O aço SAE 1552 modificado é um desenvolvimento recente da família do aço carbono manganês ligado ao silício, sendo utilizado para confecção de grampo U que tem como finalidade prender o feixe de molas no eixo do veículo. A somatória das fases de produção dessa matéria prima introduz os limites de resistência mecânica final necessária para atender a classe de resistência normativa. A peça produzida com esse aço tem alcançado crescimento de utilização na indústria automotiva devido à mesma apresentar propriedades mecânicas que atendem a requisitos normativos de classe de resistência e com vantagem de evitar tratamento térmico na fase de confecção do grampo e sendo esse processo realizado a frio em todas as suas fases. O objetivo desse trabalho foi estudar falha de grampo na etapa do processo de dobramento em forma de U e aplicar ensaios como: programa de simulação de tratamento térmico Stecal 3.0, ultrassom, fadiga, teste de cela e análise de fratura para solucionar essas falhas. Também foi realizado ensaios para prever fraturas catastróficas como: elementos finitos através de programa de computador Abaqus, ensaio de extensometria, tenacidade a fratura e medições de tensões residuais através de técnica de difração de raios-x. Foi concluído através dos resultados dos estudos de microestrutura resultante de tratamento térmico da matéria prima que o processo com resfriamento controlado em esteira é mais adequado para a produção do aço para confecção de grampo. O ensaio de ultrassom antes e após ensaio de fadiga possibilitou dimensionar o crescimento da profundidade da trinca em cotovelo de grampo e através de elementos finitos e extensometria associado com mecânica da fratura foi possível conhecer as tensões em ponto de estudo e entender o motivo de não ocorrer falha catastrófica. O ensaio de difração de raios-x permitiu o entendimento das tensões residuais introduzidas na peça de estudo. / SAE 1552 steel modified is a recent development of manganese carbon steel group linked to silicon, which is used to manufacture u-bolt that aims to fix leaf spring at vehicle axle in the back part. The sum of production stages of this raw material introduces the final mechanical resistance limits to meet class rules resistance. The piece produced with this steel has achieved growth of use in the automotive industry due to the mechanical properties it presents, which meet regulatory requirements for strength class and the advantage of avoiding heat treatment during manufacturing of the u-bolt and all the phases of this process are carried out in cold. This work aims to study the u-bolt failure during the folding process in the form of U and apply tests such as heat treatment simulation -Stecal 3.0, ultrasonic test, fatigue test, cell testing and analysis of crack. Other tests have been carried out to predict catastrophic fractures such as: finite element through computer program called Abaqus, extensometry testing, toughness testing for fracture and residual stress measurement by X ray diffraction technique. Results of heat treatment studies, by microstructure analysis, allowed choosing appropriate process for steel production. Ultrasonic testing before and after fatigue testing enabled to measure growth of crack depth on u-bolt elbow, and through finite element and extensometry testing associated with Mechanical of Fracture it was possible to know the stress concentrated at a point and to understand why catastrophic failure did not occur. Residual stress understanding has provided overall vision of u-bolt studied and contributed to have precision in measurement at inner and outer part of the u-bolt elbow.

Le présent travail s'appuie sur une approche expérimentale étendue visant l'identification des mécanismes d'endommagement en chargement quasi-statique et en fatigue du PA66/GF30, en prenant notamment en compte l'influence de la teneur en eau et de la microstructure induite par le moulage par injection. Les essais et les observations in situ au MEB mettent en exergue le rôle déterminant de l'humidité relative sur l'initiation, le niveau et la chronologie de l'endommagement. Une analyse par micro-tomographie aux rayons X sur des échantillons ayant subi un chargement de fatigue montre que l'endommagement augmente continuellement et progressivement au cours de la fatigue, et plus significativement dans la deuxième moitié de sa durée de vie. Les résultats obtenus en quasi-statique et en fatigue révèlent des mécanismes d'endommagement similaires, notamment une décohésion des interfaces fibre/matrice. Une chronologie générale de l'endommagement est établie. Celui-ci s'initie en extrémités de fibres ou plus globalement là où les fibres sont relativement proches les unes des autres. Il s'ensuit des décohésions interfaciales se propageant le long des fibres. A une contrainte en flexion plus élevée, des microfissures de la matrice peuvent apparaître et se propager par coalescence, ce qui aboutira à la rupture. Ces résultats expérimentaux permettent d'alimenter une modélisation multi-échelles de l'endommagement à fort contenu physique. Celle-ci contribuera alors à une prédiction pertinente de l'endommagement dans les thermoplastiques renforcés pour application automobile. / The current work focuses on extensive experimental approaches to identify quasi-static and fatigue damage behavior of PA66/GF30 considering various effects such as relative humidity and injection process induced microstructure. By using in situ SEM tests, it was observed that relative humidity conditions strongly impact the damage mechanisms in terms of their initiation, level and chronology. The X-ray micro-tomography analysis on fatigue loaded samples demonstrated that the damage continuously increases during fatigue loading, but the evolution occurs more significantly in the second half of the fatigue life. From the results of damage investigation under quasi-static and fatigue loading, it was established that both loading types exhibit the same damage mechanisms, with fiber/matrix interfacial debonding as the principal damage mechanisms. General damage chronologies were proposed as the damage initiates at fiber ends and more generally at locations where fibers are relatively close to each other due to the generation of local stress concentrations. Afterwards, interfacial decohesions further propagate along the fiber/matrix interface. At high relative flexural stress, matrix microcracks can develop and propagate, leading to the damage accumulation and then the final failure. The experimental findings are important to provide a physically based damage mechanisms scenarios that can be integrated into multiscale damage models. These models will contribute towards reliable predictions of damage in reinforced thermoplastics for lightweight automotive applications.

