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Breil, Jérôme. "Modélisation du remplissage en propergol de moteur à propulsion solide". Bordeaux 1, 2001. http://www.theses.fr/2001BOR10505.
Pełny tekst źródłaDoisneau, François. "Eulerian modeling and simulation of polydisperse moderately dense coalescing spray flows with nanometric-to-inertial droplets : application to Solid Rocket Motors". Thesis, Châtenay-Malabry, Ecole centrale de Paris, 2013. http://www.theses.fr/2013ECAP0030/document.
Pełny tekst źródłaIn solid rocket motors, the internal flow depends strongly on the alumina droplets, which have a high mass fraction. The droplet size distribution, which is wide and spreads up with coalescence, plays a key role. Solving for unsteady polydisperse two- phase flows with high accuracy on the droplet sizes is a challenge for both modeling and scientific computing: (1) very small droplets, e.g. resulting from the combustion of nanoparticles of aluminum fuel, encounter Brownian motion and coalescence, (2) small droplets have their velocity conditioned by size so they coalesce when having different sizes, (3) bigger droplets have an inertial behavior and may cross each other’s trajectory, and (4) all droplets interact in a two-way coupled manner with the carrier phase. As an alternative to Lagrangian approaches, some Eulerian models can describe the disperse phase at a moderate cost, with an easy coupling to the carrier phase and with massively parallel codes: they are well-suited for industrial computations. The Multi- Fluid model allows the detailed description of polydispersity, size/velocity correlations and coalescence by separately solving “fluids” of size-sorted droplets, the so-called sections. In the present work, we assess an ensemble of models and we develop a numerical strategy to perform industrial computations of solid rocket motor flows. (1) The physics of nanoparticles is assessed and included in a polydisperse coalescing model. High order moment methods are then developed: (2) a Two-Size moment method is ex- tended to coalescence to treat accurately the physics of polydispersity and coalescence and the related numerical developments allow to perform applicative computations in the industrial code CEDRE; (3) a second order velocity moment method is developed, together with a second order transport scheme, to evaluate a strategy for a moderately inertial disperse phase, and academic validations are performed on complex flow fields; (4) a time integration strategy is developed and implemented in CEDRE to treat efficiently two-way coupling, in unsteady polydisperse cases including very small particles. The developments are carefully validated, either through purposely derived analytical formulae (for coalescence and two-way acoustic coupling), through numerical cross-comparisons (for coalescence with a Point-Particle DNS, for applicative cases featuring coalescence and two-way coupling with a Lagrangian method), or through available experimental results (for coalescence with an academic experiment, for the overall physics with a sub-scale motor firing). The whole strategy allows to perform applicative computations in a cost effective way. In particular, a solid rocket motor with nanoparticles is computed as a feasibility case and to guide the research effort on motors with nanoparticle fuel propellants
Muller, Mathieu. "Modélisation de la combustion de gouttes d'aluminium dans les conditions d'un moteur fusée à propergol solide". Thesis, Sorbonne université, 2019. http://www.theses.fr/2019SORUS267.
Pełny tekst źródłaThe purpose of this thesis is to study the aluminum (Al) droplet combustion in solid rocket motor propellant. We need to model this process to evaluate the burning time and the residues length because their characterization in real conditions is very complex. A combustion model of a single droplet with a multiphysical spherical approach has been developed taking into account various phenomena. This model has been validated and used to study gaseous and surface mechanisms. Simulations in controlled atmospheres were made and the results were compared to experimental data. The study of the combustion of two particle classes (primary particle and agglomerate) under conditions typical for the Ariane 5 solid booster was conducted to evaluate the effect of different heterogeneous surface kinetics on the simulated combustion process. After the integration of the reactive surface model in the ONERA code CEDRE, simulations of the combustion using a two-dimensional axisymmetric approach were made to study the impact of the cap on the droplet surface and the convection velocity of oxidizers. By simulating the established combustion of two droplet classes at two pressures (5 and 9 MPa) in different stages of combustion, we evaluated main characteristics of the combustion and we deducted a global burning law. Finally, the heating of the droplet before an established combustion was studied to complete the characterization
Poubeau, Adèle. "Simulation des émissions d'un moteur à propergol solide : vers une modélisation multi-échelle de l'impact atmosphérique des lanceurs". Thesis, Toulouse 3, 2015. http://www.theses.fr/2015TOU30039/document.
