This work introduces a method for the inverse identification of composite material properties using dynamic response data and finite element modelling. The methodology combines numerical modal analysis, Design of Experiments (DoE), Response Surface Methodology, and a Multi-Objective Genetic Algorithm (MOGA) to determine material parameters without destructive testing. The approach was applied to a UAV composite wing, achieving high correlation between simulated and experimental modal characteristics, with natural frequencies deviations below 2%. Variations between the identified parameters and reference data are linked to inherent inconsistencies in composite manufacturing and the operational condition of the tested structure. Nevertheless, the proposed method proves to be a reliable and non-invasive tool for estimating mechanical properties, enhancing the predictive capabilities of numerical models. Its adaptability makes it a promising solution for future applications in structural health monitoring, damage assessment, and optimization of aerospace composite structures.