Aerodynamic design and structural optimization of a wing for an Unmanned Aerial Vehicle (UAV)

Abstract

This paper summarizes the process of structural design, analyses and optimization for weight reduction of a UAV wing. A semi-monocoque wing structure that consists of ribs, spars and skin are efficiently optimized for Weight minimization without reducing the Strength to weight ratio. Initially a solid wing surface is designed with the air foil co-ordinates of NACA 2412. The CFD Analysis is carried out to get pressure distribution on various arrangements of wing by changing angles of attack. From the CFD results the variation of coefficient of lift for different angle of attack is determined. The pressure fields obtained from CFD analysis is imposed on structural members for structural analysis. Optimization of this wing is done considering various cases until the required performance is obtained. The results are obtained for the optimized wing and this helps in obtaining reduced weight of the wing and increased strength to weight ratio. Results show that substantial improvement has been achieved in comparison to the standard model.