MULTI-DISCIPLINARY DESIGN OPTIMIZATION OF UNMANNED AERIAL VEHICLE

A general procedure of preliminary design of aircraft and one-way fluid-structure interaction (PSI) applied to aircraft design is introduced briefly. Then, PSI and optimization technique are implemented to optimize a wing shape of an unmanned aerial vehicle (UAV) for minimum cruise drag. FSI analysis and optimization processes for minimizing drag of UAV are explained. Design variables are wing taper ratio and dihedral angle, and objective function is the cruise drag of UAV. Fluid solution is generated with Euler solver and structural analysis is performed with FEM solver, Diamond. Sample points are selected by Design of Experiment (DOE) method and Kriging method is used for generation of an approximation model.