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Measurements have been performed to understand the sound source mechanism in turbulent boundary layer flow over two and three-dimensional surface discontinuities whose height is smaller than the incoming boundary layer thickness. The work was performed in two different types of boundary layers: a wall-jet flow and a conventional high Reynolds boundary layer. In the wall-jet flow, measurements of far field sound from two-dimensional forward facing steps, gaps with rounded corners and swept forward facing steps with rounded corners were made. The sound from a forward facing step is shown to exhibit effects of non-compactness. Rounding the step corner results in consistent drop in sound levels but the directivity of the sound field remains unchanged. The sound from gaps is dominated by the forward step component and remains unaffected by rounding of the backward step portion. The sound from swept forward facing steps was found to approximately obey an acoustic sweep independence principle up to a sweep angle of 30 deg when the spanwise inhomogeneity in the flow is accounted for using a simple source distribution model. Sweep independence is also observed for steps with corner rounding radii up to 25% of the step height. The work performed in the high Reynolds number boundary layer included measurements on forward facing steps with rounded corners and a three-dimensional circular embossment with the same height as the forward step. The highest Reynolds number based on discontinuity height achieved in this work was approximately 93,000. The results show that rounding the forward step corner has the same qualitative effect on far field sound as in the wall-jet boundary layer. Quantitatively, for similar boundary layer edge velocity the sound is higher than in the wall-jet flow. The near field measurements show that the separation bubble downstream of the step shrinks as the step corner is rounded while the bubble upstream remains unaffected by it. The unsteady surface force in the lower half of the vertical face of the step was found to be independent of corner rounding. The force on the downstream surface shows similar character within the separation bubble for each rounding but decays faster with increasing downstream distance due to reduced bubble size. The unsteady force measurements were applied to the theory of Glegg et al. (2014) and the resultant of the unsteady forces on the vertical face and downstream surface placed at the top corner of the step is shown to qualitatively describe the far field sound. The acoustic sweep independence principle was applied to the far field sound from the circular embossment and it has been shown that the sound from the three-dimensional geometry can be predicted with reasonable accuracy using sound from a two-dimensional forward step with the same span. / Ph. D.

As pesquisas modernas em aeronáutica envolvem a expansão dos envelopes de vôo, como resultado do desejo de melhorar a manobrabilidade e controlabilidade em operações táticas, e melhorar a segurança do vôo. Esses objetivos podem ser alcançados através do desenvolvimento de sistemas automáticos de controle de vôo. Os sistemas de controle aplicados a aeronaves podem ser desenvolvidos e simulados através de métodos computacionais. No entanto, existem imperfeições na simulação computacional por não se conseguir reproduzir algumas características do vôo real ou devido a simplificações no modelo matemático da aeronave. Desta forma, a construção de um modelo físico de uma aeronave em escala reduzida e a implementação de um controlador a este modelo, torna-se uma ferramenta bastante importante para validar resultados teóricos e métodos computacionais. Os custos associados a estes testes são geralmente muito menores que aqueles dos ensaios em vôo e com maior flexibilidade de instrumentação. Este trabalho descreve a construção de um modelo de aeronave, baseado no X-29, o desenvolvimento de um mecanismo de fixação do modelo ao túnel de vento, tipo rótula, e a implementação de um sistema de aumento de estabilidade longitudinal, através de um sistema de controle automático. O modelo físico possui uma configuração de asa com enflechamento negativo e canard, e que tende a ser inerentemente instável, sendo necessário o auxílio de um sistema de aumento de estabilidade. Testes de estabilidade dinâmica em arfagem foram realizados no túnel de vento em diferentes posições do centro de gravidade. Os parâmetros de estabilidade foram registrados e analisados através de uma curva de ajuste exponencial. / Modern aeronautical research involves flight envelope expansion as the result of a desire for improvement in tactical operation handling qualities and improvement in flight safety. These objectives can be achieved through the development of automatic flight control systems. Aircraft flight control systems can be developed and simulated through computational methods. However, there are imperfections in the computational simulation of flight dynamics due to the difficulty in reproducing real flight conditions or due simplifications in the aircraft mathematical model. The construction of a reduced scale physical aircraft model and the implementation of a controller is a very valuable tool to validate theoretical results and computational methods. The costs associated with these tests are usually much smaller than those associated with full scale flight testing and may offer greater flexibility for instrumentation. The present work describes the construction of an airplane model, based on the X-29, the development of a wind tunnel gimbal type support and the implementation of a longitudinal stability augmentation system using automatic flight control. The model configuration has forward swept wings and canard with a tendency to be inherently unstable and, thus, requiring a stability augmentation system. Pitching dynamic stability tests where conducted in a wind tunnel in different center of gravity positions. Stability parameters were acquired and analyzed by exponential fit curve.

