Integrated Design Tool for Conceptual Design of Aerodynamic Surfaces Based on Multi-objective Genetic Algorithm

This study aims to provide a robust and rapid design tool to be used in the sizing of the aerodynamic surfaces of an air vehicle. This tool aims to find a globally optimum aerodynamic configuration during the considered conceptual design phase. The considered tool is composed of an aerodynamic prediction module, a three-degree of freedom trajectory simulation module, and a multi-objective genetic optimization algorithm (MOGA). A robust interactive objective-normalization approach is applied. The tool is tested, and the designed fin dimensions and aerodynamic characteristics of the missile are compared with an available designed one. The design case study introduced, and the results show that the proposed tool introduces a robust aerodynamic configuration that can be introduced to the preliminary design phase. That is thanks to the used reliable aerodynamic prediction code results as well as multi-objective optimization of trajectory parameters using a suitable normalization technique.