L'hydrure d'aluminium AlH3 ou alane est à la fois un matériau très important et une espèce chimique fascinante qui reçoit actuellement un regain d'intérêt lié à son utilisation potentielle pour différentes applications : (i) comme additif énergétique pour les ergols solides, (ii) comme agent réducteur dans les piles alcalines et (iii) comme source possible d'hydrogène pour des piles à combustibles basses températures. L'alane a une capacité de stockage volumique d'hydrogène de 0,148 g mL-1 soit deux fois plus que l'hydrogène liquide (0,07 g mL-1). Sa capacité de stockage d'hydrogène est supérieure à 10 % en masse. Malheureusement, le coût de production d'alane est élevé ce qui limite son utilisation notamment dans le domaine de la propulsion. L'objectif de cette thèse était d'optimiser la synthèse de l'alane α pur, variété cristalline considérée comme la plus stable et ainsi d'en réduire les coûts de production. Différentes méthodes de synthèse sous atmosphère contrôlée ont été mises en oeuvre. Il a été montré que le traitement thermique sous vide d'un complexe éthéré de AlH3 permettait de s'affranchir de l'utilisation de toluène et ainsi de réduire la quantité de solvants et de réactifs de 25 % tout en obtenant une phase α pure mise en évidence par DRX. Des essais de stabilisation contrôlés par ATD-ATG ont montré que la température de décomposition à pression atmosphérique de l'alane α était de 174 °C contre 160 °C pour la phase α non stabilisée. Une autre voie de synthèse, sans solvant et à l'aide d'une presse fabriquée au laboratoire a été explorée. Un plan d'expériences a été réalisé afin d'identifier les paramètres influant le plus sur le rendement en alane α et la pureté de la phase obtenue. L'alane synthétisé par ces différentes méthodes a été caractérisé par DRX, MEB, MET, ATD-ATG et ICP-OES. Un transfert technologique de la synthèse en solution a été opéré vers les partenaires industriels de ce travail. / Aluminium hydride or alane (AlH3) is a very important and fascinating material that draws increasing attention due to its potential uses: (i) as an energetic component in rocket propellants, (ii) as a reducing agent in alkali batteries and (iii) as a possible hydrogen source for low temperature fuel cells. It exhibits a density of 1,48 g cm-3, a volumetric hydrogen capacity of 0,148 g mL-1, that is more than twice as much as that of liquid hydrogen (0,07 g mL-1). Its hydrogen mass capacity slightly exceeds 10 wt.-%. Unfortunately, production of alane suffers from a high cost that hinders its opportunity to be an excellent candidate for propulsion. Moreover, only the α phase of alane is known to be stable enough to be stored and used. This work aims at developing cheaper methods for alane production while keeping a maximum selectivity towards the formation of α phase. Preparation using a classical organometallic synthesis in ether was implemented. An etherate complex was formed, the ether was removed under vacuum and finally an adequate thermal treatment led to pure α phase of alane as identified by powder X-ray diffraction. A toluene free synthesis method was implemented and resulted in a cost reduction of 25 %. The stability of the material was characterized through thermal analysis (DTA-TGA). The morphology and purity of the alane were characterized using TEM, SEM and ICP-OES. Alane was synthesized using doping compounds and resulted in a significant increase in the decomposition temperature from ca. 160 °C to ca. 174 °C. Syntheses without solvent were studied using a homemade reactor and following a design of experiment to identify the key parameter towards the highest yield in α-AlH3. The synthesis method in ether was transferred to our industrial partners.

