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Abstract(s)
O presente documento expõe o projeto conceptual, preliminar e ensaios de desenvolvimento de projeto de uma aeronave elétrica não tripulada de grande autonomia movida a energia solar.
No projeto conceptual, mediante os requisitos da missão, foi definido o conceito da aeronave. A parte conceptual envolveu também a seleção da estrutura que melhor se ajusta à missão e os materiais constituintes da aeronave.
No Projeto preliminar é utilizado um estudo paramétrico, mostrando diversas soluções de dimensionamento da aeronave, que tornam possível o cumprimento da missão. Para a elaboração do estudo paramétrico é necessário uma estimativa inicial de peso da aeronave e a escolha dos sistemas (sistema propulsivo e sistema de comando). Além de a estimativa inicial ser importante para o estudo paramétrico, também serviu para uma comparação da aeronave projetada com a construída. Perante o estudo paramétrico, que estão mais relacionados com os requisitos de voo, foi selecionado o ponto de projeto.
Estando decidida a geometria e escolhido o ponto de projeto da aeronave, realizaram-se ensaios construtivos e dimensionamento estrutural da aeronave. Os ensaios construtivos tiveram o objetivo de verificação do método de construção da estrutura decidida. O dimensionamento estrutural teve como finalidade a validação da estrutura da aeronave projetada. Para uma avaliação do desempenho de voo do UAV foi construído um pré-protótipo com a mesma geometria mas diferentes materiais. Do ensaio de voo do pré-protótipo verificou-se, pela observação do desempenho, que este se aproximou daquilo que era esperado. Para o ensaio de voo em conjunto com a estrutura projetada da aeronave foi construída a asa do protótipo. Em termos de desempenho a asa do protótipo revelou-se semelhante à do pré-protótipo. Relativamente à estrutura da asa do protótipo, esta comprovou o dimensionamento e ensaios anteriormente realizados.
The present document outlines the Conceptual, Preliminary design and developing tests of aircraft project for a solar long endurance unmanned air vehicle. In conceptual design, considering the mission requirements, was defined for the aircraft. The conceptual phase also involved the structure selection that best adjusts to aircraft mission and its materials. In the preliminary design phase was used a parametric study, showing several solutions for aircraft sizing, that accomplishes the mission requirements. To prepare the parametric study an initial weight estimate and systems selection (propulsion system and control system) was required. The initial weight estimate was very important for the parametric study, and it was also used for comparing the aircraft built with the estimate. Observing the parametric study parameters that are mostly related with aircraft requirements, the design point was selected. Once decided the final geometry and design point, constructive tests and structural sizing were made. The main issue of constructive tests was to verify the structure’s manufacturing method. The main goal of structural sizing was to validate the selected structure. In order to evaluate the aircraft performance, a pre-prototype was built, with the same geometry but different materials. The flight tests of this pre-prototype, by observation, revealed the expected aircraft performance. For designed structure tests, the prototype wing was built. This new wing revealed similar performance as pre-prototype wing. The prototype wing structure performed according to the structural sizing and tests results previously made.
The present document outlines the Conceptual, Preliminary design and developing tests of aircraft project for a solar long endurance unmanned air vehicle. In conceptual design, considering the mission requirements, was defined for the aircraft. The conceptual phase also involved the structure selection that best adjusts to aircraft mission and its materials. In the preliminary design phase was used a parametric study, showing several solutions for aircraft sizing, that accomplishes the mission requirements. To prepare the parametric study an initial weight estimate and systems selection (propulsion system and control system) was required. The initial weight estimate was very important for the parametric study, and it was also used for comparing the aircraft built with the estimate. Observing the parametric study parameters that are mostly related with aircraft requirements, the design point was selected. Once decided the final geometry and design point, constructive tests and structural sizing were made. The main issue of constructive tests was to verify the structure’s manufacturing method. The main goal of structural sizing was to validate the selected structure. In order to evaluate the aircraft performance, a pre-prototype was built, with the same geometry but different materials. The flight tests of this pre-prototype, by observation, revealed the expected aircraft performance. For designed structure tests, the prototype wing was built. This new wing revealed similar performance as pre-prototype wing. The prototype wing structure performed according to the structural sizing and tests results previously made.
Description
Keywords
Desenvolvimento de Projeto Ensaios Construtivos Ensaios Estruturais Estudo Paramétrico Pré-Protótipo Projeto Conceptual Projeto Preliminar Protótipo.