This thesis presents cutter swept volume generation, in-process workpiece modeling and Cutter Workpiece Engagement (CWE) algorithms for finding the instantaneous intersections between cutter and workpiece in milling. One of the steps in simulating machining operations is the accurate extraction of the intersection geometry between cutter and workpiece. This geometry is a key input to force calculations and feed rate scheduling in milling. Given that industrial machined components can have highly complex geometries, extracting intersections accurately and efficiently is challenging. Three main steps are needed to obtain the intersection geometry between cutter and workpiece. These are the Swept volume generation, in-process workpiece modeling and CWE extraction respectively. In this thesis an analytical methodology for determining the shapes of the cutter swept envelopes is developed. In this methodology, cutter surfaces performing 5-axis tool motions are decomposed into a set of characteristic circles. For obtaining these circles a concept of two-parameter-family of spheres is introduced. Considering relationships among the circles the swept envelopes are defined analytically. The implementation of methodology is simple, especially when the cutter geometries are represented by pipe surfaces. During the machining simulation the workpiece update is required to keep track of the material removal process. Several choices for workpiece updates exist. These are the solid, facetted and vector model based methodologies. For updating the workpiece surfaces represented by the solid or faceted models third party software can be used. In this thesis multi-axis milling update methodologies are developed for workpieces defined by discrete vectors with different orientations. For simplifying the intersection calculations between discrete vectors and the tool envelope the properties of canal surfaces are utilized. A typical NC cutter has different surfaces with varying geometries and during the material removal process restricted regions of these surfaces are eligible to contact the in-process workpiece. In this thesis these regions are analyzed with respect to different tool motions. Later using the results from these analyses the solid, polyhedral and vector based CWE methodologies are developed for a range of different types of cutters and multi-axis tool motions. The workpiece surfaces cover a wide range of surface geometries including sculptured surfaces.

Skin friction drag reduction is one of the most promising paths in the investigation of the reduction of aircraft fuel burn. 40 – 50% of overall drag comes from the surfaces of the wings and stabilizers. Natural laminar flow airfoils can extend the region of laminar flow and reduce skin friction drag. However, real-world aircraft wings do not have perfectly smooth surfaces, and therefore the tolerances for step and gap excrescences on these airfoils must be investigated. Previous work has focused on excrescences on flat plates, and only recently included pressure gradient effects. A new three-dimensional swept wing airfoil with an actuated leading edge (SWIFTER) has been constructed, and will extend the body of knowledge of step and gap excrescences to a more real-world configuration and higher Reynolds numbers. An integrated control system for the leading edge actuation system is proposed, including both interface hardware and control code. A heating system for the test surface is also discussed, and the controller hardware, sensors, and code specified. For wind tunnel testing, a proposed set of wall liners are developed from zero-lift condition streamlines and divided into parts suitable for manufacturing, assembly, and installation. Finally, preliminary wind tunnel step excrescence tests using an existing swept-wing model and applique step material were conducted, and the results are discussed with relevance to testing on the new model.

This thesis presents cutter swept volume generation, in-process workpiece modeling and Cutter Workpiece Engagement (CWE) algorithms for finding the instantaneous intersections between cutter and workpiece in milling. One of the steps in simulating machining operations is the accurate extraction of the intersection geometry between cutter and workpiece. This geometry is a key input to force calculations and feed rate scheduling in milling. Given that industrial machined components can have highly complex geometries, extracting intersections accurately and efficiently is challenging. Three main steps are needed to obtain the intersection geometry between cutter and workpiece. These are the Swept volume generation, in-process workpiece modeling and CWE extraction respectively. In this thesis an analytical methodology for determining the shapes of the cutter swept envelopes is developed. In this methodology, cutter surfaces performing 5-axis tool motions are decomposed into a set of characteristic circles. For obtaining these circles a concept of two-parameter-family of spheres is introduced. Considering relationships among the circles the swept envelopes are defined analytically. The implementation of methodology is simple, especially when the cutter geometries are represented by pipe surfaces. During the machining simulation the workpiece update is required to keep track of the material removal process. Several choices for workpiece updates exist. These are the solid, facetted and vector model based methodologies. For updating the workpiece surfaces represented by the solid or faceted models third party software can be used. In this thesis multi-axis milling update methodologies are developed for workpieces defined by discrete vectors with different orientations. For simplifying the intersection calculations between discrete vectors and the tool envelope the properties of canal surfaces are utilized. A typical NC cutter has different surfaces with varying geometries and during the material removal process restricted regions of these surfaces are eligible to contact the in-process workpiece. In this thesis these regions are analyzed with respect to different tool motions. Later using the results from these analyses the solid, polyhedral and vector based CWE methodologies are developed for a range of different types of cutters and multi-axis tool motions. The workpiece surfaces cover a wide range of surface geometries including sculptured surfaces.

