The focus of this study pertains to the modeling of Unmanned Aerial Vehicle (UAV) structures utilizing composite materials. Composite materials are frequently employed in the fabrication of high-impact components owing to their favorable dynamic attributes and superior mechanical properties, including a commendable strength-to-weight ratio, notable stiffness and resistance to fatigue, as well as exceptional corrosion resistance. The initial phase of the analysis entails conducting a three-point bending test on specimens composed of composite materials. The test is subsequently simulated using the Samcef software. The congruence between empirical tests and the finite element model yields the inference that the material properties furnished by the manufacturer are accurate and faithfully depict the material's actual performance. The subsequent phase involves the formulation and construction of a finite element model encompassing the entirety of the aircraft. The model's validity is assessed through the execution of a preliminary bending test on the UAV. A comparison is made between the displacements observed in the model and those obtained in the actual experiments. The findings indicate that the model exhibits a marginal increase in rigidity compared to the actual aircraft, as anticipated. This outcome facilitates the verification of the finite element model's results. The ultimate phase entails the simulation of a verisimilar flight configuration wherein the aircraft is exposed to substantial aerodynamic forces. The designated role pertains to the resource allocation associated with the aircraft's descent for retrieval purposes. Aerodynamic loads are computed using the PanAir software and subsequently incorporated into the finite element model. The findings indicate that the structural integrity of the system is capable of withstanding the applied loads. However, it is recommended to explore potential material optimization strategies, as certain components exhibit stress levels that exceed their yield strength.