This thesis focuses on the development of a health monitoring system for gearbox transmissions. This was accomplished by developing and understanding a two-stage gearbox computer model that emulates an actual gearbox test rig. The computer model contains actual gearbox geometry, flexible shafts, bearings, gear contact forces, input motor torque, output brake torque, and realistic gearbox imbalance. The gear contact force of each gear stage and the input bearing translational acceleration were the main outputs compared between a healthy gearbox and damaged gearbox computer model. The damage of focus was a fatigue crack on the input pinion gear. A sideband energy ratio comparison yielded the computer simulation accurately modeled the difference between a healthy and damaged gearbox. The next step in this study involved the development of a repeatable procedure to initiate and propagate a fatigue crack at the tooth root in an actual spur gear. A damaged spur gear allows for a future comparison of an actual healthy and damaged gearbox system in the lab. A custom fatigue fixture was designed and manufactured for a Martin S1224BS 1 spur gear. The fatigue crack was initiated by position control fatigue testing which deflects the gear tooth a set amplitude for a number of cycles. Over the length of the test, the load that the tooth can withstand in bending decreases as damage begins to occur. Once the max load on the gear has dropped by a significant percentage (5-15%) a crack has initiated and begun to propagate across the tooth face. The use of a scanning electron microscope confirmed the presence a fatigue crack.

Indiana University-Purdue University Indianapolis (IUPUI) / Belt-drives are used in many applications such as industrial machines, washing ‎machines, and accessory drives for automobiles and other vehicles. Multibody dynamics/finite ‎element numerical models have become an effective way to predict the dynamic response of ‎belt-drives. In this thesis, a high fidelity numerical model was built using a multibody ‎dynamics/finite element code to simulate a belt-drive. The belt-drive transmits power from a ‎turbine of a Rankin cycle (that uses the exhaust waste heat of the internal combustion engine as ‎heat source) to the crank shaft of the engine. The code uses a time-accurate explicit numerical ‎integration technique to solve the multibody dynamics differential equations. The belt was ‎modeled using three-node beam elements to account for the belt axial and bending ‎stiffness/damping, while the pulleys, shafts and tensioner body were modeled as rigid bodies. ‎The penalty technique was used to model normal contact between the belt and the pulleys. An ‎asperity-based friction model was used to approximate Coulomb friction between the belt and ‎the pulleys. The dynamic response predicted using the model was validated by comparing it to ‎experimental results supplied by Cummins Inc. A parameter sensitivity study was performed to ‎evaluate the change in response due to change in various belt-drive parameters. A fatigue ‎model was developed to predict the belt fatigue life using output from the explicit finite ‎element code including normal and tangential forces between the belt and the pulleys and belt ‎tension. The belt fatigue life was evaluated for alternative belt-drive configurations in order to ‎find the configuration with the longest life.‎

