Thesis (M.A.)--University of North Carolina at Chapel Hill, 2003. / Includes bibliographical references (leaves 123-127).

Thesis (M.S.)--University of British Columbia, 2004. / Includes bibliographical references (leaves 88-98).

Thesis (Ph. D.)--Cornell University, Ithaca, N.Y., 1910. / Reprinted from the American journal of psychology, v. 17, Jan. 1906, and v. 19, Jan. 1908.

Thesis (M.S.)--University of Texas at El Paso, 2008. / Title from title screen. Vita. CD-ROM. Includes bibliographical references. Also available online.

Ce travail a porté sur l’influence d’entailles micrométriques sur la tenue en fatigue à grand nombre de cycles d’un alliage de titane et la comparaison avec un cas de fretting-fatigue. Des études préliminaire sont montré que des entailles micrométriques pouvaient reproduire les champs de contraintes d’essais de fretting-fatigue. Le projet COGNAC dirigé par Safran Aircraft Engines a été créé dans l’objectif d’évaluer la faisabilité d’un modèle unique capable de simuler la tenue en fatigue de pièces subissant des sollicitations de fretting ou de fatigue en présence d’entailles. Le cadre expérimental de cette thèse est limité à la partie du projet traitant des entailles. Afin d’avoir le même état de préparation de surface, les micro-entailles et les surfaces des éprouvettes de fretting fatigue sont usinées par meulage. Afin de reproduire les gradients de contraintes observés localement pour des chargements de fretting-fatigue, des entailles en V avec des rayons compris entre 50 μm à 500 μm ont été choisies.L’étude du taux de triaxialité et du cisaillement a permis de définir une géométrie d’éprouvette de comparaison avec le fretting fatigue qui comporte 2 entailles en V inclinées en face à face. Trois campagnes expérimentales de fatigue à grand nombre de cycles ont été menées. La première sur des éprouvettes lisses meulées afin d’obtenir une limite de fatigue de référence sans concentration de contraintes. La seconde sur des éprouvettes avec une entaille non inclinée ayant une profondeur de500 μm afin d’étudier les effets du rayon de fond d’entaille sur la limite de fatigue. La dernière est une campagne sur les éprouvettes avec 2 entailles inclinées qui permettent de reproduire les champs de contrainte des essais de fretting. Les premiers stades de fissuration ont été étudiés. Les facettes de pseudo clivage, la présence d’un premier stade de fissuration et les amorçages multiples en fond d’entaille ressemblent à ce qui peut être vu sur des essais de fretting. Par contre la présence de fissures non propageantes en fond d’entaille sous la limite de fatigue n’a pas pu être démontrée, alors que ces fissures non propageantes sont observables sur les essais de fretting-fatigue. Les sites d’amorçages et les mécanismes des premiers endommagements semblent être pilotés par les zones affectées par le meulage. Enfin trois critères de fatigue ont été utilisés afin de tenter de reproduire nos résultats expérimentaux. L’approche basée sur la théorie du gradient –avec un gradient local et un impact affine du gradient- et celle basée sur la théorie de la distance critique ont fourni des résultats corrects sur les éprouvettes entaillées mais ne peuvent faire le lien avec les éprouvettes sans concentrations de contraintes. Enfin, l’approche probabiliste utilisée a produit des résultats très proches des résultats expérimentaux à la fois sur des éprouvettes lisses et des micro-entailles. La comparaison des résultats expérimentaux montrent que le champ de contrainte de Crossland proche de la surface d’amorçage du fretting-fatigue est proportionnel à celui proche d’un fond d’entaille dans le cas d’une éprouvette avec 2 entailles en face à face. Le niveau de la sollicitation des 2 essais diffère localement d’environ20%. Dans la suite des travaux, il serait particulièrement intéressant de relancer une campagne de comparaison entre fretting et entailles en utilisant un critère probabiliste pour dimensionner les essais afin de proposer une méthodologie commune de prise en compte des concentrations de contraintes dans les cas de fretting-fatigue et de concentrateurs géométriques sollicités en fatigue. / This study is about the influence of micro-notches on the high cycle fatigue behavior of a Ti64 alloy and the comparison with similar fretting fatigue tests. Preliminary studies showed that fretting-fatigue stress fields can be reproduced by micro-notched. The COGNAC project leaded by Safran Aircraft Engines was built to verify if a unique model can reproduce both fretting-fatigue and notched samples fatigue tests. The scope of this experimental study is limited to the notched samples. In this PHD thesis, the notches are grinded and the results are compared with fretting-fatigue tests on grinded surfaces. V-notched with notch root radius from 50 to 500 μm were chosen to reproduce the stress gradient of fretting-fatigue tests. A geometry with two inclined notches facing each other allows to reproduce shear stress and stress triaxiality from fretting-fatigue tests. Three different experimental studies were performed. First on un-notched specimens with a grinded surface state to produce a reference fatigue limit for grinded surface state without stress concentration. The second study the notch root radius effect on the fatigue limit with samples with one non-inclined notch of 500 μm of depth. The last one is a series of fatigue tests on samples with two inclined notches that reproduce the stress distribution of fretting-fatigue tests. Pseudo-cleavage facets, multi cracks initiations in the notch root and the presence of two propagation stages is similar to the fretting-fatigue tests mechanisms. However, non propagating cracks were not observe at the notch root while many of them were present during the fretting-fatigue test. The initiation sites and the early stages of propagation seem to be controlled by grinded affected areas. Finally, three fatigue criteria were used to try to reproduce the experimental results. The criteria based on the critical distance theory and gradient theory –with a local gradient and an affine effect of the gradient term- can reproduce the fatigue limits of notched samples but fail to predict both notched and un-notched specimen fatigue limits with a unique data set. The third one is a probabilistic criterion which success to predict the experimental fatigue limits not only of notched samples but also smooth ones. The comparisons between the experimental results of the fatigue on the specimens with two inclined notches and the fretting-fatigue shows a difference of 20%. The distribution of the Crossland stress is quite similar. In the future, it would be useful to make a new comparison between fretting-fatigue and fatigue on notches using the probabilistic criterion to design the tests. This new comparison could lead to the proposal of a unique methodology to take into account the fretting-fatigue and the fatigue on stress concentrators.

