This thesis focuses on the design, construction, and testing of a fixed-wing UAV made of composite materials, mainly carbon fiber. The main objective is the development of an architecture capable of monitoring flight parameters from the structural behavior of the wing and aileron servo motors, using optical fiber FBG sensors integrated directly into the structure. The work was carried out as a research project and was based on the geometry and configuration of a competition UAV that had already been tested. This choice allowed the use of a reliable and safe flying platform for experimental flight tests. Starting from this validated baseline, a new UAV platform (Sirius II) was developed, introducing several structural modifications mainly related to the internal wing configuration and conceived specifically for sensor integration and structural monitoring.