The use of recommended S-N curves, presented in current literature, to analyse and determine the fatigue life of a part is common practice in, inter alia, the construction industry.However, the recommended S-N curves are generally created for larger components used in mainly the construction industry. Hence, the use of S-N curves for the evaluation of smaller parts, may result in over-dimensioning of such parts. For this reason, evaluation and designing of smaller parts could benefit from the development of an in house S-N curve specific for the part. The purpose of this thesis is to generate and validate an in-house method for creating a S-N curve, for a specific part to be compared with recommended S-N curves in the literature. The specific part used for the generating of the method is a welded steel joint with the geometry of two steel pipes, welded together in a t-formation and which has been provided by Thule AB for the purpose of the thesis. The method presented uses the results from 1) physical fatigue tests using a fatigue testing machine and 2) static FEA to derive a S-N curve for the specific part using the least squares method. A fatigue testing rig enables the gathering of data of the number of cycles to failure when the part is subject to a given cyclic load. The rig uses pneumatics to control the forces applied onto the part with the use of a cylinder. Furthermore, the fatigue testing rig was designed to be controlled by the applied force, meaning, that the rig ensured a homogeneous load cycle by measuring the force from a load cell and alternating the direction of the cylinder with an electrically controlled pressure valve. The performance of static FEA evaluations aim at locating stresses in the part. For this thesis the stresses were evaluated using the hot spot method due to the part's welded geometry. The data gathered from the physical fatigue tests and the static FEA evaluations are subsequently combined deriving S-N curves applicable to the part. From the fatigue tests and FEA evaluations for the t-shaped welded steel part, four S-N curves were derived of which two curves showed the results of a linear fitted curve whereas the other curves used the recommended slope of $-1/3$. The results showed that the S-N curves derived, using a set slope, resulted in similar curves to the recommended S-N curve provided by the literature. However, the linear fitted S-N curve showed that the part, according to the S-N curve, had a higher fatigue resistance than recommended.  Due to limitations in the thesis work, the S-N curves derived within the framework of this thesis should be regarded as theoretical and have been strictly used to identify whether the method generated is applicable for deriving of S-N curves.

Fatigue is a well-recognized issue in lightweight and high-performance aircraft structures. As fatigue failures have led to serious accidents and caused significant economic impact in the past, design against fatigue is crucial. Fatigue testing of full-scale aircraft as well as components is an important tool for the advance identification of potential fatigue issues in both new and operational aircraft. Furthermore, coupon testing is used extensively to obtain allowables for materials and structural details to be used in the design process. To obtain accurate results from fatigue testing, not only the test object but also the used load spectrum must accurately represent reality. If the aircraft is operational, an accurate load spectrum can be obtained by measuring the loads in-flight during a sufficiently long period of normal operation of the aircraft. However, the in-flight measured loads data contains an extraordinarily large number of cycles, resulting in long and uneconomical test durations. This thesis aims to propose a method for the selection of an optimal filtering level for fatigue test spectra developed from in-flight measured loads. The thesis also discusses and recommends methods for in-flight measurement of loads, cycle counting as well as damage evaluation using a crack-growth approach. Furthermore, ways to validate the proposed method and its practical application are discussed. An example filtering study is conducted using four different specimens chosen to represent typical structural details of aircraft. The study uses real in-flight measured loads of a light aircraft and also discusses temperature compensation of the loads data. The effect of filtering on fatigue damage is evaluated using crack-growth simulations conducted at a range of filtering and stress levels.  The results show that a remarkable reduction of testing time is possible and as many as 99 % of all cycles in the studied flight load history can be discarded without significantly reducing fatigue damage. The allowable filtering level is shown to differ between the specimens and the different stages of fatigue crack growth. In addition, the applied stress level is found to have a consistent effect on the allowable filtering level.

Fatigue testing of stretch sensors often focuses on high amplitude, low-cycle fatigue (LCF) behavior; however, when used for orthopaedic, athletic, or ergonomic assessments, stretch sensors are subjected to low amplitude, high-cycle fatigue (HCF) conditions. As an added layer of complexity, the fatigue testing of stretch sensors is not only focused on the life of the material comprising the sensor, but also on the reliability of the signal produced during the extension and relaxation of the sensor. Research into the development of a smart sock that can be used to measure the range of motion (ROM) of the ankle joint during athletic practices and competitions using stretch sensors is ongoing at Mississippi State University. The current smart sock prototype utilizes StretchSense™ StretchFABRIC capacitive dielectric elastomer sensors. These sensors are no longer manufactured, and FlexSense stretch sensors are being investigated as a potential replacement. To assess the reliability of the signal of the StretchFABRIC sensors currently used in the prototype, two sensors were subjected to 25,000 cycles of fatigue, under with simultaneous capture of the capacitance. The capacitances of the fatigued sensors were then compared to the capacitance of an unfatigued StretchFABRIC sensor during participant trials. Participants completed four static movements and six dynamic gait trials using either the fatigued or unfatigued sensor. Following completion of the initial static and dynamic movements, the movements were repeated using the opposite sensor. Comparison of the fatigued sensor to the unfatigued sensor revealed an upward drift in the capacitance of the fatigued sensor for all trials. Two FlexSense sensors were then subjected to either 450,000 or 250,000 cycles of fatigue with simultaneous capture of the signal from the sensor. To assess the signal, the peak capacitance recorded during the fatigue test was compared to the peak stretch percentage produced by the sensor. The peak displacement remained tight about the mean, while the peak stretch percentage exhibited a high level of scatter. From a materials standpoint, the sensors conformed to the Rabinowitz-Beardmore model of polymer fatigue where an initial monotonic overload of the material is followed by a transition to cyclic stability of the material.