Made available in DSpace on 2014-06-11T19:27:12Z (GMT). No. of bitstreams: 0 Previous issue date: 2011-02-08Bitstream added on 2014-06-13T19:35:00Z : No. of bitstreams: 1 bonora_rg_me_guara.pdf: 4519447 bytes, checksum: b9da7f058f4c7f84708e972b68f012ba (MD5) / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / No desenvolvimento de materiais para aplicação aeronáutica estrutural, como no caso de componentes de trens de pouso, deve-se considerar que os mesmos serão submetidos a carregamentos cíclicos. Em especial, estudar a fadiga dos materiais é um parâmetro fundamental. Além disso, para o trem de pouso em operação, o estudo da corrosão é fundamental, principalmente quando se pretende utilizar novos materiais. Atualmente, materiais de alta resistência mecânica, como o aço ABNT 4340, são utilizados em diversos componentes. Devido à necessidade de alta resistência ao desgaste e à corrosão, os componentes são geralmente revestidos por cromo duro e cádmio, respectivamente. Esses tratamentos produzem resíduos, como o Cr+6 e cianetos, por exemplo, gerados após a aplicação dos revestimentos. Este projeto teve origem na necessidade da indústria aeronáutica nacional em reduzir o uso de materiais revestidos com cromo ou cádmio eletrodepositado que geram resíduos nocivos à saúde e ao meio ambiente. O material escolhido foi o aço inoxidável Custom 465, também de uso aeronáutico, pois apresenta alta resistência mecânica. Considerando os esforços sofridos pelo eixo da roda do trem de pouso, o Custom 465 foi ensaiado em fadiga axial e corrosão em névoa salina. O objetivo é comparar o comportamento do Custom 465 com o do aço ABNT 4340 cadmiado. São também analisados os resultados obtidos em microscopia óptica, para análise microestrutural, e microscopia eletrônica de varredura, para análise fractográfic / Considering material development for landing gear aircraft structural components, it should be considered that cyclic loading occurs. One important parameter for design is the fatigue of materials. The study of corrosion is also fundamental specially in the case of new materials application. Currently, high strength materials, especially AISI 4340 steel, are widely used as landing gear components. Due to the high resistance to wear and corrosion requirements, components are usually coated with hard chromium or cadmium. Treatments can produce wastes such as cyanide and Cr+6, for example, generated after the application hard chromium and cadmium coatings, which are harmful to health and environment. This project was originated from the national aircraft industry requirements to reduce the use of coated materials with electroplated chromium or cadmium that produce waste, which is harmful to health or the environment. The selected material is a Custom 465 stainless steel used in the aeronautical field due to its high mechanical strength. Considering the load sustained by the wheel axis of the landing gear, the Custom 465 is tested in axial fatigue and corrosion. The objective is to compare the behavior of the Custom 465 with plated AISI 4340 steel coated with cadmium. Fractographic analysis was conducted using optical and scanning electron microscopy

