Аннотация
This study examines the potential to improve the aerodynamic performance of unmanned aerial vehicles (UAVs) through the use of carbon-based composite materials. The main goal is to reduce structural weight while maintaining high mechanical strength and aerodynamic efficiency. Results indicate that the specific tensile strength of carbon composites ranges from 2258 to 2903 MPa/g/cm³, significantly higher than that of traditional aluminum alloys. CFD simulations showed a lift-to-drag ratio (CL/CD) of 5.4 at low speeds, with stable performance up to 100 m/s. Experimental tests revealed a decrease in vibration amplitude to 0.4 mm and deformation to 1.2%, indicating enhanced vibroacoustic stability. Owing to the material’s low density (1.55 g/cm³) and efficient force distribution, structural weight was reduced by up to 40%, resulting in a 35% increase in flight duration. A notable aspect of this work is the integrated evaluation of structural and aerodynamic parameters using CAD tools for modeling, MATLAB/Maple for calculations, and ANSYS Fluent for simulation. The findings support the viability of carbon composites for industrial-scale UAVs in defense, agriculture, and emergency operations. This research was conducted under project BR249005/0224, funded by the Committee of Science, Ministry of Science and Higher Education of the Republic of Kazakhstan.