O trabalho visou realizar um estudo sobre o comportamento mecânico e de inflamabilidade de estruturas aeronáuticas de interior fabricadas a partir de compósitos reforçados por fibras naturais, especificamente compósitos de resina fenólica com fibras de algodão e de sisal, verificando assim, a possibilidade de substituir compósitos sintéticos. Num primeiro momento, análises experimentais foram executadas para determinar as propriedades mecânicas dos materiais. Em seguida, análises computacionais foram realizadas, empregando as propriedades referentes aos compósitos sintéticos e reforçados por fibras naturais, utilizando critérios de falha e tendo como referência o desempenho do compósito sintético para uma dada estrutura aeronáutica de interior. Além disso, foram efetuadas análises do seu comportamento quanto à inflamabilidade. A incorporação de retardantes de chama foi necessária para que os compósitos reforçados por fibras naturais atendessem aos requisitos de certificação aeronáutica. Após o processo de aditivação, observou-se um aumento do módulo de elasticidade à flexão (55% para o compósito de algodão, 16% para o compósito de sisal) e a diminuição da tensão de ruptura à flexão dos compósitos reforçados por fibras naturais analisados (45% para o compósito de algodão, 55% para o compósito de sisal). No entanto, com o aumento da espessura da estrutura aeronáutica adotada (5,2% para o compósito de algodão, 10,7% para o compósito de sisal), conclui-se que a substituição do compósito sintético pelo natural seria viável. Isto acarretaria em um aumento de massa em 6,2%, caso a estrutura fosse fabricada em compósito reforçado por fibra de sisal. Finalmente, constatou-se que a fração mássica de aditivo utilizada tem grande potencial de otimização e, que a eficiência dos compósitos reforçados por fibras naturais ainda pode ser melhorada. / This dissertation has aimed to study the mechanical behavior and the flammability of aeronautical interior structures manufactured from composites reinforced by natural fibers, specifically phenolic resin and cotton and sisal fibers composites, verifying the possibility of synthetic composites replacement. Firstly, experimental analyses were performed to determine the mechanical properties of the materials. Then, computational analyses were carried out, using properties of synthetic composites and composites reinforced by natural fibers. Also, failure criteria were applied, considering the synthetic composite performance of an interior aeronautical structure as reference. Furthermore, the behavior regarding flammability was analyzed. The addition of flame retardants was necessary for the composites reinforced by natural fibers in order to attend the aeronautical certification requirements. After the addition of flame retardants, an increase in the flexural modulus of elasticity (55% for the cotton composite, 16% for the sisal composite) and a decrease in the flexural stress at break (45% for the cotton composite, 55% for the sisal composite) were observed. However, with an increase of the thickness of the aeronautical structure (5.2% for the cotton composite, 10.7% for the sisal composite), it was concluded that the replacement would be feasible, which would lead to a increase of the mass equal 6.2% for the sisal fiber composite. Finally, it was evidenced that the used flame retardant mass fraction has a great potential for optimization and that the natural composites efficiency can be improved.