Pełny tekst źródłaRockets have an impact on the chemical composition of the atmosphere, and particularly on stratospheric ozone. Among all types of propulsion, Solid-Rocket Motors (SRMs) have given rise to concerns since their emissions are responsible for a severe decrease in ozone concentration in the rocket plume during the first hours after a launch. The main source of ozone depletion is due to the conversion of hydrogen chloride, a chemical compound emitted in large quantities by ammonium perchlorate based propellants, into active chlorine compounds, which then react with ozone in a destructive catalytic cycle, similar to those responsible for the Antartic "Ozone hole". This conversion occurs in the hot, supersonic exhaust plume, as part of a strong second combustion between chemical species of the plume and air. The objective of this study is to evaluate the active chlorine concentration in the far-field plume of a solid-rocket motor using large-eddy simulations (LES). The gas is injected through the entire nozzle of the SRM and a local time-stepping method based on coupling multi-instances of the fluid solver is used to extend the computational domain up to 400 nozzle exit diameters downstream of the nozzle exit. The methodology is validated for a non-reactive case by analyzing the flow characteristics of the resulting supersonic co-flowing under-expanded jet. Then the chemistry of chlorine is studied off-line using a complex chemistry solver applied on trajectories extracted from the LES time-averaged flow-field. Finally, the online chemistry is analyzed by means of the multi-species version of the LES solver using a reduced chemical scheme. To the best of our knowledge, this represents one of the first LES of a reactive supersonic jet, including nozzle geometry, performed over such a long computational domain. By capturing the effect of mixing of the exhaust plume with ambient air and the interactions between turbulence and combustion, LES offers an evaluation of chemical species distribution in the SRM plume with an unprecedented accuracy. These results can be used to initialize atmospheric simulations on larger domains, in order to model the chemical reactions between active chlorine and ozone and to quantify the ozone loss in SRM plumes
Richard, Julien. "Développement d'une chaîne de calcul pour les interactions fluide-structure et application aux instabilités aéro-acoustiques d'un moteur à propergol solide". Thesis, Montpellier 2, 2012. http://www.theses.fr/2012MON20256/document.
Pełny tekst źródłaLarge solid propellant rocket motors may be subjected to aero-acoustic instabilities arising from a coupling between the burnt gas flow and the acoustic eigenmodes of the combustion chamber. These instabilities lead to large pressure oscillations in the combustion chamber. These pressure oscillations cause vibrations which might jeopardize the payload if they happen to be larger than a certain threshold. Given the size and cost of any single firing test or launch, it is of first importance to rely on numerical tools able to predict these instabilities so that they can be avoided at the design level. The first purpose of this thesis is to build a numerical tool in order to evaluate how the coupling of the fluid flow and the whole structure of the motor influences the amplitude of the aeroacoustic oscillations living inside the rocket. A particular attention was paid to the coupling algorithm between the fluid and the solid solvers in order to ensure the best energy conservation through the interface.The numerical chain is applied to a sub-scaled configuration of Ariane 5 solid rocket motor in two studies. The first relates to the impact of vibration of the structure on aeroacoustic instabilities. The effect of a crossover frequency between the longitudinal modes of the structure and the acoustic modes of the combustion chamber is assessed. The second study examines the effect of thermal protection oscillations in the flow. An increased of the flow organisation and a significant strengthening of pressure oscillations are highlighted
Kiyoshi, Shimote Wilson. "Modélisation des phénomènes d'ablation de l'insert d'une tuyère de moteur-fusée à propergol solide. Approche expérimentale et numérique". Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2016. http://www.theses.fr/2016ESMA0028/document.
