UFU - Universidade Federal de UberlândiaTrabalho de Conclusão de Curso (Graduação)This work presents the conceptual design of two hybrid aircrafts (four and six passengers) and the structural and aeroelastic analyses for the wing and empennages. The requirements in the conceptual phase were established by the aeronautical design competition held annually by the American Institute of Aeronautics and Astronautics (AIAA). The initial characteristics and geometries of a conventional aircraft were estimated through the study of historical trends. Then, the hybridization characteristics were evaluated using the series architecture, which affects mainly the range equations and the definition of the propulsive system elements that better fit the project, e. g., the internal combustion engine and batteries. To explore the multidisciplinary characteristics of the aircraft development, it was implemented an optimization procedure based on a genetic algorithm fully integrated with an aerodynamic module with performance and stability constraints, searching for the best values of the geometrical design variables. After finishing the conceptual design, the structural evaluation of wing and empennages (horizontal and vertical) was performed considering only static loads, but the failure index and the buckling instability were checked. The evaluated loads were extracted from aerodynamic models at the extreme conditions of flight envelope presented in V-n diagrams. First, the structural components were defined in aluminum 7050-T651 and later using composite material, specifically the carbon-epoxy Hexcel 8552 NMS 128/2. Additionally, only the aeroelastic analysis for the wing was evaluated, because in this work the fuselage analysis wasn't done. The results showed no flutter speed and no divergence phenomena within the aircraft's flight envelope, which is justified by the torsional rigidity obtained in the main box structure.