Design and manufacturing of an unmanned aerial vehicle

Abstract

The purpose of this project is to design and manufacture an unmanned aerial vehicle with the highest technology and features and the lowest price possible. Based on historical data and old close range UAVs, mechanical and electrical studies and calculation were conducted to achieve the predetermined requirements and objectives of the aircraft. An aerodynamic analysis based on CFD experimental data and vortex panel code results were performed to guarantee a minimum lift of 24N and a maximum drag of 2N. The EPS-45 Foam was chosen as the main building material for its great strength/weight ratio. Multiple specimens of this foam were subjected to two standard ASTM test method: 3 point bending test and tensile test, in order to obtain the exact mechanical properties of that material. Then a structural analysis and simulation using the finite element software ANSYS was done to study the behavior of the prototype under particular situations; cruise speed and maximum speed. The results show that the wings undergo a large deformation at the tip. Wherefore, an aluminum reinforcing rod was included along the wing to prevent this large deformation decreasing it from 80mm to 14mm. Next comes choosing the best combination for the propulsion system components and the avionics to achieve a long range and endurance of 3 hours. And finally, the final product was manufactured according to the studies and the results achieved.