This thesis deals with the experimental and numerical analysis of the water hammer phenomenon generated by the discharge of a pressurized liquid into a pipeline kept under vacuum conditions. This flow configuration induces several multiphase phenomena such as cavitation and gas desorption that cannot be ignored in the water hammer behavior.<p><p>The motivation of this research work comes from the liquid propulsion systems used in spacecrafts, which can undergo fluid hammer effects threatening the system integrity. Fluid hammer can be particularly adverse during the priming phase, which involves the fast opening of an isolation valve to fill the system with liquid propellant. Due to the initial vacuum conditions in the pipeline system, the water hammer taking place during priming may involve multiphase phenomena, such as cavitation and desorption of a non-<p>condensable gas, which may affect the pressure surges produced in the lines. Even though this flow behavior is known, only few studies model the spacecraft hardware configuration, and a proper characterization of the two-phase flow is still missing. The creation of a reliable database and the physical understanding of the water hammer behavior in propulsion systems are mandatory to improve the physical models implemented in the numerical codes used to simulate this flow configuration.<p><p>For that purpose, an experimental facility modeling a spacecraft propulsion system has been designed, in which the physical phenomena taking place during priming are generated under controlled conditions in the laboratory using inert fluids. An extended experimental campaign was performed on the installation, aiming at analyzing the effect of various working parameters on the fluid hammer behavior, such as the initial pressure in the line, liquid saturation with the pressurant gas, liquid properties and pipe configuration. The influence of the desorbed gas during water hammer occurrence is found to have a great importance on the whole process, due to the added compressibility and lower speed of sound by an increasing amount of non-condensable gas in the liquid + gas mixture. This results in lower pressure levels and faster pressure peaks attenuation, compared to fluids without desorption. The two-phase flow was characterized by means of flow visualization of the liquid front at the location where the fluid hammer is generated. The front arrival was found to be preceded by a foamy mixture of liquid, vapor and non-condensable gas, and the pressure wave reflected at the tank may induce the liquid column separation at the bottom end. While column separation takes place, the successive pressure peaks are generated by the impact of the column back against the bottom end.<p><p>The resulting experimental database is then confronted to the predictions of the 1D numerical code EcosimPro/ESPSS used to assess the propulsion system designs. Simulations are performed with the flow configuration described before, modeling the experimental facility. The comparison of the numerical results against the experimental data shows that aspects such as speed of sound computation with a dissolved gas and friction modeling need to be improved. / Doctorat en Sciences de l'ingénieur / info:eu-repo/semantics/nonPublished

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Idag är de vanligaste använda raketerna flytande-bränsle- och fast-bränsle- raketer. Flytande-bränsle-raketer har fördelen att det kan manövreras men de har en komplex design och problem med förvaring. Fast-bränsle-raketer har en enkel design och kan förvaras men de har en miljöpåverkan och bränslet kan vara svårhanterligt. En tredje typ av raketer, hybridraketer, kan kombinera enkelheten från fasta-bränsle-raketer med manövreringsbarheten från vätske-bränsle-raketer. Trots fördelarna med hybridraketer används de inte på grund av att bränslet har låg regressionshastighet och låg densitet. Organiska additiv har visat sig förbättra dessa egenskaper. 50 organiska additiv granskades med avseende på deras specifika impuls, densitet, kostnad och användarvänlighet. De mest lovande organiska additiven utvärderades sedan experimentellt. Termogravimetrisk analys (TGA), isotermviktförlust, kompatibilitet och differentiell svepkalorimetri (DSC) användes. Resultaten indikerar att hexamin, fluorene, anthracene och 1,4-dicyanobenzene har mest potential att förbättra bränslet i hybridraketer. / Liquid propellant and solid propellant rockets are the most commonly used rockets Liquid propellant rockets have the advantage of being manoeuvrable with a high specific performance while they exhibit problems with storage and a complex design. Solid propellant rockets offer simplicity and are storable while they have a large environmental impact and could be difficult to handle. A third type of rocket, hybrid propellant rocket has the potential to combine the simplicity of solid propellant rocket with the manoeuvrability of liquid propellant rockets. While the hybrid propellant rocket offers advantages over liquid propellant and solid propellant rocket it have problems with its fuel which have a low regression rate and low density. Organic fillers were evaluated since they may increase in the regression rate and the density of the solid fuel. 50 organic fillers were assessed with regards to their specific impulse, density, cost and handling properties. The organic fillers with the most promising properties were then experimentally evaluated. Thermogravimetric analysis (TGA), isothermal weight loss test, compatibility test and differential scanning calorimetry analysis were conducted. The results indicate that hexamine, fluorene, anthracene and 1,4-dicyanobenzene are the most suitable organic fillers of those evaluated..

