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.

This thesis presents the derivation of the theory leading to the determination of the governing equations of chemically reacting flows under local thermodynamic equilibrium, which rigorously takes into account effects of elemental (de)mixing. As a result, new transport coefficients appear in the equations allowing a quantitative predictions and helping to gain deeper insight into the physics of chemically reacting flows at and near local equilibrium. These transport coefficients have been computed for both air and carbon dioxide mixtures allowing the application of this theory to both Earth and Mars entry problems in the framework of the methodology for the determination of the catalytic activity of Thermal Protections Systems (TPS) materials.<p>Firstly, we analyze the influence of elemental fraction variations on the computation of thermochemical equilibrium flows for both air and carbon dioxide mixtures. To this end, the equilibrium computations are compared with several chemical regimes to better analyze the influence of chemistry on wall heat flux and to observe the elemental fractions behavior along a stagnation line. The results of several computations are presented to highlight the effects of elemental demixing on the stagnation point heat flux and chemical equilibrium composition for air and carbon dioxide mixtures. Moreover, in the chemical nonequilibrium computations, the characteristic time of chemistry is artificially decreased and in the limit the chemical equilibrium regime, with variable elemental fractions, is achieved. Then, we apply the closed form of the equations governing the behavior of local thermodynamic equilibrium flows, accounting for the variation in local elemental concentrations in a rigorous manner, to simulate heat and mass transfer in CO2/N2 mixtures. This allows for the analysis of the boundary layer near the stagnation point of a hypersonic vehicle entering the true Martian atmosphere. The results obtained using this formulation are compared with those obtained using a previous form of the equations where the diffusive fluxes of elements are computed as a linear combination of the species diffusive fluxes. This not only validates the new formulation but also highlights its advantages with respect to the previous one :by using and analyzing the full set of equilibrium transport coefficients we arrive at a deep understanding of the mass and heat transfer for a CO2/N2 mixture.<p>Secondly, we present and analyze detailed numerical simulations of high-pressure inductively coupled air plasma flows both in the torch and in the test chamber using two different mathematical formulations: an extended chemical non-equilibrium formalism including finite rate chemistry and a form of the equations valid in the limit of local thermodynamic equilibrium and accounting for the demixing of chemical elements. Simulations at various operating pressures indicate that significant demixing of oxygen and nitrogen occurs, regardless of the degree of nonequilibrium in the plasma. As the operating pressure is increased, chemistry becomes increasingly fast and the nonequilibrium results correctly approach the results obtained assuming local thermodynamic equilibrium, supporting the validity of the proposed local equilibrium formulation. A similar analysis is conducted for CO2 plasma flows, showing the importance of elemental diffusion on the plasma behavior in the VKI plasmatron torch.<p>Thirdly, the extension of numerical tools developed at the von Karman Institute, required within the methodology for the determination of catalycity properties for thermal protection system materials, has been completed for CO2 flows. Non equilibrium stagnation line computations have been performed for several outer edge conditions in order to analyze the influence of the chemical models for bulk reactions. Moreover, wall surface reactions have been examined, and the importance of several recombination processes has been discussed. This analysis has revealed the limits of the model currently used, leading to the proposal of an alternative approach for the description of the flow-surface interaction. Finally the effects of outer edge elemental fractions on the heat flux map is analyzed, showing the need to add them to the list of parameters of the methodology currently used to determine catalycity properties of thermal protection materials. / Doctorat en sciences appliquées / info:eu-repo/semantics/nonPublished

The aim of the diploma thesis is to evaluate the economic efficiency of the investment in the complete insulation of a reference panel apartment building located in Bytča. The issue of the ETICS external contact system, the energy performance of the building, its thermal protection and the possibilities of financing and evaluation of the economic efficiency of the investment in question are approached in this thesis. The output of the diploma thesis will be an evaluation of the current state of the reference building, with a propper proposal for a thermal insulation. The optimal thermal insulation option and the financial provision of the investment will be selected based on economic efficiency indicators.

This thesis is devoted to the choice of materials suitable for construction building envelope and its influence on the price of the works. It evaluates the thermal insulating characteristics of the selected structures and monitors their impact on operating costs of the object.

The Thesis "Analysis of Technical Requirements for Buildings with focus on Building Physics" deals with the solution of masonry and monolithic residential buildings in terms of building physic requirements primarily listed in Decree No.268/2009 Coll and in Czech technical standards.

