Em função das limitações apresentadas pelos relés eletromecânicos, a proteção térmica de motores foi historicamente tratada como um problema de coordenação de sobrecorrente, sem levar em consideração a dinâmica e o histórico térmico envolvido na operação contínua do motor. Os atuais relés microprocessados para proteção de motores implementam equações diferenciais de primeira ordem, cujos algoritmos, processados em tempo real, possibilitam uma nova abordagem para uma adequada proteção térmica, utilizando modelos matemáticos. Especialmente para os motores industriais de grande porte e de maior importância operacional, somente os recentes relés de proteção microprocessados e seus algoritmos digitais tem sido efetivamente capazes de fornecer proteção adequada, baseados em modelos térmicos que realisticamente estimam, continuamente e em tempo real, o nível térmico atual do motor. A proteção térmica de motores de indução trifásicos tem sido uma das maiores áreas onde a proteção numérica, baseado em microprocessadores, tem proporcionado um aprimoramento do nível básico das funções de proteção de motores. O método da proteção térmica tem sido aperfeiçoado, de forma a implementar modelos que levam em consideração o aquecimento do motor devido às correntes de seqüência positiva e negativa e as características térmicas de um motor de indução. A capacidade do processamento digital de sinais tem possibilitado a implementação de novas soluções para as deficiências de proteção de motores industriais trifásicos apresentadas pelas tecnologias convencionais de proteção, até então fundamentadas em proteção de sobrecorrente. As principais funções de proteção aplicáveis para motores trifásicos industriais, bem como os aspectos do estado da arte de hardware, software e filtros digitais implementados nos atuais relés de proteção microprocessados são discutidos neste trabalho. O equacionamento de um sistema térmico de primeira ordem e os requisitos de modelo para a implementação da proteção térmica de motores são também aqui analisados. São discutidas as dinâmicas de dois modelos térmicos, um baseado em proteção por sobrecorrente e outro baseado em um sistema térmico de primeira ordem. São simulados e comparados os desempenhos destes dois diferentes algoritmos de proteção térmica de motores, quando submetidos às correntes de carga e de sobrecarga, tanto constantes como cíclicas. / On account of the limitations presented for the electromechanical relays, the motor thermal protection was historically treated as an overcurrent coordination issue, without taking into account the dynamics and the thermal historical involved in the process. The modern microprocessor-based relays for motor protection implement discrete time first-order differential equations, whose algorithms, based on the power of the real time signal processing, make possible a new approach for a proper thermal protection, applying mathematical models. Especially for large and critical operational significance industrial motors, only the recent numerical relays for motor protection and its digital algorithms has been efficiently suitable to provide an adequate protection, based in thermal models that realistically take into account, continuously and in real time, the actual motor thermal level. The thermal protection of three-phase induction motors has been one of the biggest areas where the numerical protection, based in microprocessor-based relays, has provide an improvement of the basic level of the motor protection functions. The method of the thermal protection has been improved, in such wise as to implement models that take into account the motor heating due to both positive and negative sequence currents, and the thermal characteristics of an induction motor. The capacity of the digital signal processing has made possible the implementation of new solutions for the deficiencies of three-phase industrial motors protection, established on the conventional protection technologies, till then based on overcurrent protection. The main applicable protection functions for industrial three-phase motors, as well as the aspects of the state of the art of the hardware, software and digital filters implemented in the actual microprocessor-based protection relays are discussed in this work. The derivation of a first-order thermal system and the requirements of model for the implementation of the motor thermal protection also are studied in this work. The dynamics of two thermal models, one based in overcurrent protection and another based on a first-order thermal system are analyzed. The performances of these two different algorithms of motor thermal protection are simulated and compared, when subjected to both constants and cyclic, load and overload currents.

During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent the payload from overheating, charring ablative materials are favored to be applied as the heat shield at the exposing surface of the vehicle. Accurate modeling not only prevents mission failures, but also helps reduce cost. Existing models were mostly limited to one-dimensional and discrepancies were shown against measured experiments and flight-data. To help improve the models and analyze the charring ablation problems, a multidimensional material response module is developed, based on a finite volume method framework. The developed computer program is verified through a series of test-cases, and through code-to-code comparisons with a validated code. Several novel models are proposed, including a three-dimensional pyrolysis gas transport model and an orthotropic material model. The effects of these models are numerically studied and demonstrated to be significant.

