About the Project
Cracks are represented as a strong discontinuity in the displacement field. Under compression cracks tend to be inclined within the layer mid-plane which can lead to failure where the outer plies are pushed out of the plane of the laminate and eventually buckle.
In principle, it is possible to model the inclined crack plane with the Finite Element Method. The basic idea is that the direction into which stiffness recovery under compression takes place is altered for a crack that develops under compression. Only one layer of elements per ply might be used, which is typically done for reasons of computational efficiency.
The project can also include simulations where in-plane shear is acting on the potential crack plane.
This project is available only for Self funded students.
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