A multilevel multi-objective surrogate-based optimization of a UAV wing considering structural and aerodynamic performances

In this work, we propose a generic approach for the shape optimization and structural sizing of fixed-wing UAV wings. This approach is multidisciplinary, integrating aerodynamic and structural analyses through a one-way coupling suitable for preliminary design. The aerodynamic analysis is performed using the panel method, while structural analysis is carried out using the finite element method. The optimal design problem, aiming to find the shape and dimensions of the structure that minimize wing weight and maximize Lift-to-Drag Ratio, is formulated as a multi-objective problem and solved using the NSGA-II algorithm. The multidisciplinarity and large number of design variables are managed through a multi-level approach: for each shape configuration, structural sizing is performed using the Fully Stressed Design (FSD) method. Surrogate Based Optimization (SBO) is used to efficiently solve the problem. The Predator MQ-1 drone wing was chosen as a case study. The optimization results demonstrated the effectiveness of the proposed approach.