Les pulses tubes sont des cryoréfrigérateurs similaires aux machines Stirling mais sans pièce mobile à froid, ce qui diminue les vibrations et augmente leur fiabilité. Toutes ces caractéristiques sont les bienvenues pour les applications spatiales, un domaine où le poids et la taille de la machine sont critiques. C'est dans ce cadre qui s'insère la recherche sur la miniaturisation des pulses tubes ; pour le réussir, on peut diminuer le volume déplacé pendant un cycle de la machine, en augmentant simultanément la fréquence d'opération. Pour savoir quels sont les limitations à l'augmentation de fréquence, des simulations sur le comportement du régénérateur et l'inertance à très hautes fréquences ont été faits; une étude expérimentale sur les pertes thermiques dans le tube a été aussi élaborée; et, finalement, des prototypes de pulse tube ont été dimensionnés et caractérisés, l'un desquels satisfait les spécifications initialement données : 0.25 W à 120 K avec 20 W puissance mécanique, à 100 Hz. / Pulse Tubes are a kind of cryocoolers similar to Stirling refrigerators, apart from the cold mobile element, absent in the first, which lessens their exported vibrations and increases their reliability. Spatial applications seek these characteristics for the instruments embarked, along with small weight and size. These needs stimulate the research on pulse tube miniaturization; to achieve this reduction, one can decrease the swept volume per cycle, whilst increasing the frequency of operation. To understand the barriers to carry out very high frequency operation, simulations on the behavior of the regenerator and inertances were made, as well as an experimental study on the thermal losses of the expansion tube. Finally, several very high frequency pulse tube prototypes were built and benchmarked, one of which fulfills the requirements we had initially set : 0.25 W at 120 K, with 20 W of input power at 100 Hz.

This work is concerned with the design, development and performance evaluation of an inertance Pulse Tube Cryocooler (PTC). The main components of a PTC are the compressor, regenerator, pulse tube and inertance tube coupled to a reservoir. The inertance tube is a key component that affects the pressure and mass flow and phase shift between them and hence the performance. In conjunction with the compressor, it also plays a strong role in determining the frequency of operation. The PTC is designed based on system level numerical models (SAGE and DeltaE), component level thermo-acoustic models (DeltaE) of inertance tube and regenerator and experimental data of earlier fabricated Stirling coolers. As a starting point, an inertance tube with a diameter of 3 mm and 3.1 m long was chosen through component level analysis that provides phase shift of around 50 degrees at a pressure ratio of 1.1 for an acoustic power of about 4 W (in order to achieve 1 W of net cooling at 80 K) at 25 bar mean pressure and 60 Hz. From this inertance tube geometry, an estimate of the mass flow rate at the cold heat exchanger is obtained. Based on this mass flow rate, the initial dimensions of the pulse tube and regenerator are arrived at. A parametric study using system level model is carried out to obtain the maximum COP by varying inertance tube length and regenerator diameter. A flexure bearing compressor consisting of moving coil linear motor coupled to a piston is designed for the above cold head. Based on the above design considerations, the PTC compressor and cold head are fabricated and assembled. The PTC is charged with helium at mean pressure of 25 bar and instrumented with pressure and position transducers, temperature sensors and a skin-bonded heater for simulating the heat load on the cold head. Experimental data for the PTC were obtained with two different inertance tube lengths for different frequencies of operation. The cold head temperature exhibited a minimum with respect to the frequency. This optimum frequency shifts towards lower frequency with increased length of the inertance tube. The experimental data clearly shows that with different inertance tube lengths the optimum frequency locates itself for obtaining zero phase shift at the middle of the regenerator. It is observed that the optimum frequency is closely linked to the natural frequency of the pressure wave in the inertance tube suggesting a standing wave within the inertance tube with the pressure node at the reservoir. Thus the inertance tube is found to be analogous to a quarter wave resonator in a thermo-acoustic device. It may thus be possible to pre-fix an operating frequency for a given PTC cold head by choosing an inertance tube length close to quarter wave resonator length. This study has given insights on the phase shift between pressure and mass flow rate governed by the inertance tube and the connection between the optimum and natural frequencies which can be used for better design of PTCs.