Pełny tekst źródłaThe main objective of this study is understand the ablation mechanisms in the presence of a critical environment in pressure and temperature within a solid propellant rocket motor. The well-known parameters, aluminum percentage in the flow, adiabatic flame temperature and the consequent heat flux in front of the geometry of the insert and its thermochemical properties are studied from anumerical and experimental strategy. The ablation phenomenon, which occurs at the nozzle insert during the operation of the solid propellant rocket motor, is th us studied and results of tests of the small and full-scale motors are presented as well as numerically simulated. Indeed, tests carried-out provide results on the conditions of the material of the insert before and after firing tests, do not allow is to provide a complete analysis of the development of the mechanisms involved during the running time of the engines. To introduce these rather complex physical phenomena a strategy of progressive development is followed. Initially, a 1D model treated the heat transfer equations using a multi-block numerical discretization technique. From the 1D method, simple expressions to represent the evolution of the ablation and pyrolysis fronts are defined. These expressions are then used directly on the treatment of axisymmetric problems and confronted with simulations of the scale motor. Finally, the immersed boundary method is applied to tackle coupling between flow and heat transfer on the insert, highlighting the phenomenon of ablation. The numerical simulations reproduce the experimental results and show a robust numerical methodology, corresponding to expectations in what concerns the evaluation of the ablation phenomenon within a solid propellant rocket motor nozzle
Pascal, Jérôme. "Vitesse de combustion d'un propergol solide composite en présence d'oscillations de la vitesse de l'écoulement". Paris 11, 1987. http://www.theses.fr/1987PA112066.
Pełny tekst źródłaBreton, Mélanie. "Détection de l'allumage d'un moteur-fusée à propergol solide avec une matrice linéaire de filtres holographiques et par diffraction conique". Thesis, Université Laval, 2007. http://www.theses.ulaval.ca/2007/24914/24914.pdf.
Pełny tekst źródłaLacassagne, Laura. "Simulations et analyses de stabilité linéaire du détachement tourbillonnaire d'angle dans les moteurs à propergol solide". Phd thesis, Toulouse, INPT, 2017. http://oatao.univ-toulouse.fr/17932/1/Lacassagne_Laura_INPT.pdf.
Pełny tekst źródłaSilvestrini, Jorge Hugo. "Simulation des grandes échelles des zones de mélange : application à la propulsion solide des lanceurs spatiaux". Grenoble INPG, 1996. http://www.theses.fr/1996INPG0104.
Pełny tekst źródłaDoisneau, François. "Modélisation et simulation d'écoulements diphasiques polydisperses modérément denses chargés de particules nonométriques à modérément inertielles avec coalescence : application aux moteurs à propergol solide". Phd thesis, Ecole Centrale Paris, 2013. http://tel.archives-ouvertes.fr/tel-00966185.
Pełny tekst źródłaBernigaud, Pierre. "Modélisation de la combustion des matériaux énergétiques nouvelle génération". Electronic Thesis or Diss., Institut polytechnique de Paris, 2023. http://www.theses.fr/2023IPPAE017.
Pełny tekst źródłaUsed in civil and military rocket engines, composite propellants are characterized by a heterogeneous structure at the microscopic level. They consist mainly of oxidizer particles embedded in a polymer matrix known as the binder. The binder maintains the structural integrity of the propellant, and produces via its pyrolysis gases whose combustion is responsible for most of the heat release within the flame. The combustion products of the oxdizer particles oxidize the fuel generated by the binder.Ammonium perchlorate (AP) is a widely used oxidizing agent in composite propellants, mainly in association with a polymer binder such as hydroxytelechelic polybutadiene (HTPB). Next-generation propellants could include nitramines in their composition, such as hexogen (RDX), as a partial replacement for AP for certain specific purposes. In particular, reducing the amount of AP contained in the propellant can limit the formation of a visible trail at the engine exhaust, reducing the vehicle's signature.In this thesis, we propose to revisit the studies carried out on the combustion of conventional AP/HTPB propellants, and to characterize the effect of RDX inclusion in their composition.To this end, the first part of the thesis is dedicated to the development of combustion models for the ingredients under consideration: AP, homogenized AP/HTPB blend, and RDX.A chemical kinetics mechanism is assembled, capable of representing the chemical processes characteristic of the combustion of all these energetic materials. For each ingredient, a condensed-phase decomposition model is also formulated, to be associated with the kinetic mechanism. One-dimensional simulations are then carried out using a coupled flame/solid approach, in order to validate the whole on available experimental data.Due to their heterogeneous structure, the study of composite propellant combustion requires the use of multidimensional numerical methods. A second part of the thesis is therefore dedicated to the development and validation of a 2D calculation code, enabling the simulation of the combustion of an oxidizer particle surrounded by a layer of binder, in an axisymmetric configuration.In a final section, the combustion models and the computational code are used in conjunction to study the effect of RDX inclusion in a conventional AP/HTPB propellant. For the first time, the flame structure produced by such AP/HTPB/RDX propellant is obtained and characterized. The effect of pressure and RDX particle size on propellant regression is investigated, demonstrating the existence of different combustion regimes. Recommendations are made for optimizing the performance of this type of composition
Cesco, Nathalie. "Étude et modélisation de l'écoulement diphasique à l'intérieur des propulseurs à poudre". Toulouse, ENSAE, 1997. http://www.theses.fr/1997ESAE0019.
