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These days composite materials are widely used as elements of various machinery.
They are applied as reliable machinery parts e.g. in aviation or automotive. This paper is referred
to coupled laminates, which are one of composite materials types. Most common damage form
in laminates is delamination. The aim of this paper is to show how to use Cohesive Zone Model
technique (CZM) to model fracture propagation in laminate specimens. Finite element models
were constructed using shell type elements in ABAQUS, which allows to analyze fracture
propagation involving cohesive zone effect [5]. This operation needs many material constants
which obtaining experimentally is problematic . The FE analysis is helpful in reasonable
planning the stand tests and shows the accuracy of experimental studies. It also provides a lot of
relevant information on laminate properties. Boundary conditions, loads and the obtained
fracture toughness distributions of the numerical models of coupled laminate beams correspond
to the mode I and mode II delamination propagation: the double-cantilever beam (DCB) and the
end-notched flexure (ENF) [1, 3].