Space vehicles, while entering the planetary atmosphere, experience high loads of heat. Ablative materials are commonly used for a thermal protection system, which undergo mass removal mechanisms to counter the heat rates. Spallation is one of the ablative processes, which is characterized by the ejection of solid particles from the material into the flow. Numerical codes that are used in designing the heat shields ignore this phenomenon. Hence, to evaluate the effectiveness of spallation phenomenon, a numerical model is developed to compute the dynamics and chemistry of the particles. The code is one-way coupled to a CFD code that models high enthalpy flow field around a lightweight ablative material. A parametric study is carried out to examine the variations in trajectories with respect to ejection parameters. Numerical results are presented for argon and air flow fields, and their effect on the particle behavior is studied. The spallation code is loosely coupled with the CFD code to evaluate the impact of a particle on the flow field, and a numerical study is conducted.

Induction motors are widely used in industrial processes. The malfunction of a motor may not only lead to high repair costs, but also cause immense financial losses due to unexpected process downtime. Since thermal overload is one of the major root causes of stator winding insulation failure, an accurate and reliable monitoring of the stator winding temperature is crucial to increase the mean time to catastrophic motor breakdown, and to reduce the extraordinary financial losses due to unexpected process downtime. To provide a reliable thermal protection for induction motors fed by motor control devices, a dc signal-injection method is proposed for in-service induction motors fed by soft-starter and variable-frequency drives. The stator winding temperature can be monitored based on the estimated stator winding resistance using the dc model of induction motors. In addition, a cooling capability monitoring technique is proposed to monitor the cooling capability of induction motors and to warn the user for proactive inspection and maintenance in the case of cooling capability deterioration. The proposed cooling capability monitoring technique, combined with the proposed stator winding temperature monitoring technique, can provide a complete thermal protection for in-service induction motors fed by motor control devices. Aside from online thermal protection during a motor's normal operation, the thermal protection of de-energized motors is also essential to prolong a motor's lifetime. Moisture condensation is one of the major causes to motor degradation especially in high-humidity environments. To prevent moisture condensation, a non-intrusive motor heating technique is proposed by injecting currents into the motor stator winding using soft-starters. A motor's temperature can be kept above the ambient temperature due to the heat dissipation, so that the moisture condensation can be avoided. To sum up, active stator winding temperature estimation techniques for induction motors under both operating and de-energization conditions are proposed in this dissertation for both thermal protection and optimizing the operation of a motor system. The importance of these proposed techniques lies in their non-intrusive nature: only the existing hardware in a motor control device is required for implementation; a motor's normal operation is not interrupted.

The advancement of each component of aerospace vehicles is necessary as the continual demand for more aggressive missions are created. Improvements in propulsion and guidance system electronics are invaluable; however without material development to protect the vehicle from its environment those advances will not have a practical application. Thermal protection systems (TPS) are required in both external applications; for example on reentry vehicles, as well as in internal applications; to protect the casing of rockets and missiles. This dissertation focuses on a specific type of internal solid rocket motor TPS, ablatives. Ablatives have been used for decades on aerospace vehicles. To protect the motor from the hostile environment, these materials pyrolyze and char. Both of these mechanisms produce a boundary between the combustion gases and the motor as well as release the heat that the decomposed material has absorbed. These sacrificial materials are intended to protect the casing that it is attached to. With the development of polymer nanocomposites (PNCs) in the last couple of decades, it is of interest to see how these two fields can merge. Three different nanomaterials (carbon nanofibers, multiwall carbon nanotubes, and nanoclays) are examined to observe how each behaves in environments that simulate the motor firing conditions. These nanomaterials are individually added to a thermoplastic polyurethane elastomer (TPU) at different loadings, creating three distinct families of polymer nanocomposites. To describe a materials ablative performance, a number of material properties must be individually studied; such as thermal, density, porosity, char strength, and rheology. Different experiments are conducted to isolate specific ablative processes in order to identify how each nanomaterial affects the ablative performance. This dissertation first describes each material and the ablative processes which are characterized by each experiment. Then basic material properties of each family of materials are described. Degradation and flammability experiments then describe the degassing processes. Studies of the material char are then performed after full blown rocket experiments are done. These tests have shown that of the three nanomaterials, nanoclay enhances the TPU ablative performance the most while the CNF provides the least enhancement. / text

