Nonlinear Finite Element Method simulations are carried out to study the response of a laminated composite structure. Both damage onset and damage progression is considered in the plies as well as at the ply interfaces. The effect of residual stresses from curing is taken into account. The Finite Element Program ABAQUS/Standard 2024 (Dassault Syst`emes Simulia Corp., Johnston, Rhode Island, USA) is used with onboard means only. The numerically efficient “stacked shell approach” is adopted which allows for the modeling and simulation of large structures, see e.g. [1]. Each ply is modeled by an individual layer of conventional shell elements employing the Hashin continuum damage mechanics model for fiber reinforced materials. The ply interfaces are represented by cohesive zone elements which connect adjacent ply layers. The constitutive response is given by a traction separation law which allows for delamination. The investigated structure is a three point bending type experiment under quasi-static loading conditions as reported in [2]. The load–displacement curve will be predicted as well as the onset and progression of the modeled damage mechanisms. The advantages of the chosen modeling approach will be discussed and possible limitations will be identified. REFERENCES [1] M. Schwab and H.E. Pettermann. Modelling and simulation of damage and failure in large composite components subjected to impact loads. Composite Structures 158, 208-216, 2016. [2] O.A. Batmaz and D. Coker. Effect of Ply Thickness on Dynamic Damage Progression in Cross-Ply Laminates Under Low-Velocity Impact. In: Proceedings of the 9th ECCOMAS Thematic Conference on the Mechanical Response of Composites. Ed. by G. Catalanotti, H. Pettermann, and G. Pittaresi. ECCOMAS. Trapani, Italy, 2023.