<p>As the small satellite market has grown from a niche of the space economy to a full commercial force,  microthrusters remain an area of significant growth in the space industry as new technologies mature. The \textit{Film-Evaporation Microelectricalmechanical Tunable Array} (FEMTA) is one such device. FEMTA is \textit{microelectricalmechanical system} (MEMS) device that harnesses the microcapillary action of water and vacuum boiling to generate thrust. The water propellant is not chemically altered at all by the process; it is simply evaporated. This technology has been tested in relevant laboratory environments, and a suborbital flight opportunity in 2023 as a payload on a Blue Origin New Shepard rocket  will grant FEMTA a demonstration in a space environment. The flight will provide 150 seconds of weightlessness at the zenith of the suborbital flight path before the booster returns to land. During weightlessness, the experiment will be exposed to the ambient environment allowing for a full capability test of the thruster. The experiment is meant to demonstrate the propellant management system for FEMTA in 0G and measure the thrust produced by a FEMTA thruster.</p> <p><br></p> <p>The propellant management system portion of the experiment consists of an oversized version of the subsystem intended for use in the thruster. The propellant management system uses a hydrofluoroether to inflate a diaphragm to ensure constant wetting of the propellant tank exit and nozzle inlet. The experiment will take tank pressure data and flow sensor data to understand the system's behavior. The system is duplicated for redundancy and to double the possible data. This system requires further testing before being prepared for launch, vibrational testing, thermal testing, and vacuum testing. </p> <p><br></p> <p>The 0G thrust experiment and plume analysis portion of the experiment consists of numerical modeling and a novel thrust measurement approach. \textit{Direct Simulation Monte Carlo} (DSMC) is being applied to understand the pressure, density, and temperature distributions of the plume of water vapor produced by the FEMTA thruster. The FEMTA nozzle environment is challenging to simulate with computational fluid dynamics  or DSMC due to chaotic transient effects and because both the continuum and molecular regimes must be considered. The current analysis consisted of a two-dimensional model and investigated the effect of meniscus location and contact angle on thrust generated.</p> <p><br></p> <p>It is not possible to use traditional thrust measurement devices (sensitive torsional thrust stands or microsensors intended for use on small satellites) for microthrusters on a rocket booster. Two  novel approaches for performing thrust measurement in the range of 100 microNewtons have been investigated. The first approach ionizes the FEMTA thruster plume and analyzes the plasma by optical emission spectroscopy. The theory states that the relative intensity of a given wavelength observed correlates to the density of the species in the plasma. The density of water would be directly correlated to the thrust generated by FEMTA during the experiment, as more water is evaporated as thrust is increased. This method is no longer being considered for the suborbital experiment but did yield promising results. </p> <p><br></p> <p>The second approach employs a d'Arsonval meter, a photo-interrupt, and an Arduino controller. The d'Arsonval meter consists of a stationary permanent magnet with a moving coil and a pointer. Increasing the voltage in the coil causes a torque on the system due to the magnetic field induced by the permanent magnet. This torque causes a deflection of the pointer that is proportional to the voltage applied. The flag of the sensor will be placed in the path of the gas jet from the thruster. The force caused by the jet pressure will move the flag. An Arduino controller will vary the voltage to hold the flag in place. As the mass flow rate increases, the reaction force required to hold the flag in place will increase. This sensor can be calibrated using an analog cold gas system that passes various gases (air nitrogen, argon, etc.) through an orifice nozzle at mass flow rates that are set by a mass flow rate controller. DSMC analysis has been performed to understand the flow field and flow properties and how they directly relate to the force experienced by the flag sensor. </p> <p>An undergraduate course has supported parts of the work described in this dissertation. This course has applied the Vertically Integrated Projects approach to project-based learning. This method and its results were analyzed and lessons learned as well as a blueprint for future application of this method to other small satellite projects are discussed.</p>

