Modeling of corrugated laminates

This work compares two modeling approaches for corrugated laminates. Both models use a unit cell and a generalized plane-strain approach in order to determine a substitute plate model. The first model is based on a linear thin-shell theory and the second model uses a self-programmed finite element program with planar elements. The comparisons show the differences of the models as well as the limits of the shell theory approach. Furthermore, the realizable anisotropy of corrugated laminates which is important for morphing wing applications is investigated.