Submitted by PEDRO GUILHERME SILVA PESCI null (peg_pesci@hotmail.com) on 2017-11-30T13:40:46Z No. of bitstreams: 1 Versão Final.pdf: 56735184 bytes, checksum: 4e1d7d9c3a8db1009fa3e028174b3593 (MD5) / Approved for entry into archive by Pamella Benevides Gonçalves null (pamella@feg.unesp.br) on 2017-11-30T17:38:21Z (GMT) No. of bitstreams: 1 pesci_pgs_me_guara.pdf: 56735184 bytes, checksum: 4e1d7d9c3a8db1009fa3e028174b3593 (MD5) / Made available in DSpace on 2017-11-30T17:38:21Z (GMT). No. of bitstreams: 1 pesci_pgs_me_guara.pdf: 56735184 bytes, checksum: 4e1d7d9c3a8db1009fa3e028174b3593 (MD5) Previous issue date: 2017-11-24 / Materiais utilizados em componentes de veículos espaciais, como em tubeiras ou superfícies expostas à reentrada atmosférica, são sujeitos a ambientes termicamente agressivos. Este trabalho apresenta estudos envolvendo o desempenho de materiais compósitos utilizados em sistemas de proteção térmica, a partir da exposição a jatos de plasma, onde os fluxos de calor são comparáveis aos da reentrada atmosférica de componentes de veículos espaciais. Amostras de compósitos ablativos de carbono/fenólica foram ensaiadas no túnel de plasma do Laboratório de Plasmas e Processos do ITA (Instituto Tecnológico de Aeronáutica), por meio de uma tocha de plasma alimentada por uma fonte de energia elétrica de corrente contínua de 50kW. Os parâmetros de operação do túnel de plasma foram otimizados para reproduzirem as condições próximas do ponto crítico de reentrada das cargas úteis dos veículos espaciais desenvolvidos pelo IAE (Instituto de Aeronáutica e Espaço). As amostras em estudo foram desenvolvidas e fabricadas no Brasil, a partir de materiais de especial interesse do IAE. Para comparação, foi também ensaiado outro material com propriedades já bem estabelecidas como o teflon, sob as mesmas condições ablativas. Foram determinadas as perdas de massa e as taxas de perda de massa específicas das amostras, as temperaturas radiométricas superficiais e termométricas internas, em função do tempo de exposição ao fluxo térmico. Foi realizada também a avaliação da evolução das interfaces por comparação entre simulação e a amostra após o ensaio. Os resultados obtidos permitiram estimar as propriedades do comportamento ablativo dos materiais testados e validar o modelo teórico usado na simulação computacional para sua utilização em geometrias próximas às dos sistemas de proteção térmica utilizadas no setor aeroespacial / Materials used in space vehicles components, such as nozzles or surfaces exposed to atmospheric reentry, are subjected to thermally aggressive environments. This work presents studies involving the performance of composite materials used in thermal protection systems, through the exposure to plasma jets, where the heat fluxes are comparable to atmospheric reentry of space vehicle components. Samples of ablative carbon/phenolic composites were tested in the plasma tunnel of ITA’s (Aeronautics Institute of Technology) Plasma and Process Laboratory, by a plasma torch with a 50kW DC power source. The plasma tunnel operating parameters were optimized to reproduce the conditions close to the critical re-entry point of the space vehicles payloads developed by the IAE (Aeronautics and Space Institute). The samples in study were developed and manufactured in Brazil, from materials of special interest to IAE. For comparison, another material with well established properties such as teflon was also tested under the same ablative conditions. The mass loss and the specific mass loss rates of the samples, the surface radiometric and internal thermometric temperatures, as a function of the exposure time to the thermal flow, were determined. The evolution of the interfaces was also performed by comparison between simulation and the sample after the test. The results allowed to estimate the properties of the ablative behavior of the materials tested and to validate the theoretical model used in the computational simulation for its use in geometries close to the thermal protection systems used in the aerospace sector