Made available in DSpace on 2014-06-11T19:27:12Z (GMT). No. of bitstreams: 0 Previous issue date: 2009-03-27Bitstream added on 2014-06-13T20:08:17Z : No. of bitstreams: 1 tonoli_cs_me_guara.pdf: 6263213 bytes, checksum: b9be92a4785ed36cad560de2367c06a8 (MD5) / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / O tubo superior do garfo suspensão é um dos componentes de grande importância no conjunto de peças que compõe uma bicicleta, pois durante a operação é submetido a carregamentos cíclicos e caso falhe pode causar acidentes ao ciclista. Este componente é confeccionado por processo de usinagem a partir de um perfil tubular extrudado em liga de alumínio Al 6013-T6. Neste trabalho foi realizado um estudo sobre o comportamento em fadiga desta liga de alumínio submetida a diferentes condições de shot peening, objetivando aumentar a resistência à fadiga do material e conseqüentemente aumentar a vida útil/segurança do componente. Para ensaiar os corpos-de-prova em perfil tubular com geometria embasada nas dimensões do tubo superior, desenvolveu-se uma metodologia especifica de ensaio. Os ensaios mostraram que o processo de fabricação de rosca por conformação mecânica aumentou consideravelmente a resistência à fadiga dessa liga em relação ao processo de fabricação por usinagem convencional. Os efeitos de concentradores de tensão como filetes de rosca usinada e defeitos superficiais são extremamente prejudiciais para a vida em fadiga da liga Al 6013-T6. Os tratamentos de shot peening realizados pela empresa Zirtec induziram um perfil significativo de tensões residuais compressivas, porém, reduziram a vida em fadiga da liga Al 6013-T6 em perfil tubular. Esse efeito foi potencializado com intensidades Almen elevadas. O aumento na vida em fadiga ocorreu apenas nos corpos-de-prova que foram lixados na superfície interna. O shot peening com esfera de vidro e intensidade Almen intermediária apresentou a maior vida em fadiga. Os resultados deste trabalho estão sendo usados para providenciar melhorias na matéria prima e como base para novos ensaios com o tubo superior. / The fork supension's steerer tube is one of component of great importance in a set that makes a bicycle, since during operation is subjected to cyclic loading and if fails may cause accident to the rider. This component is manufactured by machining processes from the extrusion tubular profile in aluminum alloy 6013-T6. This work carried out a study on the fatigue behavior of aluminum alloy subjected to different shot peening conditions, proposing to increase the fatigue strength and consequently to increase a useful life/safety of the component. To test tubular profile specimen with geometry based in steerer tube dimensions, has developed a specific methodology for testing. The tests showed that thread forming by manufacturing process, increase the fatigue strength of this aluminum alloy comparing the manufacturing process through conventional machining. The effects of concentration stress like machined thread and surface defects are extremely detrimental to fatigue life alloy AL 6013-T6. Shot peenig treatment carried out in Zirtec company induced a significant compressive residual stress profile, but decrease the fatigue life alloy Al 6013-T6 in tubular profile. This effect was strengthened with high Almen intensities. The fatigue life incresase ocurred only specimen that were polished on the inner surface. Shot peening using glass shot and intermediate Almen intensity had the greatest fatigue life. The results os this work are being used to provide improvements in primary material and as a basis for new test on the stereer tube.

