This study presents a finite element–based weight optimization framework for a composite UAV wing using ANSYS. The main objective is to minimize the structural mass while satisfying strength-related constraints by limiting lamina stresses within allowable material bounds. A parametric APDL model was developed to represent the wing geometry and key structural parameters (e.g., rib configuration and spar layout), and to define optimization design variables including the number of plies, ply orientations, and stacking sequence for carbon fabric and honeycomb-based components. The wing mass was taken as the objective function, while stress constraints were enforced using the maximum-stress criterion. The obtained results demonstrate a significant improvement over the baseline design, achieving a weight reduction from approximately 209 kg to 114 kg (about 45%) while also decreasing the maximum stress from about 421 MPa to 330 MPa, remaining within the material strength limits. Owing to its parametric nature and straightforward implementation, the proposed approach can be extended to different wing geometries, composite materials, and loading conditions for lightweight UAV structural design.