As pesquisas modernas em aeronáutica envolvem a expansão dos envelopes de vôo, como resultado do desejo de melhorar a manobrabilidade e controlabilidade em operações táticas, e melhorar a segurança do vôo. Esses objetivos podem ser alcançados através do desenvolvimento de sistemas automáticos de controle de vôo. Os sistemas de controle aplicados a aeronaves podem ser desenvolvidos e simulados através de métodos computacionais. No entanto, existem imperfeições na simulação computacional por não se conseguir reproduzir algumas características do vôo real ou devido a simplificações no modelo matemático da aeronave. Desta forma, a construção de um modelo físico de uma aeronave em escala reduzida e a implementação de um controlador a este modelo, torna-se uma ferramenta bastante importante para validar resultados teóricos e métodos computacionais. Os custos associados a estes testes são geralmente muito menores que aqueles dos ensaios em vôo e com maior flexibilidade de instrumentação. Este trabalho descreve a construção de um modelo de aeronave, baseado no X-29, o desenvolvimento de um mecanismo de fixação do modelo ao túnel de vento, tipo rótula, e a implementação de um sistema de aumento de estabilidade longitudinal, através de um sistema de controle automático. O modelo físico possui uma configuração de asa com enflechamento negativo e canard, e que tende a ser inerentemente instável, sendo necessário o auxílio de um sistema de aumento de estabilidade. Testes de estabilidade dinâmica em arfagem foram realizados no túnel de vento em diferentes posições do centro de gravidade. Os parâmetros de estabilidade foram registrados e analisados através de uma curva de ajuste exponencial. / Modern aeronautical research involves flight envelope expansion as the result of a desire for improvement in tactical operation handling qualities and improvement in flight safety. These objectives can be achieved through the development of automatic flight control systems. Aircraft flight control systems can be developed and simulated through computational methods. However, there are imperfections in the computational simulation of flight dynamics due to the difficulty in reproducing real flight conditions or due simplifications in the aircraft mathematical model. The construction of a reduced scale physical aircraft model and the implementation of a controller is a very valuable tool to validate theoretical results and computational methods. The costs associated with these tests are usually much smaller than those associated with full scale flight testing and may offer greater flexibility for instrumentation. The present work describes the construction of an airplane model, based on the X-29, the development of a wind tunnel gimbal type support and the implementation of a longitudinal stability augmentation system using automatic flight control. The model configuration has forward swept wings and canard with a tendency to be inherently unstable and, thus, requiring a stability augmentation system. Pitching dynamic stability tests where conducted in a wind tunnel in different center of gravity positions. Stability parameters were acquired and analyzed by exponential fit curve.

Cette thèse décrit le design, la simulation et la fabrication d’une matrice 4x4 de micro-miroirs actionnée verticalement et munie d’un capteur de position. Le micro-scanneur vertical a pour vocation à être intégré au sein d’un micro-interféromètre de Mirau de type matriciel, réalisé àbase de composants micro-optiques fabriqués grâce à des méthodes collectives. Le mouvement du micro-scanneur, développé dans cette thèse, génère un signal de référence utilisé pour l’implémentation de l’interférométrie à modulation de phase dans un système de tomographie par cohérence optique (OCT). Dans un premier temps, la thèse introduit le besoin d’un système d’imagerie adapté pour la détection précoce des cancers de la peau et établit les spécifications optiques requises par cette application. A partir de ces spécifications, le design du système OCT basé sur le micro-interféromètre de Mirau est présenté. En parallèle, l’état de l’art des technologies de micro-actionnement est décrit et un actionnement électrostatique à base de peignes interdigités est choisi pour actionner et lire la position de la matrice de micro-miroirs. En effet ce type d’actionnement bénéficie d’une bonne compatibilité avec le design du micro-interféromètre de Mirau. Dans un second temps, le cœur de la thèse expose le développement du micro-scanneur vertical, c.à.d le design et les simulations ainsi que la fabrication et la caractérisation. / This thesis describes the design, simulation and fabrication of a vertically actuated 4x4 array ofmicromirrors with embedded position sensing function. The vertical microscanner is meant to beintegrated within an array-type Mirau microinterferometer realized with optical microcomponentsfabricated using collective techniques. The microscanner, developed in this thesis, provides areference signal that is used for the implementation of phase modulation interferometery in an opticalcoherence tomography (OCT) system. This thesis first introduces the need for adapted imagingsystems for the early diagnosis of skin cancer and establishes the optical specifications requiredby this specific application. Based on these specifications, the design of the OCT system based onthe Mirau microinterferometer is presented. In parallel, the state of the art of the microactuationtechnologies is discussed and comb drive electrostatic actuation is chosen, for its compatibilitywith the design of the Mirau microinterferometer, to actuate and sense the position of the array ofmicromirrors. Then, the core of the thesis deals with the development of the vertical microscanner,i.e. its design and simulations, its fabrication and its characterization.

