Citation:
Saludheen A, Muhammed Zakariya F, Ankith M, Nandakumar N, George J, Thankachen G, Renjith R, Ajith Kumar A, Viswanath A, Jithin PN. Carbon fibre composite development for in-ground UAV’s with NACA0012 aerofoil wing. Materials Today: Proceedings [Internet]. 2021.
Abstract:
A carbon fibre reinforced polymer is designed for NACA0012 airfoil wing using a finite element model to determine the stresses and deformation by considering the aerodynamic loads from wind tunnel testing. The composite airfoil is designed for the use in morphing wings which are known to increase the aerodynamic efficiency of unmanned aerial vehicles. This paper deals with the design procedures of modelling a composite wing using different design variables in conformance to the first order shear deformation theory using ANSYS® 19.2 and optimizing the design by using a fourth degree polynomial found by surface fitting and genetic algorithm in MATLAB® R2020a. The analysis is carried out on 125 samples consisting of different materials, orientation and thickness. The pressure loads found from the wind tunnel testing was converted using weighted average method and applied in ANSYS® 19.2. While designing the airfoil, monocoque concept is used for structural integrity and this is implemented by the usage of Styrene acrylonitrile at the leading and trailing edges which has high strength to weight ratio. The composite laminae with a certain orientation and thickness is found to have the lowest deformation of 158 nm in response to the aerodynamic load.
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