Otimização Bi-Objetivo do projeto conceitual de aeronaves de baixo número de Reynolds utilizando algoritmos genéticos

Abstract

Aircraft conceptual design constitutes the initial phase of aircraft development, in which numerous potential configurations are tested to identify the concept that best meets the project requirements. This process is both time-consuming and labor-intensive when conducted through traditional methods that rely on multiple human iterations. One of the most effective techniques to expedite this stage involves applying a design optimization routine that can determine the ideal concept with greater accuracy and shorter time cost, through the optimization of an objective function and established constraints. In this context, the present study aims to develop a bi-objective optimization model applied to the conceptual design of a low Reynolds number aircraft. The established objectives are to maximize the maximum takeoff and minimize the empty weight. A total of nine design variables were included in the optimization process, representing the selection of the airfoil, propulsive system, and wing’s geometric variables. Each configuration is evaluated through a routine that integrates the aerodynamic analyses of the Athena Vortex Lattice software with an algorithm that simulates takeoff performance. The results showed the capability of the bi-objective optimization model to identify configurations that meet the design requirements while delivering high performance. Additionally, the model demonstrated low computatuinal cost, enabling the evaluation of more than 1500 solutions per hour. The optimal solution identified successfully met the objectives established for the SAE Brasil AeroDesign competition, contributing to the project’s competitiveness and highlighting the efficiency of the applied approach.