Fast-bränsle-raketer (SRM) har funnit sin plats i en stor mängd tillämpningar sedan deras framkomst mer än 2000 år sedan. En SRMs prestanda är förutbestämd av geometrin av drivmedelskrutet och är begränsad av gjutningsmetoden, som idag främst används i produktion. Forskning inom 3D-skrivning av drivmedelskrut har undersökt nya komplexa geometrier som kan öka prestandan. Studier kring 3D-skrivning med UV-härdning är få till antalet och undersöks i detta projekt. Ett bindemedel av polyuretandiakrylat (PUDA) har syntetiserats och därefter karakteriserats, med och utan diverse monomerer genom dragprovsmätningar och differentialkalorimetri (DSC). Tillsats av tvärbindarna 1,6-hexandioldiakrylat (HDDA) samt trimetylolpropantriakrylat (TMPTA) till PUDA producerade ett mer sprött material. Denna skillnaden var mer påtaglig för TMPTA än HDDA, vilket tillskrivs den högre akrylatfunktionaliteten i den förstnämnda. Den kommersiella produkten Ebecryl 113 har karakteriserats med inerta fyllmedel. Härddjupet (DOC) undersöktes med Ebecryl 113 i ett experiment, vilket påvisade en minskning av härddjupet med ökande mängder aluminium. Orsaken är troligen de reflektiva egenskaperna för UV-ljus som aluminium innehar. Reologiska studier utfördes, från vilka en minskning i viskositet påvisades till följd av en ökad polydispersitet i partikelstorlekarna. 3D-skrivning med kolvextrudering och påföljande härdning med UV-strålning utforskades. Detta visade utmaningar med tekniken som behövs bemästras. I synnerhet uppmärksammades fasseparation och residuell härdning från reflekterat UV-ljus som begränsande faktorer för fortsatt arbete. / Solid rocket motors (SRMs) have found their place in many applications since their conception more than 2000 years ago. The performance of SRMs is determined by the geometry of the propellant grain and is limited by the cast-and-mould production method typically used today. Research has been made on 3D printing propellant grains to explore new complex geometries, which may increase performance. Studies on 3D printing techniques using UV curing are limited and are in this work investigated. A polyurethane diacrylate (PUDA) binder was synthesized and then characterized, with and without various monomers by tensile testing and differential scanning calorimetry. Additions of the crosslinkers 1,6-hexanediol diacrylate (HDDA) and trimethylolpropane triacrylate (TMPTA) to PUDA rendered the final product more brittle. This change was more noticeable for TMPTA than HDDA, as the former has a higher acrylate functionality. The commercial product Ebecryl 113 was also characterized with inert fillers added. A depth of cure (DOC) study with Ebecryl 113 was conducted, which showed a decrease in DOC with increasing amounts of aluminium. This is attributed to the reflective properties of aluminium in the UV spectrum. Rheological studies were conducted and a decrease in viscosity could be seen as a result of increasing the polydispersity of particle sizes. A 3D printing technique using plunger extrusion followed by UV curing was explored, which highlighted challenges which need to be overcome. Most notably, phase separation and residual curing from scattered UV rays are limiting factors for future work.

<p dir="ltr">Laser absorption spectroscopy (LAS) is a widely used technique to acquire path-integrated measurements of gas properties such as temperature and mole fraction. Although extremely useful, the application of LAS to study heterogeneous combustion environments can be challenging. For example, beam steering can be one such challenge that arises during measurements in heterogeneous combustion environments such as metallized propellant flames or measurements at high-pressure conditions. The ability to only obtain path integrated measurements has been a major challenge of conventional LAS techniques, especially in characterizing combustion environments with a non-uniform thermo-chemical distribution along the line of sight (LOS). Additionally, simultaneous measurements of multiple species using LAS with narrow-bandwidth lasers often necessitates employing multiple light sources. Aerospace applications, such as characterizing hypersonic flows