O trabalho visou realizar um estudo sobre o comportamento mecânico e de inflamabilidade de estruturas aeronáuticas de interior fabricadas a partir de compósitos reforçados por fibras naturais, especificamente compósitos de resina fenólica com fibras de algodão e de sisal, verificando assim, a possibilidade de substituir compósitos sintéticos. Num primeiro momento, análises experimentais foram executadas para determinar as propriedades mecânicas dos materiais. Em seguida, análises computacionais foram realizadas, empregando as propriedades referentes aos compósitos sintéticos e reforçados por fibras naturais, utilizando critérios de falha e tendo como referência o desempenho do compósito sintético para uma dada estrutura aeronáutica de interior. Além disso, foram efetuadas análises do seu comportamento quanto à inflamabilidade. A incorporação de retardantes de chama foi necessária para que os compósitos reforçados por fibras naturais atendessem aos requisitos de certificação aeronáutica. Após o processo de aditivação, observou-se um aumento do módulo de elasticidade à flexão (55% para o compósito de algodão, 16% para o compósito de sisal) e a diminuição da tensão de ruptura à flexão dos compósitos reforçados por fibras naturais analisados (45% para o compósito de algodão, 55% para o compósito de sisal). No entanto, com o aumento da espessura da estrutura aeronáutica adotada (5,2% para o compósito de algodão, 10,7% para o compósito de sisal), conclui-se que a substituição do compósito sintético pelo natural seria viável. Isto acarretaria em um aumento de massa em 6,2%, caso a estrutura fosse fabricada em compósito reforçado por fibra de sisal. Finalmente, constatou-se que a fração mássica de aditivo utilizada tem grande potencial de otimização e, que a eficiência dos compósitos reforçados por fibras naturais ainda pode ser melhorada. / This dissertation has aimed to study the mechanical behavior and the flammability of aeronautical interior structures manufactured from composites reinforced by natural fibers, specifically phenolic resin and cotton and sisal fibers composites, verifying the possibility of synthetic composites replacement. Firstly, experimental analyses were performed to determine the mechanical properties of the materials. Then, computational analyses were carried out, using properties of synthetic composites and composites reinforced by natural fibers. Also, failure criteria were applied, considering the synthetic composite performance of an interior aeronautical structure as reference. Furthermore, the behavior regarding flammability was analyzed. The addition of flame retardants was necessary for the composites reinforced by natural fibers in order to attend the aeronautical certification requirements. After the addition of flame retardants, an increase in the flexural modulus of elasticity (55% for the cotton composite, 16% for the sisal composite) and a decrease in the flexural stress at break (45% for the cotton composite, 55% for the sisal composite) were observed. However, with an increase of the thickness of the aeronautical structure (5.2% for the cotton composite, 10.7% for the sisal composite), it was concluded that the replacement would be feasible, which would lead to a increase of the mass equal 6.2% for the sisal fiber composite. Finally, it was evidenced that the used flame retardant mass fraction has a great potential for optimization and that the natural composites efficiency can be improved.

Les ingénieurs sont constamment mis au défi de concevoir des avions plus légers et moins polluants. En même temps, ils se doivent de respecter un certain nombre de critères de dimensionnement établis pour assurer l'intégrité des structures aéronautiques. Pour répondre à ce double défi, les chercheurs du milieu industriel et académique travaillent à l'unisson pour constamment repousser les limites du savoir scientifique. Ces collaborations aboutissent notamment au développement de nouveaux outils mathématiques, numériques, expérimentaux et de production.On trouve de nombreuses pièces métalliques parmi les composants aéronautiques les plus critiques, comme les trains d’atterrissages, les arbres moteurs ou les chapes. Ces structures subissent des chargements extrêmes de par leur environnement thermique ou leur intense sollicitation mécanique ponctuelle ou cyclique. Pour ces structures élastoplastiques, la ruine peut généralement être causée par l'apparition et la propagation de fissures, ou l'émergence d'instabilités locales, comme la localisation de la déformation plastique, ou d'instabilités globales, comme le flambement.Dans les travaux présentés dans ce manuscrit, nous nous sommes intéressés à la détection d’instabilités locales et globales dans des structures élastoplatiques en grandes déformations. Alors qu'elles sont classiquement considérées indépendamment, nous avons fait le choix d'étudier les deux types d'instabilités simultanément pour mieux comprendre la compétition entre ces deux phénomènes. Pour ce faire, plusieurs développements analytiques sont présentés et fondés sur le critère de stabilité de Hill (1958) et le critère de localisation de la déformation de Rice (1976), ainsi que la proposition d'une nouvelle méthode d'"analyses de stabilité affaiblie" permettant d'investiguer la sensibilité aux types de conditions limites imposées. Tous ces critères ont été implémentés dans le code de calcul par éléments finis Zset, ce qui nous a permis, entre autres, d'analyser l’apparition d'instabilités élastoplastiques dans différentes éprouvettes de traction/torsion, des tubes en torsion et une chape en traction. / Aeronautical engineers are constantly challenged to provide lighter structures in order to reduce fuel consumption, and thus the environmental impact and flight costs. At the same time, the design of aeronautical structures is subjected to strict regulation aimed at ensuring the integrity of the aircraft and the safety of the passengers. To tackle this challenge, the limits of structural and material mechanics are consistently explored which in turn leads to the development of new, mathematical, numerical, experimental and manufacturing tools.There are numerous metallic parts in the most critical aeronautical structures, like landing gears, engine shafts, or mechanical lugs. These parts are subjected to extreme loading conditions due to the thermal environment or to the intense mechanical ultimate or cyclic loading. The failure of these elastoplastic structures is generally caused by the initiation and propagation of cracks or by the emergence of local instabilities, such as plastic strain localization, or global instabilities, such as buckling.In the present work, we focus on the detection of local and global elastoplastic instabilities in a finite deformation framework. While they are generally studied separately, it was chosen to study both phenomena together in order to analyze and better understand the competition between localization and buckling in elastoplastic structures. For this purpose, multiple analytical developments are presented founded on Hill's global stability criterion (1958) and Rice's strain localization criterion (1976). The new "weakened stability analysis" has been introduced in order to analyze the sensitivity to the type of prescribed boundary conditions. All these criteria have been implemented in the finite element software Zset, which allowed us to analyze the emergence of elastoplastic instabilities in various experimental samples, tubes loaded in torsion, and a lug loaded in tension.

