Proceedings of the 20th International Conference on Composite Materials, Paper #4417-4, 2015
M. Schwab, M. Todt, H.E. Pettermann
Institute of Lightweight Design and Structural Biomechanics,
TU Wien, Vienna, Austria
A strategy for modelling impact on woven fabric reinforced laminates at
intermediate velocities using the framework of the explicit finite element
method is presented such that the energy absorption of the laminate can be
predicted and assigned to individual failure mechanisms.
Thereby a "stacked shell" approach is utilized where each ply of the laminate
is discretized by an individual layer of shell elements.
The damage and failure behaviour of the plies is modelled using an energy based
continuum damage mechanics approach.
Tensile and compressive ply damage along the fibre directions, as well as shear
damage are considered.
Additionally plastic deformations due to shear loads are captured.
Delamination is accounted for by modelling the interfaces between individual
plies using cohesive zone elements in combination with a traction-separation
based constitutive law.
Element deletion is utilized to cope with fully damaged elements and,
furthermore, contact definitions between delaminated plies are included.
Hence, the approach is capable of predicting the impact response of laminated
composites up to complete perforation.
In order to show the predictive capabilities of the presented modelling
approach, a rectangular carbon fabric/epoxy reinforced laminated plate with
quasi-isotropic layup in a drop tower test setup is modelled.
The predicted energy absorption of the plate, as well as the deformation
behaviour and the damage and failure behaviour are compared to equivalent
Additionally, the contributions of individual failure mechanisms to the total
energy absorption are predicted.
The described modelling strategy is particularly advantageous in terms
computational efficiency, while maintaining detailed and quantitative