may require ultrashort time resolution to study fast-evolving chemistry. Similarly, atmospheric entry most often requires measurements of atoms and molecules that absorb at wavelengths ranging from ultraviolet to mid-infrared. The availability of appropriate light sources for such measurements has been limited. In the past, several researchers have come up with diagnostic techniques to overcome the above-mentioned challenges to a certain extent. Most often, these solutions have been need-based while compromising on other diagnostic capabilities. Therefore, LAS diagnostics capable of acquiring broadband measurements with ultrafast time resolution and the ability to acquire measurements at wavelengths in ultraviolet through mid-infrared is required to study advanced combustion systems and for the development of advanced aerospace systems for future space missions. Ultrafast laser absorption spectroscopy is one such technique that provides broadband measurements, enabling simultaneous multi-species and high-pressure measurements. The light source utilized for ULAS provides the ultrafast time resolution necessary for resolving fast-occurring chemistry and more importantly the ability to acquire measurements at a wide range of wavelengths ranging from ultraviolet to far-infrared. The development and application of ULAS for characterizing propellant flames and hypersonic flows under non-equilibrium conditions by overcoming the above-mentioned challenges is presented here. </p><p>This work describes the development of a single-shot ultrafast laser absorption spectroscopy (ULAS) diagnostic for simultaneous measurements of temperature and concentrations of CO, NO, and H₂O in flames and aluminized fireballs of HMX (C₄H₈N₈O₈). Ultrashort (55 fs) pulses from a Ti:Sapphire oscillator emitting near 800 nm were amplified and converted into the mid-infrared through optical parametric amplification (OPA) at a repetition rate of 5 kHz. Ultimately, pulses with a spectral bandwidth of ≈600 cm^-1 centered near 4.9 µm were utilized in combination with a mid-infrared spectrograph to measure absorbance spectra of CO, NO, and H₂O across a 30 nm bandwidth with a spectral resolution of 0.3 nm. The gas temperature and species concentrations were determined by least-squares fitting simulated absorbance spectra to measured absorbance spectra. Measurements of temperature, CO, NO, and H₂O were acquired in an HMX flame burning in air at atmospheric pressure and the measurements agree well with previously published results. Measurements were also acquired in fireballs of HMX with and without 16.7 wt% H-5 micro-aluminum. Time histories of temperature and column densities are reported with a 1-σ precision of 0.4% for temperature and 0.3% (CO), 0.6% (NO), and 0.5% (H₂O), and 95% confidence intervals (C.I.) of 2.5% for temperature and 2.5% (CO), 11% (NO), and 7% (H₂O), thereby demonstrating the ability of ULAS to provide high-fidelity, multi-parameter measurements in harsh combustion environments. The results indicate that the addition of the micron-aluminum increases the fireball peak temperature by ≈100 K and leads to larger concentrations of CO. The addition of aluminum also increases the duration fireballs remain at elevated temperatures above 2000 K.</p><p dir="ltr">Next, the application of ULAS for dual-zone temperature and multi-species (CO, NO, H₂O, CO₂, HCl, and HF) measurements in solid-propellant flames is presented. ULAS measurements were acquired at three different central wavelengths (5.121 µm, 4.18 µm, and 3.044 µm) for simultaneous measurements of temperature and: 1) CO, NO, and H₂O, 2) CO₂ and HCl, and 3) HF and H₂O. Absorption measurements with a spectral resolution of 0.35 nm and bandwidth of 7 cm^-1, 18 cm^-1, and 35 cm^-1, respectively were acquired. In some cases, a dual-zone absorption spectroscopy model was implemented to accurately determine the gas temperature in the hot flame core and cold flame boundary layer via broadband absorption measurements of CO₂, thereby overcoming the impact of line-of-sight non-uniformities. Results illustrate that the hot-zone temperature of CO₂ agrees well with the equilibrium flame temperature and single-zone thermometry of CO, the latter of which is insensitive to the cold boundary layer due to the corresponding oxidation of CO to CO₂.