L’objectif de cette thèse est de réaliser un système de Contrôle Santé Intégré des structures aéronautiques (CSI ou SHM) autonome et à double-fonctionnalité. Ce système doit être en mesure d’assurer son autonomie énergétique tout en réalisant les tâches de détection et de localisation des endommagements. Latechnique retenue pour alimenter ce système est basée sur la récupération d’énergie vibratoire par transducteurs piézoélectriques SHM collés. Durant ces travaux, un modèle analytique complet de la chaîne de récupération d’énergie vibratoire a d’abord été créé. Ce modèle, validé par la Méthode des ÉlémentsFinis (MEF), permet d’améliorer le rendement du système en déterminant les dimensions, les locali-sations et le type de matériau piézoélectrique idéals des transducteurs. Ce modèle a ensuite été étendu à une configuration plus représentative des conditions de vibrations d’une structure en vol. Une bonne corrélation entre les résultats provenant du modèle prédictif et les essais sur un banc de mesures a étémise en évidence. Une puissance de 1.67mW a été récupérée et la capacité large bande des transducteurs a été vérifiée. L’application de la récupération d’énergie au contrôle de structures composites en cours d’assemblage sur les lignes de production a également été étudiée. Dans ce cas, un transducteur stratégiquement localisé et alimenté par une source de tension disponible génère des ondes de Lambdans la structure afin de pallier l’absence de vibrations naturelles. Un réseau de transducteurs secondaires disséminés sur cette structure récupère et convertit cette énergie vibratoire en énergie électrique. Une puissance de 7.36 mW a été récoltée et ce système a été en mesure de détecter une chute d’outil sur le composite et d’éclairer de façon autonome une diode électroluminescente (DEL) simulant ici la consommation de la transmission sans fil de l’information. / The aim of this thesis is to develop a self-powered Structural Health Monitoring (SHM) system for aeronautical applications. This system has to be fully autonomous and has to be able to carry out SHM tasks such as damage detection and location. The energetic autonomy of the system is provided by a vibrational energy harvesting technology using bonded SHM piezoelectric transducers. In this document,an analytical model of the energy harvesting process has been proposed. This model, validated by the Finite Element Method (FEM), allows the optimization of the energy harvesting system by determining the ideal type of transducers as well as their optimal dimensions and locations. Then, this model has been applied to a configuration aiming to be more representative of the in-flight vibrations experienced by a structure. Good agreement has been found between the analytical simulation and the experimental measurements. A power of 1.67mW has been harvested and the wideband capability of the transducers has been verified. Afterwards, the possibility of using the vibrational energy harvesting technology to control composite structures on assembly line has been investigated. For this case study, a transducer strategically located nearby an available power supply generates Lamb waves throughout the structure to tackle the absence of natural vibration. The remaining sensors, spread all over the structure, convertthe mechanical vibrations into electrical power. Using this technology, a power of 7.36mW has been harvested. Finally, this SHM system has also been able to detect a tool drop on the composite structure and to light simultaneously and autonomously a light-emitting diode (LED) simulating the consumption required to transmit the information wirelessly.