Made available in DSpace on 2014-06-11T19:27:12Z (GMT). No. of bitstreams: 0 Previous issue date: 2011-02-09Bitstream added on 2014-06-13T19:35:03Z : No. of bitstreams: 1 shiino_my_me_guara.pdf: 3902027 bytes, checksum: 6b8b675f5c370e00fec9d53eaca61233 (MD5) / Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP) / O setor de transporte tem buscado materiais mais leves e resistentes para melhorar a autonomia e capacidade de seus veículos. Os materiais compósitos de carbono/epóxi têm superado as expectativas neste setor e volumes significativos já são empregados na aviação. Com a intenção de produzir peças estruturais para a área aeronáutica, esse trabalho propôs a implantação do processo RTM e produção de compósitos com potencial aplicação estrutural. O foco principal do trabalho foi o domínio total na montagem e uso do equipamento RTM para um perfeito funcionamento de forma a evitar erros de processamento. O trabalho envolveu a seleção de fibras de carbono e resina epóxi com a intenção de atingir propriedades superiores às ligas metálicas, principalmente as ligas de alumínio. Para estabelecer os parâmetros de processo a resina foi caracterizada quanto a viscosidade e propriedades físico-químicas. Para avaliar a qualidade do processamento foi utilizada a inspeção por ultrassom A-scan e C-scan e as frações volumétricas foram determinadas através da metodologia da norma ASTM D 3171-09. Já para a caracterização do compósito foram utilizados ensaios mecânicos de tração, flexão, fadiga e posterior análise fractográfica. Análise térmica foi empregada para assegurar que o material foi completamente curado. Ao todo foram avaliados dois tipos de laminados: com 4 camadas do tipo Satin Harness (5HS) com 10 camadas e quasi-isotrópico com 5 camadas / The transportation field has searched for lighter and strengthen materials to improve the autonomy and load capacity of their vehicles. Carbon/epoxy composites have overcome the expectations in this field. Appreciable volume production of structural components has been employed in aircrafts. Aiming of producing structural parts for aeronautic field, this research work focuses on the implementation of the RTM process and production of carbon/epoxy composite material. The work had the main objective on managing the assemblage and usage for a perfect operation, in the way to avoid processing errors. The research involved the right choice of carbon fibers and resin system intended to obtain higher specific properties than the metal alloys, mainly the aluminum alloys. Process parameters were established by characterizing the viscosity and physicalchemical properties. The quality assessment was performed by A-Scan and CScan ultrasonic test and volumetric fractions analysis. The volumetric analysis were performed according to the ASTM 3171-09. Besides the evaluation of material performance it was performed tensile, flexure, fatigue tests and further fractographic analysis was carried out using scanning electron microscopy. To ensure complete cure thermal analyze was performed. Two laminate architectures were evaluated: one 10 plies Harness Satin (5HS) and one 5 plies quasi-isotropic laminate

Made available in DSpace on 2014-06-11T19:28:35Z (GMT). No. of bitstreams: 0 Previous issue date: 2005Bitstream added on 2014-06-13T19:37:21Z : No. of bitstreams: 1 rocha_pcf_me_guara.pdf: 3559287 bytes, checksum: 5d2438ca3739708a996fc1df3aa87c36 (MD5) / Universidade Estadual Paulista (UNESP) / O tema proposto surgiu do interesse da ELEB - Embraer Liebherr Equipamentos do Brasil, em buscar por novas alternativas para a recuperação dimensional de peças. O processo de niquelação tipo sulfamato, é com freqüência utilizada em aplicações de engenharia devido às excelentes propriedades mecânicas do revestimento, tais como, alta ductibilidade e baixa tensão residual. Este estudo objetivou analisar a influência do revestimento de níquel, processo sulfamato, eletrodepositado no aço de alta resistência, ABNT 4340 , na dureza 53 HRc, como camada simples e como camada intermediária sob cromo duro convencional. A análise foi realizada por meio de dados obtidos nos ensaios de fadiga por flexão rotativa, em amostras revestidas somente com níquel, com cromo duro mais camada intermediária de níquel, ambas com e sem prétratamento shot peening, comparativamente às amostras do metal base. Os resultados demonstram que a aplicação da camada de níquel, processo sulfamato, reduziu o desempenho em fadiga tanto na alternativa somente níquel como na alternativa camada intermediária sob o cromo duro. Entretanto, o pré-tratamento shot peenig se mostrou eficaz, atenuando o efeito da redução em fadiga nas duas alternativas estudadas. / This work proposes to reach the interest of ELEB- Embraer Liebherr Equipamentos do Brasil in searching for new alternatives to parts dimensional recovery. The process of nickel electroplating sulphamate has often been used on engineering appliances due to its high mechanical property, such as ductility and low residual stress. This study aims to analyse the nickel layer effect, sulphamate process, electroplated on high strength stell, ABNT 4340 on hardness HRc 53, as simple layer and as interlayer under conventional hard chromium. The analysis was performed by means of obtained data from rotating bending fatigue tests of specimens coated with nickel only and coated with hard chromium plus nickel sulphamate interlayer, both with and without shot peening pre-treatment, in relation to ABNT 4340 specimens. The results showed that the nickel sulphamate coat decreased the ABNT 4340 fatigue performance in both cases, in the one coated with nickel only, and the one coated with hard chromium plus nickel sulphamate interlayer. However, the shot peeing pretreatment was efficient, because the fatigue loss effects have been reduced in both alternatives studied.

No description available.