Projeto de veiculo aéreo não tripulado baseado em efeito Magnus

• Autor(a) principal: Rosa, Victor Stafy Megda
• Data de Publicação: 2017
• Tipo de documento: Trabalho de conclusão de curso
• Idioma: por
• Título da fonte: Repositório Institucional da UFU
• Texto Completo: https://repositorio.ufu.br/handle/123456789/20738
• topic: Efeito Magnus; VANT; Engenharia Aeronáutica; Fluidodinâmica Computacional; Análise de Estabilidade; Magnus Effect; UAV; Aeronautical Engineering; CFD; Stability Analysis; CNPQ::ENGENHARIAS::ENGENHARIA AEROESPACIAL

This research evaluates an aircraft type that was already tested in the past, the Fletter plane, but it never entered the aerospace industry, due to many factors, principally because of the high costs. Instead of the test done in 1930, with a manned aircraft, the research focused on the use of Flettner rotor on a mini-UAV. The first thing done on this research was to validate the results with data from the literature, after this a sensitivity analysis on the boundary of the fluid domain was performed, and also a grid-dependence study. The software used in the simulations was STAR-CCM+. After the validation of the first results, the UAV project began. To start the project was done a research on the spinning cylinder, calculating the drag, lift and pitching moment of it for some values of velocity ratio, after that it was investigated the influence of the aspect ratio in the forces and moments generated by the cylinder, as well the use of end-plates and spanwise discs, and finally, after the end of this investigation, the best cylinder for the mission was reached. After the spinning cylinder study the fuselage project started, the project took into account the aerodynamic drag, the components internal to the aircraft and the payload. After this was performed the flight dynamics analysis, the tail and the control surfaces were projected, assuring the stability and control of the vehicle on the flight envelope. Finally, the complete aircraft was simulated, on these simulations were done some modifications to make improvements on the flight quality as the insertion and placing of the ailerons and also the modification of the CG position. After this was possible to make a final flight dynamics analysis and define the flight quality and performance. After the end of this project, it was made the construction of the prototype, with low costs materials.