Le SMA Nitinol est largement utilisé dans de nombreux domaines de recherche récemment ( astronautes, biomédical ) et la combinaison de leurs propriétés dans la structure de conception désirée, en particulier les matériaux de l'architecture, est développé dans la dernière décennie. Des études récentes fabriqués avec succès la structure cellulaire, en particulier nid d'abeil, par processus thermomécanique à partir de tubes ou de barres mais les caractères de la liaison entre les éléments constitutifs ne sont pas clarifiées.Ce travail est consacré à l'étude de la liaison entre NiTi alliage quasi- équatomic qui est créé par le processus frittage des tubes ou des fils et par le procédé de soudage de tubes. Les liaisons obtenues des deux méthodes semblent forts et ils sont analysés par les essais de métallurgique et mécanique. Les résultats ont conduit aux conclusions suivantes :Pour les processus de frittage, les liaisons pour les des fils et des tubes semblent être forte quand ils sont chauffés à 1200oC pendant 1 heure avec les fils et 2 heures avec les tubes, respectivement. Cependant, le traitement entraîne le changement de la composition dans le matière. Le traitement à 900oC peut aider l'homogénéisation de la liaison, mais la phase inattendu TiNi2O est existé. En outre, la diffusion entre le Nitinol et Al2O3 est commencé quand ils sont chauffés à 1200oC.Pour le procédé de soudage, les liaisons entre tubes soudés sont forts avec seulement la phase TiNi mais la microstructure a changé. Il ya 2 nouvelles zones existantes à l'intérieur de la liaison de soudure: la zone de soudage, la zone affectée thermique. Les résistances de traction de la liaison de soudge une fois sont 12N/mm et 50N/mm pour tubes ayant la paroi 0,12 mm et la paroi 0,3 mm, respectivement. L'optimisation des paramètres de soudage montre que l'énergie de soudure a un effet fortement sur la création et la résistance de la liaison. La liaison est amilioré si l'énergie augmente. Charge de soudage a un rôle important pour améliorer la résistance de la liaison, et la charge de soudage est adapté pour le tube est 100N. Le deuxième fois de soudage peuvent améliorer la résistance de la liaison de la paroi du tube de 0,3 mm, mais il diminue après le troixième fois de soudage. En plus, l'addition de fois de soudage sous pression plus que de 100N conduit à la réduction de la résistance de la liaison. Ainsi, les paramètres de soudage doivent être tout d'abord examiné base de l'épaisseur de paroi du tube, puis l' énergie de soudage, la pression de soudure et la soudure fois. / Nickel-Titane shape memory alloys are widely used in many fields (aerospace, biomedical) and the combination of their outstanding properties in designed structures, namely architecture materials, has been considered in last decade. Recent studies successfully fabricated cellular structures, in particular honey combs, by thermo-mechanical processing from tubes or bars but the properties of the bonds created between the components need to be carefully investigated.This work is dedicated to the study of the bonds between NiTi near-equatomic alloy (Nitinol) elements, which are created by sintering together tubes or wires and by welding tubes under load. These bonds are characterized from metallurgical, microstructural and mechanical points of view. The obtained results led to the following conclusions.To provide a reasonably strong bond between wires and between tubes, sintering should be operated at least at 1200°C during one hour under the maximal load allowed by the experimental device, 3.5 N. However, this treatment causes intense compositional changes inside the material. A subsequent aging treatment at 900oC can help in homogenizing the material but prejudicial TiNi2O phase still exists. Besides, the interdiffusion between Nitinol elements and alumina tools at 1200°C perturbs sintering experiments. The sintering route has thus found to be inadequate unless the used device allows applying a higher load, so that the temperature can be set down.Tube welding has been more successful in terms on bond strength and NiTi phase conservation, although important microstructure changes have been observed. Three zones have been identified after welding, the weld zone, with large and long grains, the heat-affected zone, with smaller, spherical grains, and the non-affected zone. The extent of these zones is estimated from local hardness measurement. The tensile resistance of the bonds is about 12 and 50 N/mm for tubes having 0.12 and 0.3 mm thickness, respectively. A standard aging treatment does not significantly change these values although it allows material homogenization. The parameters that mainly influence the resistance and the microstructure of the bond are the weld energy, the rate of release of this energy and the load. Achieving successive welding steps is not clearly beneficial.