This thesis presents cutter swept volume generation, in-process workpiece modeling and Cutter Workpiece Engagement (CWE) algorithms for finding the instantaneous intersections between cutter and workpiece in milling. One of the steps in simulating machining operations is the accurate extraction of the intersection geometry between cutter and workpiece. This geometry is a key input to force calculations and feed rate scheduling in milling. Given that industrial machined components can have highly complex geometries, extracting intersections accurately and efficiently is challenging. Three main steps are needed to obtain the intersection geometry between cutter and workpiece. These are the Swept volume generation, in-process workpiece modeling and CWE extraction respectively. In this thesis an analytical methodology for determining the shapes of the cutter swept envelopes is developed. In this methodology, cutter surfaces performing 5-axis tool motions are decomposed into a set of characteristic circles. For obtaining these circles a concept of two-parameter-family of spheres is introduced. Considering relationships among the circles the swept envelopes are defined analytically. The implementation of methodology is simple, especially when the cutter geometries are represented by pipe surfaces. During the machining simulation the workpiece update is required to keep track of the material removal process. Several choices for workpiece updates exist. These are the solid, facetted and vector model based methodologies. For updating the workpiece surfaces represented by the solid or faceted models third party software can be used. In this thesis multi-axis milling update methodologies are developed for workpieces defined by discrete vectors with different orientations. For simplifying the intersection calculations between discrete vectors and the tool envelope the properties of canal surfaces are utilized. A typical NC cutter has different surfaces with varying geometries and during the material removal process restricted regions of these surfaces are eligible to contact the in-process workpiece. In this thesis these regions are analyzed with respect to different tool motions. Later using the results from these analyses the solid, polyhedral and vector based CWE methodologies are developed for a range of different types of cutters and multi-axis tool motions. The workpiece surfaces cover a wide range of surface geometries including sculptured surfaces. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

Frequency response analysis (FRA) has emerged as the de-facto industry standard condition-monitoring tool to assess mechanical integrity of transformer windings during its service life. It the prerequisite detection sensitivity and customized portable commercial instruments are also available. Considering its importance and taking cognizance of its hidden potential, international bodies, viz., IEEE, IEC, and CIGRE have published standards/guides on its use and interpretation. In spite of all the progress witnessed over the past two decades, FRA has still not attained the status of a diagnostics tool. Probing the vast literature and research carried out in this points to the fact that lack of a rigorous mathematical basis to explain the underlying complex processes is, perhaps, one of the main reasons for the present predicament of FRA method. How-ever, it must be acknowledged that domain-knowledge is di cult to generalize in this. Having said that, the diagnostic part, which involves, the task of working back-wards starting from the FRA data to interpret a winding damage, locate it, and assess its severity, has so far remained teasingly elusive. As a consequence, FRA continues to remain as a sensitive condition-monitoring tool. Given its inherent potential, this situation seems to be a paradox, and so, calls for investigations. Once a mechanical damage has been detected by FRA, the next task is to locate its position and estimate its severity. An engineer expects FRA to provide these answers, so that corrective action, if needed, can be determined and initiated. In this context, even though FRA has attained global acceptance as a monitoring tool, it has failed as a diagnostic tool. Therefore, e orts that aim to address this issue are desirable. Driven by this motivation, the author's thesis proposes to explore a new school of thought in this direction, viz., to theoretically analyze the problem of localization of an incipient/minor mechanical damage (displacement in particular) and also assess its severity. Such an investigation seems to have not been undertaken previously. So, the goal is to establish a relationship to capture the complex interactions that exist between specific winding damages, winding parameters, and their overall in hence on the natural frequency deviations observable in the FRA data. Hence, exploring this possibility, subject to the constraint that the proposed method shall use inputs that are measurable at the terminals, becomes the primary objective of this research. In this thesis, a generalized analytical framework for handling winding displacements and FRA data has been successfully formulated. The formulation provides a general platform for localization and severity assessment of true radial and axial winding dis-placements occurring in an actual winding. An analytical solution becomes possible mainly due to manipulation of the system matrix, i.e., to consider the harmonic sum of squares of natural frequencies, instead of just the natural frequencies. This manipulation leads to an elegant closed-form expression that connects the displacement location and its severity, to changes in natural frequencies. For its implementation, short circuit natural frequencies and a few other terminal measurements are the only inputs that are necessary. This formulation is initially used in Chapter-3 to demonstrate localization of radial displacement in an isolated, actual, single, air-cored continuous-disk winding. Armed with this success, the supplicant proceeds further to show (in Chapter-4) how a minor manipulation of the formulation renders it suitable for localization of actual axial displacements as well. Extensive experimental verification was done and the results are encouraging. Accuracy of localization of radial/axial displacement is uniformly good for all positions, and so is the estimation of severity. Further details are presented in the thesis.