Thin-walled composite structures are critical in aerospace engineering, making it essential to understand their failure mechanisms. However, manufacturing test samples and conducting high-fidelity experimental tests are both complex and expensive, making advanced modeling techniques essential. The Cohesive Zone Model (CZM) is a widely used method for modeling delaminations in composites, but it typically depends on artificial elastic compliance, which can compromise accuracy. This thesis introduces a high-fidelity finite element model that integrates the Discontinuous Galerkin method with geometrically exact shell elements to explicitly model each lamina during large deformations and buckling in multi-layered materials. By coupling the layers, this approach eliminates the need for artificial compliance. Numerical simulations show the model’s accuracy in predicting structural behavior under various loading conditions, although challenges remain in maintaining proper layer separation during deformation. This study lays the groundwork for modeling delaminations along arbitrary interfaces.