Cette thèse étudie le transfert de chaleur par rayonnement observé dans les conditions d'écoulement raréfié, en régime hypersonique qui seraient rencontrés au cours d'une mission d'aérocapture dans l'atmosphère de Titan. Des estimations précises du rayonnement hors-équilibre dans des écoulements à grande vitesse tels que ceux autour des corps de re-entrée, sont indispensables pour la conception de systèmes de protection thermique plus efficace. Parce que la masse du système de protection thermique est une fraction importante de la masse totale du véhicule, il ya un grand intérêt dans la conception de systèmes plus légers et plus efficaces. Les expériences en vol sont coûteuses et contraignantes, c'est pourquoi l'essai en laboratoire dans des installations capables de produire des écoulements hypersoniques est nécessaire. Malheureusement, les échelles de longueur généralement impliquées dans les expériences en vol sont trop grandes pour être testées dans des installations expérimentales et donc des modèles réduits de véhicules 'aeroshells' sont généralement testés. Les tubes d'expansion de l'université de Queensland - X1, X2 et X3 - ont été largement utilisés pour la modélisation à l'échelle réduite des écoulements hypersoniques (Morgan 2001). Pour les installations d'essais au sol telle que la soufflerie X2, une mise à l'échelle binaire est utilisée pour tester des modèles à échelle réduite de véhicules de vol, ce qui constitue le paramètre le plus important à respecter afin de reproduire un vol à haute vitesse. La mise à l'échelle binaire, appelé aussi 'mise à l'échelle 'ƒÏL', exige que le produit de la densité et de la longueur caractéristique du véhicule soit conservé entre le vol et les conditions expérimentales. Toutefois, il a été montré par Capra (2007) que le transfert de chaleur par rayonnement ne suit pas cette même loi de mise à l'échelle, et la similitude n'est pas crée pour les cas en vol où le transfert de chaleur par rayonnement et par convection sont fortement couplés. Cela peut entraîner d'importantes erreurs dans les estimations des propriétés d'écoulement associée et l'estimation du transfert de chaleur due au rayonnement. L'installation X2 a été modifiée en 2006 pour permettre l'expérimentation à basse pression en mode tube à choc non-réfléchi. L'utilisation d'un tube à choc non-réfléchi a permis la mesure du transfert de chaleur par rayonnement à la densité réelle en vol et supprimé les problèmes d'échelle liés à la mesure des rayonnements sur les véhicules en modèle réduit, au moins pour une partie de l'écoulement. Des mesures ont été effectuées dans la région immédiatement située derrière le choc et le long de la ligne médiane de l'écoulement de base, où le choc reste plan. Les écoulements externes, tels que ceux entourant une capsule de re-enntrée, n'ont pas été reproduits. La limite de basse pression d'exploitation était d'environ 10 Pa, limitée par la croissance de la couche limite sur les murs. / This thesis investigates the radiative heat transfer encountered in rarefied, hypervelocity flow conditions such as would be experienced during an aerocapture mission to Titan. Accurate estimates of the nonequilibrium radiation involved in high speed operations such as reentry are essential in order to design these thermal protection systems more efficiently. Because the mass of the thermal protection system is a large fraction of the overall vehicle mass, there is great interest in designing lighter and more efficient systems. Flight experiments are expensive and restrictive, hence laboratory testing is needed in facilities that are capable of producing hypervelocity flow. Unfortunately, as the size of a typical flight vehicle is too large to reasonably test in experimental facilities, subscale models of the aeroshell vehicles are generally tested. The University of Queensland's expansion tube facilities - X1, X2 and X3 - have been widely used for subscale modelling of hypersonic flowfields (Morgan 2001). Ground testing facilities such as the X2 facility take advantage of binary scaling to test small scale models of flight vehicles, which is the most important parameter to match in order to reproduce high speed flight. Binary scaling, also called 'ƒÏL' scaling, requires that the multiplication of density and the characteristic length of the vehicle be balanced between flight and experimental conditions. However, it was shown by Capra (2007) that radiative heat transfer does not follow this same scaling factor, and true similarity with flight is not created for flows where the radiative and convective heat transfer are strongly coupled. This can result in significant errors in the estimates of the associated flow properties and the estimation of the heat transfer due to radiation. The X2 facility was modified in 2006 to allow experimentation at low pressures in nonreflected shock tube mode. Nonreflected shock tube operation allowed the taking of true-flight density measurements of the radiative heat transfer and removed the scaling problems involved in radiation measurements for model vehicles, at least for part of the flowfield. Measurements were made in the region immediately behind the shock along the centreline of the core flow, where the shock remained planar. External flow fields, such as those surrounding a reentry capsule, were not reproduced. The low density operating limit was approximately 10 Pa, limited by boundary layer growth on the walls.

