Hierarchical models for aircraft joints analyses

• Ano de defesa: 2022
• Autor(a) principal: Marco Túlio dos Santos
• Tipo de documento: Dissertação
• Tipo de acesso: Acesso aberto
• Idioma: eng
• Instituição de defesa: Universidade Federal de Minas Gerais; Brasil; ENG - DEPARTAMENTO DE ENGENHARIA ESTRUTURAS; Programa de Pós-Graduação em Engenharia de Estruturas; UFMG
• Palavras-chave em Português: Hierarchical models; Aircraft joints; Finite element method; Aircraft fastener; Engenharia de estruturas; Aeronaves; Método dos elementos finitos
• Link de acesso: http://hdl.handle.net/1843/63927

The procedure of structural design for aircraft parts is widely known and discussed in the academy and in the industry, although it has been improved along the time. It is based on a detailed process of aerodynamics loads study coupled or not with specifications required by regulatory agencies. Further, several interactions of analysis are done to define the critical stress state of the structure submitted to load conditions, because it is a complex structure that needs to be often improved and updated (considering the requirement of assembly/disassembly simplicity). There are several components in an aircraft attached to each other by the use of fasteners, rivets or nuts made of different materials (aluminum, steel, titanium among others). In fact, it is not to easy to obtain stress state of the aeronautical structure for the actual loading conditions and also it is also difficult to calculate the load acting on each one of the joints. Several studies were already performed in order to obtain the correct understanding of how actual loads is distributed through the joints. The present work aims to calculate the load acting in aircraft joints (focusing in spar and skin regions), considering three types of modeling approach, being each one with a such level of detail and then understand the differences in the structural response. Furthermore three types of joint configuration will also be analyzed, in which it will be considered the fasteners distributed in a single and double row and also is used staggered configuration considering the same distance between the fasteners for all models. Finite Element models made using Hyperworks and Femap software were performed and they are going to be solved using Nastran solver. The study proposed has shown a good correlation between the models with low and intermediate level of detail, besides the model with low level of detail has shown a conservative approach to calculate aircraft joints during the product development process.