O presente trabalho consiste basicamente num estudo experimental de juntas híbridas metal-compósito unidas mecanicamente por fixadores. Foram analisadas juntas fabricadas através de uma chapa metálica de titânio unida a uma placa em compósito de fibra de carbono e resina epóxi por fixadores de monel. As juntas avaliadas são juntas simples (\"single lap joint\"), ou seja, as mesmas foram submetidas ao simples cisalhamento. Antes, porém, dos ensaios das juntas, foram fabricados corpos-de-prova (CDPs) do compósito seguindo as especificações das normas ASTM D3039 e ASTM D3518. Os ensaios de tração e cisalhamento dos CDPs de compósito possibilitaram a determinação de propriedades mecânicas, bem como de valores de resistência. Sob posse das propriedades e resistência média, foram executadas simulações computacionais via Método dos Elementos Finitos com o intuito de prever o comportamento mecânico das juntas a serem ensaiadas seguindo a norma ASTM D5961 e, assim, delinear estratégias para os ensaios. Os ensaios das juntas foram realizados, possibilitando assim a avaliação do comportamento mecânico de juntas híbridas e de seus mecanismos de falha. Por fim, as conclusões e as perspectivas para trabalhos futuros foram apresentadas. / This work consists on an experimental investigation of hybrid joints (metal-composite) joined by fasteners. For this work, hybrid joints of titanium joined to composite (carbon fiber with epoxy resin) by monel fasteners were manufactured. Only single lap joints were investigated. However, before manufacturing specimens of joints, composite specimens were tested following the ASTM D3039 e ASTM D3518. The tensile and shear tests provided the mechanical properties and strength values of the composite. Finite element analyses of the hybrid joints were carried out, using average mechanical properties and strength values. These simulations followed the specifications of ASTM D5961 in order to predict the mechanical behavior of the joints during the experimental tests, as well as, provide a good strategy for the test setup. The experimental tests were carried out, observing the mechanical behavior and failure mechanisms of the hybrid joints. Finally, the conclusions and perspective of future works were showed.

O presente trabalho consiste basicamente num estudo experimental de juntas híbridas metal-compósito unidas mecanicamente por fixadores. Foram analisadas juntas fabricadas através de uma chapa metálica de titânio unida a uma placa em compósito de fibra de carbono e resina epóxi por fixadores de monel. As juntas avaliadas são juntas simples (\"single lap joint\"), ou seja, as mesmas foram submetidas ao simples cisalhamento. Antes, porém, dos ensaios das juntas, foram fabricados corpos-de-prova (CDPs) do compósito seguindo as especificações das normas ASTM D3039 e ASTM D3518. Os ensaios de tração e cisalhamento dos CDPs de compósito possibilitaram a determinação de propriedades mecânicas, bem como de valores de resistência. Sob posse das propriedades e resistência média, foram executadas simulações computacionais via Método dos Elementos Finitos com o intuito de prever o comportamento mecânico das juntas a serem ensaiadas seguindo a norma ASTM D5961 e, assim, delinear estratégias para os ensaios. Os ensaios das juntas foram realizados, possibilitando assim a avaliação do comportamento mecânico de juntas híbridas e de seus mecanismos de falha. Por fim, as conclusões e as perspectivas para trabalhos futuros foram apresentadas. / This work consists on an experimental investigation of hybrid joints (metal-composite) joined by fasteners. For this work, hybrid joints of titanium joined to composite (carbon fiber with epoxy resin) by monel fasteners were manufactured. Only single lap joints were investigated. However, before manufacturing specimens of joints, composite specimens were tested following the ASTM D3039 e ASTM D3518. The tensile and shear tests provided the mechanical properties and strength values of the composite. Finite element analyses of the hybrid joints were carried out, using average mechanical properties and strength values. These simulations followed the specifications of ASTM D5961 in order to predict the mechanical behavior of the joints during the experimental tests, as well as, provide a good strategy for the test setup. The experimental tests were carried out, observing the mechanical behavior and failure mechanisms of the hybrid joints. Finally, the conclusions and perspective of future works were showed.