No description available.

Depuis plusieurs années, les procédés à grandes déformations plastiques (SPD) sont développés pour affiner la microstructure de métaux afin d’obtenir des tailles de grains submicroniques. Cet affinement confère au matériau des propriétés améliorées (ex : limite élastique). Durant ces procédés, la géométrie globale du matériau reste inchangée. C’est pourquoi les procédés sont spécifiques pour une géométrie donnée. Dans cet objectif, un procédé récemment inventé au sein du LEM3, nommé HPTT - High Pressure Tube Twisting – permet de nanostructurer des échantillons tubulaires. Un tube est confiné par l’application d’une pression hydrostatique de plusieurs GPa et de grandes forces de frottement sont ainsi générées. Une déformation en cisaillement (> 4) dans l’épaisseur du tube est ensuite appliquée. Dans le cadre de cette thèse, un dispositif expérimental a été développé et utilisé pour la production d’échantillons à grains ultrafins (UFG). Des études analytiques et par éléments finis ont permis de comprendre l’état de contrainte et de déformation dans la paroi du tube. Un acier IF (Interstitial-Free) rendu nanostructuré a fait l’objet de caractérisations approfondies pour déterminer l’évolution de la microstructure (MEB-EBSD), des textures (rayons X) et du comportement mécanique (compression). Dans le but de mieux comprendre les phénomènes de fragmentation, un code polycristallin impliquant la courbure du réseau comme élément principal conduisant à l’affinement de la microstructure a été utilisé et comparé aux mesures expérimentales. Ce travail est conclu par une étude de la taille limite atteignable par ces procédés / For several years, Severe Plastic Deformation (SPD) processes have been developed to refine the microstructure of metals in order to obtain ultrafine grains (UFG). This refinement attributes improved properties (ex: yield stress) to the material. The overall geometry of the material remains unchanged. That is why these processes are specific for a given geometry. For this purpose, a process recently initiated at the LEM3, the so called HPTT – High Pressure Tube Twisting – is designed to nanostructure tubular samples. A tube is confined by applying a hydrostatic pressure of several GPa and large friction forces are generated. A shear strain (> 4) is finally applied in the tube thickness. In this thesis, an experimental device was developed and used to produce UFG materials. Finite element and analytical studies have been carried out to understand the stress and strain state in the tube wall. The obtained ultrafine grains IF (Interstitial-Free) steel was characterized to determine the evolution of the microstructure (SEM-EBSD), textures (X-rays) and the mechanical behavior (compression tests). For a better understanding of the fragmentation phenomena, a polycrystal code involving lattice curvature as the main element leading to refinement of the microstructure was used and compared with experimental measurements. This work is concluded by a study on the limited grain size achievable by SPD processes

<p>Hypersonic flow conditions, such as temperature, pressure, and flow velocity, are challenging to measure on account of the extreme conditions experienced by a craft moving above Mach 5. At Mach 5, the temperature in stratospheric air behind a normal shock wave exceeds temperatures of 1,300 K, and as the craft speed increases, so does the temperature. At these temperatures and conditions, traditional measurement techniques such as thermocouples and pressure transducers either alter the flow path, affecting the measurement, or they do not survive the external conditions. As such, there is interest in investigating alternative ways to measure flow properties. This thesis focuses on the implementation of several optical measurement techniques designed to determine the flow temperature, density gradient, and flow velocity in a detonation driven shock tube. A detonation driven shock tube was chosen for the project as it reliably creates high-speed, low-density, gas flows that are reminiscent of hypersonic conditions. </p><p>The first optical measurement technique implemented was background oriented schlieren, a measurement technique that quantitatively provides density gradient data. Experimental data obtained at pressures up to 3,000 psia resulted in density gradients at the exit of the detonation tube in good agreement with the literature.</p><p>The detonation tube was also fitted with two fiber optic ports to gather chemiluminescence thermometry data. Both a Stellarnet Black-Comet spectrometer and a Sydor Ross 2000 streak camera were used to capture spectroscopic data at these ports, in order to determine the detonation speed and the rotational temperature of the intermediate OH* combustion products. The Stellarnet spectrometer did not have a fast enough data capture rate to gather reliable data. While the streak camera captured data quickly, we had difficulty gathering enough light from the combustion event and the gathered data was very noisy. The streak camera did however capture the time duration of the full combustion event, so if the fiber connector ports are improved this data taking method could be used in the future to gather rotational temperature data. Both measurement techniques provided some unintrusive measurements of high-speed flows, and improvements to the data taking system could provide much needed information on hypersonic flow conditions. </p>

