Numerical assessment of failure mechanisms in fibre metal laminates

In this contribution numerical models are discussed for describing failure mechanisms in fibre metal laminates. Fibre metal laminates form a new class of materials which are considered for a possible application to the fuselage of future aircraft generations. The intensive experimental analyses of these materials are focused on the assessment of their residual strength and on the assessment of new design methods. To support the experimental analyses numerical models are used to describe cracking and delamination in fibre metal laminates. A special continuum element and a corresponding interface element are introduced. Furthermore, loading functions are applied which account for cracking and delamination. Subsequently, results are discussed which are obtained from numerical analyses of the residual strength of plates made of GLARETM . Finally, the splicing technique as a new design method is assessed by a comparison between numerical and experimental results.Koiter Institute DelftAerospace Engineerin