In the design of a thermal protection system for atmospheric entry, aerothermal heating presents a major impediment to efficient heat shield design. Recombination of atomic species in the boundary layer results in highly exothermic surface-catalyzed recombination reactions and an increase in the heat flux experienced at the surface. The degree to which these reactions increase the surface heat flux is partly a function of the heat shield material. Characterization of the catalytic behavior of these materials takes place in experimental facilities, however there is a dearth of detailed computational models for the fluid dynamic and chemical behavior of such facilities. A numerical model coupling finite rate chemical kinetics and high temperature thermodynamic and transport properties with a computational fluid dynamics flow solver has been developed to model the chemically reacting flow in the inductively coupled plasma torch facility at the University of Vermont. Simulations were performed modeling the plasma jet for hybrid oxygen-argon and nitrogen plasmas in order to validate the models developed in this work by comparison to experimentally-obtained data for temperature and relative species concentrations in the boundary layer above test articles. Surface boundary conditions for wall temperature and catalytic efficiency were utilized to represent the different test article materials used in the experimental facility. Good agreement between measured and computed data is observed. In addition, a code-to-code validation exercise was performed benchmarking the performance of the models developed in this dissertation by comparison to previously published results. Results obtained show good agreement for boundary layer temperature and species concentrations despite significant differences in the codes. Lastly, a series of simulations were performed investigating the effects of recombination reaction rates and pressure on the composition of a nitrogen plasma jet in chemical nonequilibrium in order to better understand the composition at the boundary layer edge above a test article. Results from this study suggest that, for typical test conditions, the boundary layer edge will be in a state of chemical nonequilibrium, leading to a nonequilibrium condition across the entire boundary layer for test article materials with high catalytic efficiencies.

Com o aumento dos tratamentos químicos e/ou físicos nos cabelos aos quais são realizados mediante o uso de dispositivos térmicos, há uma maior preocupação a respeito dos danos causados aos cabelos por estes tipos de tratamentos. O conhecimento dos efeitos, benefícios e/ou malefícios, de ingredientes cosméticos em cabelos torna-se necessário, pois facilita a busca por produtos baseada no tipo de cabelo. O principal objetivo do trabalho foi a caracterização físico-química, analítica e térmica de mechas de cabelo de diferentes etnias (caucasiano, oriental e afro-étnico virgem e brasileiro virgem e descolorido) antes e após o uso de ingredientes cosméticos seguido de um tratamento térmico (utilizando piastra) e intercalando com lavagens. O estudo das amostras de cabelo e de uma amostra de queratina animal envolveu a utilização das técnicas de TG/DTG, DSC, análise elementar, FTIR, MEV e técnicas de avaliação de eficácia, como tensão/deformação, penteabilidade e quebra por escovação. A partir da TG/DTG, foi possível avaliar as etapas de decomposição térmica das amostras de cabelo virgem e de queratina animal e estas apresentaram um comportamento térmico semelhante entre si. O estudo cinético não isotérmico por TG mostrou que, dos diferentes tipos de amostras de cabelo virgem, o afro-étnico apresentou menor estabilidade térmica e o oriental foi o mais estável termicamente. Os resultados de DSC corroboraram os obtidos por TG, demonstrando que a amostra de cabelo afro-étnico apresentou temperatura de desnaturação térmica das cadeias de α-queratina menor (TD = 223°C) do que as amostras dos outros tipos de cabelo (TD = 236°C). As mechas de cabelo virgem e clareadas foram tratadas com formulações cosméticas contendo silicones e avaliadas quanto a eficiência destes na proteção térmica dos cabelos. Algumas delas mostraram eficiência na proteção térmica das cadeias de α-queratina, diminuindo o seu grau de desnaturação. Foi possível observar que a associação do calor da piastra com as lavagens sucessivas causou danos tanto à cutícula (conforme resultados de FTIR e MEV), como também, ao córtex dos cabelos (conforme resultados de DSC). Em alguns casos, os danos causados foram tão graves que as camadas mais superficiais da cutícula sofreram descamações. O estudo mostrou, também, que a eficiência da proteção térmica nos cabelos depende do tipo da formulação cosmética em que estes protetores estão incorporados e do estado em que os cabelos se encontram. A DSC permitiu a avaliação da modificação termicamente induzida das cadeias de α-queratina e sua posterior desnaturação. O estudo envolvendo a associação das diferentes técnicas apresentou-se viável na avaliação tanto dos danos causados aos cabelos quanto na eficiência dos ingredientes cosméticos na proteção térmica dos mesmos. / With the increase of chemical and/or physical hair treatments, there is an increased concern about the damage caused by the continued use of thermal equipment. This is due to products identified as \"progressive brush\", widely used by individuals of various types of hair, in order to straighten them that are employed with the mandatory use of piastra. Thus, knowledge about the effects, benefits and/or detriments, of cosmetic ingredients in hair of different ethnic groups becomes necessary because it facilitates the search for products based on the type of hair. The main objective this work was the physicochemical, analytical and thermal characterization of hair samples of different ethnic groups (caucasian, oriental, african-ethnic and brazilian type II) before and after the use of cosmetic ingredients followed by heat treatment, using piastra, interleaved by washes. For such purpose, it was used the TG/DTG, DSC, EA, FTIR, SEM and techniques for evaluation of effectiveness as stress/strain and combing. By TG/DTG, it was possible to evaluate the thermal decomposition events of hair and animal keratin samples and these showed a similar thermal behavior between them. The TG-non isothermal kinetic study showed that, from the different types of virgin hair samples, the african-ethnic hair samples had the lowest thermal stability and oriental hair samples were more thermally stable. The DSC results confirm the results obtained by TG, demonstrating that african-ethnic hair samples had thermal denaturation temperature of α-keratin chains (TD = 223°C) lower than the samples from other types of hair (TD = 236°C). The virgin and bleached hair tresses were treated with cosmetic formulations containing silicones and evaluated the efficiency of the thermal protection of the hair. Some of the formulations tested have shown to be efficient as to its protective effect on the degradation of the α-keratin chains, decreasing the degree of denaturation. It was observed that the combination of the heat of piastra with successive washes caused damage to the hair cuticle (according to the IR and SEM results) as well as the cortex of hair (according DSC results). In some cases, the damage was so severe that the most superficial layers of the cuticle suffered flaking. The study also showed that the efficiency of the thermal protection in the hair depends on the type of cosmetic formulation that these protectors are incorporated and the condition of the hair. DSC technique allowed monitoring of the thermally induced modification of the α-keratin chains and subsequent denaturation. The study of the combination of all the techniques, as presented, is feasible in measuring damage to hair and the efficiency of cosmetic ingredients in protecting them.

