Delamination is common in composite layered materials. These out-of-plane cracks are conventionally modelled through a layerwise strategy where each composite layer is represented with finite elements. The interface between layers is modelled with cohesive elements. This modelling strategy involves a fine discretisation through the thickness of the laminate. Additionally, cohesive elements need small in-plane elements (typically < 1 mm) to accurately represent the interface fracture process zone. As a result, this conventional approach leads to prohibitive computational costs for large assemblies. The present work develops a strategy that is orders of magnitude more efficient for modelling delamination in large structures. The model initiates with a single solid-shell element representing the laminate thickness. The out-of-plane stresses are accurately recovered through the thickness of the laminate [1]. The model is enriched with additional nodes at interfaces, where delamination is detected, to kinematically describe the cracks [2]. Then, a novel energy-based cohesive method is used to model the crack propagation using large elements (e.g. 5 mm) [3,4]. The presented examples show that the novel modelling strategy is orders of magnitude faster than the conventional layerwise method while achieving comparable accuracy. [1] P. Daniel et al: Complete transverse stress recovery model for linear shell elements in arbitrarily curved laminates, Composite Structures, 2020. [2] J. Främby and M. Fagerström: An adaptive shell element for explicit dynamic analysis of failure in laminated composites Part 2: Progressive failure and model validation, Engineering Fracture Mechanics, 2021. [3] P. Daniel et al: An efficient ERR-Cohesive method for the modelling of delamination propagation with large elements, Composites Part A, 2023. [4] P. Daniel et al: A method for modelling arbitrarily shaped delamination fronts with large and distorted elements, Engineering Fracture Mechanics, 2024.