</p><p dir="ltr">The initial development and implementation of an ultraviolet and broadband ultrafast-laser-absorption-imaging (UV-ULAI) diagnostic for one dimensional (1D) imaging of temperature and CN via its <i>B</i>²Σ⁺←<i>X</i>²Σ⁺absorption bands near 385 nm. The diagnostic was demonstrated by acquiring single-shot measurements of 1D temperature and CN profiles in HMX flames at a repetition rate of 25 Hz. Ultrashort pulses (55 fs) at 800 nm were generated using a Ti:Sapphire oscillator and then amplification and wavelength conversion to the ultraviolet was carried out utilizing an optical parametric amplifier and frequency doubling crystals. The broadband pulses were spectrally resolved using a 1200 l/mm grating and imaged on an EMCCD camera to obtain CN absorbance spectra with a resolution of ≈0.065 nm and a bandwidth of ≈4 nm (i.e. 260 cm^-1). Simulated absorbance spectra of CN were fit to the measured absorbance spectra using non-linear curve fitting to determine the gas properties. The spatial evolution of gas temperature and CN concentration near the burning surface of an HMX flame was measured with a spatial resolution of ≈10 µm. 1D profiles of temperature and CN concentration were obtained with a 1-σ spatial precision of 49.3 K and 4 ppm. This work demonstrates the ability of UV-ULAI to acquire high-precision, spatially resolved absorption measurements with unprecedented temporal and spatial resolution. Further, this work lays the foundation for ultraviolet imaging of numerous atomic and molecular species with ultrafast time resolution.</p><p dir="ltr">Ultraviolet ULAS was applied to characterize the temporal evolution of non-Boltzmann CN (<i>X</i>²Σ⁺) formed behind strong shock waves in N₂-CH₄ mixtures at conditions relevant to entry into Titan's atmosphere. An ultrafast (femtosecond) light source was utilized to produce 55 fs pulses near 385 nm at a repetition rate of 5 kHz and a spectrometer with a 2400 lines/mm grating was utilized to spectrally resolve the pulses after passing through the Purdue High-Pressure Shock Tube. This enabled broadband single-shot absorption measurements of CN to be acquired with a spectral resolution and bandwidth of ≈0.02 nm and ≈6 nm (≈402 cm^-1 at these wavelengths), respectively. A line-by-line absorption spectroscopy model for the <i>B</i>²Σ⁺←<i>X</i>²Σ⁺ system of CN was developed and utilized to determine six internal temperatures (two vibrational temperatures, four rotational) of CN from the (0,0), (1,1), (2,2) and (3,3) absorption bands. Measurements were acquired behind reflected shock waves in 5.65% CH₄ and 94.35% N₂ with an initial pressure of 1.56 mbar and incident shock speed of ≈2.1 km/s. For this test condition, the chemically and vibrationally frozen temperature of the mixture behind the reflected shock was 5000 K and the pressure was 0.6 atm. The high repeatability of the shock-tube experiments (0.3% variation in shock speed across tests) enabled multi-shock time histories of CN mole fraction and six internal temperatures to be acquired with a single-shot time resolution of less than 1 ns. The measurements revealed that CN <i>X</i>²Σ⁺ is non-Boltzmann rotationally and vibrationally for greater than 200 µs, thereby strongly suggesting that chemical reactions are responsible for the non-Boltzmann population distributions. </p><p><br></p>

Thesis is focused on fight against indirect tax evasion. This topic was selected because it is a current issue. This is evidenced by media coverage regarding revealed tax evasion schemes; total estimated volume of tax evaded and increased activity of legislator in this field. The thesis is divided into three parts. In first part, I start with a general description of indirect taxes. I subsequently proceed with description of individual indirect taxes in the Czech Republic - value added tax, excise tax, and energy tax - and a brief summary of their evolution, main principles of functioning and their sources of law, both Czech and European. In second part, I tackle the problem of tax optimization, in particular the difference between legal and illegal methods of lowering ones tax. For this purpose, I go into more detail in explaining differences between tax planning, tax avoidance and tax evasion. I also draw attention to problems related to distinguishing these categories and to how these are interpreted differently by tax authorities in Anglo-Saxon and Continental area. After establishing theoretical background, I proceed by describing particular methods of evading tax, focusing mainly at illegal imports and carousel fraud, which, according to the Ministry of Finance, deprives Czech Republic of CZK 15...

