-Laukant, B.: Finite Elemente Analyse für Ingenieure. Hanser-Verlag. München. 2012
Set a constant elastic modulus for the composite material and assemble the stiffness matrix using FE soft. Then the stiffness matrix of the composite material can be formed by postprocessing the stiffness matrix.
See the following paper for details.
http://www.sciencedirect.com/science/article/pii/S0045794913003155
Thanks for the answer!
For me, setting a constant elastic modulus means no anisotropic effect. So actually i don´t think this will work.
Thank you for the answer! I didn´t recognize the notification, sorry.
- Badges
- Science method