Historically, the endeavor of scale testing flight vehicles at supersonic Mach numbers, especially for long durations, has required the development of closed-loop wind tunnels, which are extremely expensive both to build and operate due to the high complexity and incredible power required to drive such a system. The intermittent blowdown wind tunnel, indraft tunnel, and shock tunnel have alleviated many of these cost requirements to some degree, whilst facilitating testing at very high Mach numbers and enthalpies; however, these systems require the handling of gases at pressures and temperatures that can be prohibitive for many university settings. The Ludwieg tube provides a simple, elegant method for producing testable supersonic flows at price points significantly lower than the aforementioned test-system architectures. Unfortunately, the spacial footprint and moderate cost required for driver tube and nozzle hardware can make it difficult to implement for many non-research universities. In this thesis, a new supersonic test system architecture is conceived, designed, implemented, and validated for the purpose of making supersonic aerodynamic testing capability attainable for most universities, by combining properties of the Ludwieg Tube and indraft wind tunnel to reduce the cost needed to produce this capability. This system, the Indraft Tube Tunnel, requires no long driver-tube or test-section hardware, aside from a vacuum chamber. Furthermore, it is safe to operate, as high pressure containment systems are not required for the Indraft Tube Tunnel System. It is designed and operated to draw stagnant atmospheric air through a converging-diverging nozzle to achieve a steady-state Mach number of 2.5. Sufficient pressure ratio to reach the desired Mach number is attained by evacuating the vacuum chamber and placing a thin cellophane diaphragm across the inlet of the nozzle, thus separating the vacuum section from ambient atmosphere. To initiate gas flow, the diaphragm is mechanically burst with a puncture device. This design requires much less hardware to implement than a typical Ludwieg tube, and had an operating cost of less than one dollar per test. Using this method, steady, uninterrupted Mach 2.44 is attained for a duration of 13.6 ms and a test section diameter of 7 inches. The standard deviation of the Mach number measurements is .08 Mach. A shadowgraph imaging setup is used to view and measure the angle of oblique shockwaves on a simple wedge test-model. The Indraft Tube Tunnel is novel in the field of high-speed aerodynamic testing, and may be implemented by other universities to produce supersonic flows with a relatively small investment in hardware and laboratory space.

This diploma thesis has been elaborated within the Master's study of department 2307 that submits a production hooped component. The material of the component is steel ČSN 15 130. Single – part as far as small–lot production. On the basis of the literary study problems bend tubing was sugested the method: rotary draw bending. For this method was sugested mechanical bending machine with mandrel support arm, for bending with mandrel and exact bends in three – dimensional.

The thesis describes the knowledge from a round tube bending technology, as a description of conventional and unconventional devices. There are technological parameters in relation to the creation of defects, and equations for determining the bending moment. These knowledge has been generalized and applied to solution the changes of cross-section shape and thickness in the bending of square cross-section. The solution was implemented to specific component (20x2 mm steel tube with two successive radii R57,2 and R131,5). The results of experiments shows that the material is almost rigid-perfectly plastic, in the most stressed areas has a sufficient supply of material formability. Thickness measurement was applied to calculate the approximate center of gravity changes. This shows a shift of 1.4 mm, which is negligible value for the pure bending. The end of the thesis summarizes the deficiencies of current manufacturing technology, which used mandrel is inadequate, wrong located and poor lubrication.