The present research is an experimental and numerical study of aeroacoustic phenomena occurring in large solid rocket motors (SRM) as the Ariane 5 boosters. The emphasis is given to aeroacoustic instabilities that may lead to pressure and thrust oscillations which reduce the rocket motor performance and could damage the payload. The study is carried out within the framework of a CNES (Centre National d'Etudes Spatiales) research program. <p><p>Large SRM are composed of a submerged nozzle and segmented propellant grains separated by inhibitors. During propellant combustion, a cavity appears around the nozzle. Vortical flow structures may be formed from the inhibitor (Obstacle Vortex Shedding OVS) or from natural instability of the radial flow resulting from the propellant combustion (Surface Vortex Shedding SVS). Such hydrodynamic manifestations drive pressure oscillations in the confined flow established in the motor. When the vortex shedding frequency synchronizes acoustic modes of the motor chamber, resonance may occur and sound pressure can be amplified by vortex nozzle interaction.<p><p>Original analytical models, in particular based on vortex sound theory, point out the parameters controlling the flow-acoustic coupling and the effect of the nozzle design on sound production. They allow the appropriate definition of experimental tests.<p><p>The experiments are conducted on axisymmetric cold flow models respecting the Mach number similarity with the Ariane 5 SRM. The test section includes only one inhibitor and a submerged nozzle. The flow is either created by an axial air injection at the forward end or by a radial injection uniformly distributed along chamber porous walls. The internal Mach number can be varied continuously by means of a movable needle placed in the nozzle throat. Acoustic pressure measurements are taken by means of PCB piezoelectric transducers. A particle image velocimetry technique (PIV) is used to analyse the effect of the acoustic resonance on the mean flow field and vortex properties. An active control loop is exploited to obtain resonant and non resonant conditions for the same operating point.<p><p>Finally, numerical simulations are performed using a time dependent Navier Stokes solver. The analysis of the unsteady simulations provides pressure spectra, sequence of vorticity fields and average flow field. Comparison to experimental data is conducted.<p><p>The OVS and SVS instabilities are identified. The inhibitor parameters, the chamber Mach number and length, and the nozzle geometry are varied to analyse their effect on the flow acoustic coupling.<p><p>The conclusions state that flow acoustic coupling is mainly observed for nozzles including cavity. The nozzle geometry has an effect on the pressure oscillations through a coupling between the acoustic fluctuations induced by the cavity volume and the vortices travelling in front of the cavity entrance. When resonance occurs, the sound pressure level increases linearly with the chamber Mach number, the frequency and the cavity volume. In absence of cavity, the pressure fluctuations are damped.<p><p> / Doctorat en sciences appliquées / info:eu-repo/semantics/nonPublished

<div>Since as early as the 1920s, dinitrogen tetroxide (N2O4) has been regarded as a promising oxidizer in rocket propulsion systems. In more recent times, its predecessor, mixed oxides of nitrogen (MON), remains a top contender among oxidizers, due to its unique characteristics such as low freezing temperature and compatibility with common spacecraft materials. Today, these N2O4-based oxidizers are the preferred choice in many upper stages, launch escape systems, reaction control systems, liquid apogee engines, and in-space primary propulsion systems. N2O4-based oxidizers are a key factor in rocket propulsion, and thoroughly understanding their history, development, characteristics, synthesis, and composition analysis are crucial for space exploration today and into the future.<br><br></div><div>To fully understand and predict the physical properties of a MON sample, it is important to measure and quantify its chemical composition. The recommended method for MON composition analysis, as prescribed by the Department of Defense’s Defense Specification (MIL-SPEC) document on N2O4, involves the oxidation of NO and dinitrogen trioxide (N2O3) in the MON sample to determine their amounts. An equation unofficially called the “MIL-SPEC equation” is then used to determine the amount of NO needed to mix with N2O4 to synthesize that particular MON sample. However, no explanation is given as to how the equation was derived, or its significance.<br><br></div><div>This thesis aims to collect and organize key information on the synthesis, handling, and composition analysis of MON propellant. First, the history of development of N2O4-based oxidizers was researched, and current and future uses of N2O4 and MON propellants were identified. Then a method for synthesis and composition analysis was devised and tested. Water contamination was expected of skewing the results, so the process of water contamination was examined analytically. Then a detailed derivation of the MIL-SPEC equation was conducted, to fully understand its mechanics. An attempt was then made to reverse-engineer an unexplained numerical value in the equation, labeled by the author as the “solubility factor”. Several derivations were provided with varying degrees of complexity, producing alternative solubility factors of varying accuracies. Finally, experimental data was applied to these derived, hypothetical solubility factors and the MIL-SPEC solubility factor, with the intent of determining whether improvements could be made to the MON composition determination process.<br><br></div><div>The results suggest that the MIL-SPEC equation is sufficient for providing a relatively accurate measurement of the composition of a MON sample, while also being easy to implement, both in taking the necessary measurements and in conducting the numerical calculation. However, some minor adjustments to the equation could produce consistently more accurate composition measurements without adding any more difficulty or complication.</div>