Optimización de una superficie aerodinámica de geometría variable para vehículos aéreos no tripulados (UAVs).

Abstract

In the last decade, variable camber morphing wings have evolved in the technique of transforming the leading edge and the trailing edge using compliant mechanisms to improve their structural and aerodynamic characteristics. The optimization of these mechanisms requires a multidisciplinary approach, aerodynamic and structural, to meet the goal of increasing the flight autonomy of an unmanned aerial vehicle (UAV), subject to geometric restrictions to achieve the best adapted mechanism. This work presents a systematic approach to optimize a 2D compliant mechanism to carry out the required shape changes under distributed loads for the baseline airfoil (NACA 0012). To minimize the force applied through a servomotor to transform and preserve the deformed geometry of the baseline airfoil towards the target profile (NACA 8412). This methodology uses MATLAB, GMSH, XFOIL, and CALCULIX to optimize the flexible mechanism using a genetic algorithm (GA). The mechanism with the resulting structure can perform the transformation to the target profile with a maximum curve fitting error of 0,92% and with an applied force of 0,16 N at the leading edge and 0,07 N at the trailing edge, lower than required by the baseline configuration, the reduction resulted in lower power consumption by the servomotor and greater autotomy of the UAV. The experimental data of the model confirm the feasibility of this approach.