Pełny tekst źródłaBriault, Pauline. "Développement d'une cellule SOFC de type monochambre pour la conversion en électricité des gaz d'échappement d'un moteur thermique". Phd thesis, Ecole Nationale Supérieure des Mines de Saint-Etienne, 2014. http://tel.archives-ouvertes.fr/tel-00993720.
Pełny tekst źródłaGenot, Aurélien. "Instabilités thermoacoustiques dans les moteurs à propergol solide". Thesis, Université Paris-Saclay (ComUE), 2019. http://www.theses.fr/2019SACLC032/document.
Pełny tekst źródłaIn a solid rocket motor, self-sustained thermo-acoustic instabilities, induced by the coupling of the combustion dynamics of aluminum droplets released by the burning propellant with the acoustic field can induce pressure oscillations.The analysis conducted throughout this manuscript relies thus on a set of simplifying hypothesis by assuming (i) that the response of the combustion of aluminum droplets to acoustic perturbations is controlled by the oscillating drag exerted by the local flow around the droplet, (ii) that this unsteady combustion process can be assumed quasi-steady for the range of frequencies and acoustic amplitudes studied and (iii) that aluminum combustion is abruptly quenched when the aluminum droplet diameter falls below a residual diameter.The thermo-acoustic instability is studied first by numerical flow simulations in a generic solid rocket motor and theoretical analyses. The post-combustion residual diameter of the aluminum particles, the amplitude of acoustic perturbation and the lifetime of the burning aluminum droplets are among the main parameters altering the instability. Also, three combustion response behaviors to acoustics are identified : a linear behavior for small acoustic pressure levels followed by a quadratic behavior then a highly non-linear behavior when the pressure amplitude increases in the motor chamber. Moreover, two important features of the response of aluminum droplets are identified. They are associated to oscillations of the droplet lifetime at the boundary of the droplet cloud and to fluctuations of the droplet evaporation rate, controlled by convection. The dynamics of the droplets highly depends on gas and droplet velocity fields and on droplet diameter. Taking these features into account, yields analytical expressions that allow to reproduce with accuracy the numerical results from the flow simulations. Four dimension less numbers are then identified. They govern the dynamics of these instabilities. Inspired from the previous theoretical analysis, a weakly nonlinear low-order numerical model is finally developed to predict limit cycles
Chedevergne, François. "Instabilités intrinsèques des moteurs à propergol solide". Toulouse, ENSAE, 2007. http://www.theses.fr/2007ESAE0009.
Pełny tekst źródłaCerqueira, Stéphane. "Étude du couplage aéro-mécanique au sein des moteurs à propergol solide". Thesis, Paris, ENMP, 2012. http://www.theses.fr/2012ENMP0011/document.
Pełny tekst źródłaFluid Structure Interaction of an inhibitor with the internal flow induced by wall injection was studied in an axisymmetric cold flow apparatus. Experiments were carried out over a wide range of injection velocities in order to underline how the obstacle not only modifies the mean flowfield but also its entire dynamic behaviour.The resulting instability (from the interaction of the unstable shear layer with the Taylor-Culick flow) exhibits a significant shift with respect to the Taylor-Culick instability and therefore emphasizes the strong impact of the inhibitor on hydrodynamics.The mecanisms responsible of such behaviour are studied in this thesis with the help of global linear stability analysis and multi-physics numerical computations
Joumani, Youssef. "Transferts radiatifs dans les moteurs à propergol solide". Valenciennes, 2001. https://ged.uphf.fr/nuxeo/site/esupversions/95e74661-8e9a-4d99-863a-817cdf44b81e.
Pełny tekst źródłaFeraille, Thierry. "Instabilités de l'écoulement interne des moteurs à propergol solide". École nationale supérieure de l'aéronautique et de l'espace (Toulouse ; 1972-2007), 2004. http://www.theses.fr/2004ESAE0008.
Pełny tekst źródłaCabrit, Olivier. "Modélisation des flux pariétaux sur les tuyères des moteurs à propergol solide". Montpellier 2, 2009. http://www.theses.fr/2009MON20239.