This thesis deals with the temperature-moisture assessment of builgind constructions apartment building. Selected critical details are examined in special programs Area 2015 and Cube3D 2015. The thesis also includes thermal measurement of apartment building using a termovision camera. Theoretical calculations are then compared with measurements which were performed on a real building.

<p dir="ltr">A current engineering challenge is to understand and validate material systems capable of maintaining structural viability under the elevated temperature and environmental conditions of hypersonic flight. One aspect of this challenge is the joining of multiple materials with thermal expansion mismatch, which can lead to residual stress, resulting in debits in component lifetime under in-service loading. The focus of this work is a series of studies focused on a ceramic-metal composite (WC/Cu), a zirconia coating applied to a carboncarbon (C/C) composite, and a silicide (R512E) coating applied to a Nb-based alloy (C103). Each of these material systems are candidates for elevated temperature applications in which dissimilar constituents result in residual stress in the material. Each study leveraged experimental residual strain measurements, with the primary focus on the use of synchrotron X-ray diffraction, in conjunction with representative models, and microscopy to illuminate the active mechanisms in the development and evolution of residual stress in the bulk material. The combination of experimental and modeling predictions provides a framework to inform the viability and lifing of material systems exhibiting dissimilar expansion properties.</p>

Ce travail de recherche répond aux besoins actuels et futurs dans le domaine de l’Aérospatial de faire évoluer les règles de dimensionnement au flambage des réservoirs structuraux de l’Etage Principal Cryogénique (EPC) des lanceurs. Ces réservoirs, composés de coques cylindriques, peuvent être associés à un faible raidissage en termes de masse ajoutée. L’objectif d’alléger le lanceur pour optimiser la charge utile, conduit au choix de coques constitutives de plus en plus minces, le risque de flambage sous diverses sollicitations est donc d’autant plus accru. Le dimensionnement au flambage de l’EPC est basé principalement sur la norme NASA SP8007 qui date de 1968, et qui semble trop conservative, notamment aux basses pressions. Précisons aussi, que l’EPC est équipé d’une couche de protection thermique (PT) qui n’est pas prise en compte dans le design au vue de sa très faible rigidité de membrane. La contribution de cette couche à la capacité de flambage de la coque est cependant un sujet ouvert. / This research work responds to the current and future requirements in Aerospatiale are to improve the design for buckling of the tanks of the Cryogenic Main Stage (EPC) of the launcher. These tanks are composed of cylindrical shells and can be associated with weak stiffening, which are becoming thinner and therefore more susceptible to a risk of buckling. The buckling design of the EPC based mainly on the NASA SP8007 standard, which is ac-cording to many specialists too preservative, especially under low pressure. Moreover, the EPC is equipped with a thermal protection layer (PT), which is extremely light and has an excellent thermal insulation property but very low mechanical properties. The contribution of this layer to the buckling capacity of a lightly pressurized thin cylindrical shell under var-ious solicitations, therefore, appears to be a major subject.

