Loading...
Publication
Projeto estrutural de um Veículo Aéreo Não Tripulado com uma célula de combustível de hidrogénio
| Name: | Description: | Size: | Format: | |
|---|---|---|---|---|
| 8.64 MB | Adobe PDF |
Authors
Advisor(s)
Abstract(s)
Recentemente, o hidrogénio tem vindo a ganhar relevância no contexto nacional como fonte de armazenamento de energia renovável. Segundo a “Visão Estratégica para o Plano de Recuperação Económica de Portugal 2020-2030”, o hidrogénio é fundamental para atingir o objetivo político de neutralidade
carbónica e sustentabilidade. Neste sentido, a Força Aérea Portuguesa (FAP) criou um projeto para um Veículo Aéreo Não-Tripulado (VANT) elétrico, com hidrogénio como fonte de armazenamento de energia, em detrimento das baterias de lítio. A transformação de energia é efetuada por uma célula de combustível de hidrogénio. A presente dissertação tem como objetivo o projeto estrutural do VANT. Primeiramente, elaborou-se o projeto conceptual, no qual se definiu a geometria da aeronave e respetivo envelope de voo, para determinar o fator de carga de projeto. Adicionalmente, efetuou-se um estudo de mercado para avaliar a percentagem de peso estrutural expectável para um VANT deste género. No projeto preliminar definiu-se os materiais compósitos usados e respetivas propriedades mecânicas, a partir das quais se calculou os laminados necessários numa longarina preliminar. Posteriormente, avaliou-se a distribuição dos componentes pela aeronave, calculando o peso total do VANT e respetivo centro de gravidade. Finalmente, o projeto detalhado realizou-se através de modelação em Desenho Assistido por Computador (CAD), a partir da qual se efetuou uma Análise de Elementos Finitos (FEA) para confirmar se os laminados atribuídos à estrutura da asa cumpriam os requisitos estipulados.
Verificou-se que a configuração selecionada suporta a condição de carga crítica, estando o peso estrutural dentro do previsto.
Recently, hydrogen has gained relevance in the national context, as a source of storage of renewable energy. According to the “Strategic Vision for Portugal’s Economic Recovery Plan 2020-2030”, hydrogen is essential to achieve the political objective of carbon neutrality and sustainability. In this sense, the Portuguese Air Force (FAP) created a project for an Unmanned Aerial Vehicle (UAV), with hydrogen as a source of energy storage, in detriment to lithium batteries. Energy transformation is carried out by an hydrogen fuel cell. This dissertation aims at the structural design of the UAV. Firstly, the conceptual design was made, in which the aircraft geometry and its flight envelope were defined to determine the design load factor. Additionally, a market study was carried out to assess the expected structural weight percentage for a UAV of this type. In the preliminary design, the composite materials and their mechanical properties were defined, from which the necessary laminates for a preliminary spar were calculated. Subsequently, the distribution of components throughout the aircraft was evaluated, calculating the total weight of the UAV and its center of gravity. Finally, the detailed design was carried out through modeling in Computer Aided Design (CAD), from which a Finite Element Analysis (FEA) was produced to confirm whether the laminates assigned to the structure met the requirements stipulated. It was found that the selected configuration supports the critical load condition, with the structural weight being within the expected values.
Recently, hydrogen has gained relevance in the national context, as a source of storage of renewable energy. According to the “Strategic Vision for Portugal’s Economic Recovery Plan 2020-2030”, hydrogen is essential to achieve the political objective of carbon neutrality and sustainability. In this sense, the Portuguese Air Force (FAP) created a project for an Unmanned Aerial Vehicle (UAV), with hydrogen as a source of energy storage, in detriment to lithium batteries. Energy transformation is carried out by an hydrogen fuel cell. This dissertation aims at the structural design of the UAV. Firstly, the conceptual design was made, in which the aircraft geometry and its flight envelope were defined to determine the design load factor. Additionally, a market study was carried out to assess the expected structural weight percentage for a UAV of this type. In the preliminary design, the composite materials and their mechanical properties were defined, from which the necessary laminates for a preliminary spar were calculated. Subsequently, the distribution of components throughout the aircraft was evaluated, calculating the total weight of the UAV and its center of gravity. Finally, the detailed design was carried out through modeling in Computer Aided Design (CAD), from which a Finite Element Analysis (FEA) was produced to confirm whether the laminates assigned to the structure met the requirements stipulated. It was found that the selected configuration supports the critical load condition, with the structural weight being within the expected values.
Description
ALF/ENGAER 139432-A Paulo Jorge Pinto Sá.
Júri: Presidente: COR/ENGAER Luís António Monteiro Pessanha;
Orientador: MAJ/ENGAER Luís Filipe da Silva Félix; Prof. André Calado Marta;
Vogal: Prof. Pedro Vieira Gamboa
Keywords
FAP VANT CAD FEA Materiais compósitos UAV Composite materials
Citation
Publisher
Academia da Força Aérea