<p>This research focuses on developing a numerical model for predicting time-varying displacement responses of damaged fibre-metal laminate (FML) hybrid structural components using a higher-order mathematical model, including pre-damage. The numerical solution accuracy obtained using a customized computational code (MATLAB) through the mathematical model is verified with experimental dynamic deflection data. The numerical transient responses are computed through Newmark’s (average acceleration) integration technique in association with the isoparametric finite element approach. Additionally, the pre-damage (crack) is introduced through a variable crack closure technique (VCCT) in a simulation tool (ABAQUS), and the mesh details, including the nodal information, are imported to the MATLAB platform using the compatibility code. For experimental validation purposes, a few hybrid FML (glass fibre epoxy panels joined with aluminium plates) are fabricated and utilized for experimentation, including the experimental material properties. The numerical model accuracies are initially verified with previously published transient values of the laminated composite. After fulfilling the necessary convergence criteria and the validation, the computational model is extended to work out a few parametric analyses to understand the significance of damage and limiting factors (curvature ratio, geometric shapes, and modular ratios) in designing such FML components. It can be concluded from the numerical experimentation that the geometrical parameters (curvature ratio, stacking sequence, and aspect ratio) largely influence the dynamic deflections, i.e. the responses vary from 4–8% (increase in peak displacement). Meanwhile, the values upsurge by 32%, while the structural end-restrained conditions are less (for a cantilever case: CFFF). Finally, a set of recommendations is listed to understand the advantages of the proposed model for the analysis of FML structure, including the damage effects.</p>