The Kentucky Re-entry Universal Payload System (KRUPS) is an adaptable testbed for atmosphere entry science experiments, with an initial application to thermal protection systems (TPS). Because of the uniqueness of atmospheric entry conditions that ground testing is unable to replicate, scientists principally rely on numerical models for predicting entry conditions. The KRUPS spacecraft, developed at the University of Kentucky, provides an inexpensive means of obtaining validation data to verify and improve these models. To increase the technology readiness level (TRL) of the spacecraft, two sub-orbital missions were developed. The first mission, KUDOS, launched August 13th, 2017 on a Terrier-Improved Malamute rocket to an altitude of ~150 km. The second mission, KOREVET, launched on March 25th, 2018 on the same type of rocket to an altitude of ~170 km. The chief purpose of both missions was to validate the spacecraft design, ejection mechanism, on-board power, data transmission, and data collection. After both missions, the overall TRL improved from 4 to 5 by validating most subsystems in a relevant environment. Both of these missions were invaluable preparation for the project's ultimate goal of releasing multiple experimental testbeds from the ISS.

Thermal Protection System (TPS) is required to shield an atmospheric entry vehicle against the high surface heating environment experienced during hypersonic flight. There are significant uncertainties in the tools and models currently used for the prediction of entry aeroheating and TPS material thermal response. These uncertainties can be reduced using experimental data. Analysis of TPS ground and flight data has been traditionally performed in a direct fashion. Direct analyses center upon comparison of the computational model predictions to data. Qualitative conclusions about model validity may be drawn based on this comparison and a limited number of model parameters may be iteratively adjusted to obtain a better match between predictions and data. The goal of this thesis is to develop a more rigorous methodology for the estimation of surface heating and TPS material response using inverse estimation theory. Built on theoretical developments made in related fields, this methodology enables the estimation of uncertainties in both the aeroheating environment and material properties from experimental temperature data. Unlike direct methods, the methodology developed here is capable of estimating a large number of independent parameters simultaneously and reconstructing the time-dependent surface heating profile in an automated fashion. This methodology is applied to flight data obtained from thermocouples embedded in the Mars Pathfinder and Mars Science Laboratory entry vehicle heatshields.