Aviation industry is continuously growing especially for very long distance flights due to the globalisation of local economies around the world and the explosive economic growth in Asia. Reducing the time of intercontinental flights from 16-20 hours to 4 hours or less would therefore make the, already booming, ultra-long distance aviation sector even more attractive. To accomplish this drastic travel time reduction for civil transport, hypersonic cruise aircraft are considered as a potential cost-effective solution. Such vehicles should also be fuelled by liquid hydrogen, which is identified as the only viable propellant to achieve antipodal hypersonic flight with low environmental impact. Despite considerable research on hypersonic aircraft and hydrogen fuel, several major challenges should still be addressed before such airliner becomes reality. The current thesis is therefore motivated by the potential benefit of hydrogen-fuelled hypersonic cruise vehicles associated with their limited state-of-the-art.Hypersonic cruise aircraft require innovative structural configurations and thermal management solutions due to the extremely harsh flight environment, while the uncommon physical properties of liquid hydrogen, combined with high and long-term heat fluxes, introduce complex design and technological storage issues. Achieving hypersonic cruise vehicles is also complicated by the multidisciplinary nature of their design. In the scope of the present research, appropriate methodologies are developed to assess, design and optimize the thermo-structural model and the cryogenic fuel tanks of long-range hydrogen-fuelled hypersonic civil aircraft. Two notional vehicles, cruising at Mach 5 and Mach 8, are then investigated with the implemented methodologies. The design analysis of light yet highly insulated liquid hydrogen tanks for hypersonic cruise vehicles indicates an optimal gravimetric efficiency of 70-75% depending on insulation system, tank wall material, tank diameter, and flight profile. A combination of foam and load-bearing aerogel blanket leads to the lightest cryogenic tank for both the Mach 5 and the Mach 8 aircraft. If the aerogel blanket cannot be strengthened sufficiently so that it can bear the full load, then a combination of foam and fibrous insulation materials gives the best solution for both vehicles. The aero-thermal and structural design analysis of the Mach 5 cruiser shows that the lightest hot-structure is a titanium alloy construction made of honeycomb sandwich panels. This concept leads to a wing-body weight of 143.9 t, of which 36% accounts for the wing, 32% for the fuselage, and 32% for the cryogenic tanks. As expected, hypersonic thermal loads lead to important weight penalties (of more than 35%). The design of the insulated cold structure, however, demonstrates that the long-term high-speed flight of the airliner requires a substantial thermal protection system, such that the best configuration (obtained by load-bearing aerogel blanket) leads to a titanium cold design of only 4% lighter than the hot structure. Using aluminium 7075 rather than titanium offers a further weight saving of about 2%, resulting in a 135.4 t wing-body weight (with a contribution of 23%, 25%, 18% and 34% from the TPS, the wing, the fuselage, and the cryogenic tanks respectively). Given the design hypotheses, the difference in weight is not significant enough to make a decisive choice between hot and cold concepts. This requires the current methodologies to be further elaborated by relaxing the simplifications. Investigation of the thermal protection must be extended from one single point to different regions of the vehicle, and the TPS thickness and weight should be considered in the structural sizing of the cold design. More generally, the design process should be matured by including additional (static, dynamic and transient) loads, special structural concepts, multi-material configurations and other parameters such as cost and safety aspects. / Doctorat en Sciences de l'ingénieur et technologie / This thesis was conducted in co-tutelle between University of Sydney and Université Libre de Bruxelles.Professor Dries Verstraete was my supervisor at the University of Sydney (so as a member of SydneyUni), but is automatically registered here as a member of ULB because he worked at ULB almost ten years ago.Ben Thornber is also a member of the University of Sydney but the application does not save it for an unknown reason. / info:eu-repo/semantics/nonPublished

A porous silica –silica composite was processed with varying fiber diameters using the slurry moulding technique. The advantage of the process was that the density of the composite could be processed to the required levels. The reinforcements used were fibers obtained by leaching E-glass cloth, imported silica fibers with diameter <1.8µ and hollow silica fibers processed using sol-gel method. All the properties depend on the density of the composite. The compressive strength was measured in the perpendicular and parallel directions. Strength was high when the load axis was along the fiber direction. The composite with fine fibers (< 1.8 µ pure silica fibers) showed higher strength compared to the leached silica fibers. The thermal conductivity measurement on these composites showed an increase with temperature owing to the domination of radiation at high temperatures. As the vacuum level was approached, the thermal conductivity showed a decrease due to the absence of the convective part of the thermal transfer process. For use as a thermal protection system, it is important to measure the thermal response of these tiles in a simulated re-entry environment. Tests were done to measure this response for a given heat flux conditions at 38W/cm2 to 75W/cm2 and the backwall temperature was measured for various types of silica -silica composites. The role of impurities like sodium and B2O3 was also studied with respect to the conversion from amorphous to crystalline forms of SiO2. The severe increase in the coefficient of thermal expansion when SiO2 converted from amorphous to α– crystoballite was also measured. CSZP CSZP which belongs to the NZP family was processed using the co-precipitation technique. The influence of substituting the ‘P’ site with ‘Si’ atom was studied for its influence on thermal expansion – both at the bulk level by dilatometry and at the intrinsic level using high temperature XRD. For many anisotropic materials micro-cracking is a serious issue while cooling from the sintering temperature. It has been previously proved that this extent of micro-cracking depends on the particle size. Smaller the particle size is therefore preferred. One of the significant results obtained in this study was the successful use of microwaves to process crack free CSZP with fine grain size. CSZP with 95% density having a grain size as small as 1µ have been processed using microwave sintering. Dielectric property evaluation namely dielectric constant, dielectric loss and temperature coefficient of resonant frequency which are vital parameters required if this material is to be used as a candidate TPS have also been measured. The thermal conductivity of the sample was measured using Laser flash apparatus and was found to be 0.9 W/mk which provides an indication that this material can be used as a successful material for TPS. Finally a composite consisting of silica fiber with CSZP as matrix was processed and tested for heat flux. The low back wall temperature indicates that this material is a potential replacement for silica tile.