Pełny tekst źródłaThe nozzles of solid rocket motors must resist to severe wall fluxes. Carbon/carbon composite materials are then chosen to insure the structure integrity. In spite of their excellent thermo-mechanical properties, these materials are exposed to the ablation phenomenon: chemical oxidation of the solid material by the combustion products. On the one hand, this feature protects the nozzle structure since this process considerably reduces the wall heat flux. On the other hand, the ablation process must be perfectly controlled because of the geometrical changes induced by the surface recession. The assessment of mass/momentum/heat fluxes at the wall is thus a crucial part for the nozzle design. Numerical simulations are nowadays commonly used to define new nozzles. However, considering the power of the available computers, the use of wall models is a necessary step to simulate full scale devices. With this framework, one presents a set of direct numerical simulations whose analysis allows to derive new wall functions integrating several complex physical aspects that modify the "classical" behavior of the turbulent boundary layer: multicomponent reacting compressible flow, with non-unity Prandtl number, radiative transfer, streamwise pressure gradient, and wall ablation. These new models are now ready to be tested on realistic configurations
Dupuy, Magali. "Etude par simulations numériques instationnaires de l'écoulement dans les moteurs à propergol solide". Phd thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2012. http://tel.archives-ouvertes.fr/tel-00744017.
Pełny tekst źródłaBouyges, Maxime. "Instabilités dans les moteurs à propergol solide : influence de la géométrie étoilée et étude numérique de la transition laminaire-turbulent". Thesis, Toulouse, ISAE, 2017. http://www.theses.fr/2017ESAE0031/document.
Pełny tekst źródłaSolid rocket motors may exhibit thrust oscillations induced by pressure oscillations inside the engine. In the scientific literature, the so-called vortex shedding parietal, a hydrodynamic instability specific to the internal flow, has been proven to be the triggering mechanism through linear stability analyses. However, some questions still remain. These oscillations are observed during the second half of Ariane 5 launches only, the laminar-turbulent transition of the intern flow being expected to play a significant role in that behavior. Additionally, non-circular grain shapes used in some engines may impact the stability study. The present PhD work extends the base flow linear stability studies to star-shaped geometries and investigate transition mechanisms in a circular configuration. Firstly, an analytical expression of the base flow in a duct with a star-shaped cross-section is determined. Wall-normal injection is assumed, which is representative of solid rocket engines. The velocity profile may exhibit an inflection point depending on both the Reynolds number and wall radial deformation. Secondly, both local and biglobal stability analyses are applied to this flow. In contrast to the circular case, the flow may exhibit one or several unstable modes. Lastly, a large eddy simulation of the VALDO experimental test bench is performed. The influence of the acoustic impedance of the outflow boundary condition on the amplitude of pressure oscillations is highlighted
Basset, Thierry. "Contribution à la modélisation des écoulements diphasiques et réactifs internes : application aux propulseurs à propergol solide". Aix-Marseille 1, 1997. http://www.theses.fr/1997AIX11049.
Pełny tekst źródłaBoyer, Germain. "Étude de stabilité et simulation numérique de l’écoulement interne des moteurs à propergol solide simplifiés". Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0029/document.
Pełny tekst źródłaThe current work deals with the modeling of the hydrodynamic instabilities that play a major role in the triggering of the Pressure Oscillations occurring in large segmented solid rocket motors. These instabilities are responsible for the emergence of Parietal Vortex Shedding (PVS) and they interact with the boosters acoustics. They are first modeled as eigenmodes of the internal steady flowfield of a cylindrical duct with sidewall injection within the global linear stability theory framework. Assuming that the related parietal structures emerge from a baseflow disturbance, discrete meshindependant eigenmodes are computed. In this purpose, a multi-domain spectral collocation technique is implemented in a parallel solver to tackle numerical issues such as the eigenfunctions polynomial axial amplification and the existence of boundary layers. The resulting eigenvalues explicitly depend on the location of the boundaries, namely those of the baseflow disturbance and the duct exit, and are then validated by performing Direct Numerical Simulations. First, they successfully describe flow response to an initial disturbance with sidewall velocity injection break. Then, the simulated forced response to acoustics consists in vortical structures wihich discrete frequencies that are in good agreement with those of the eigenmodes. These structures are reflected into upstream pressure waves with identical frequencies. Finally, the PVS, which response to a compressible forcing such as the acoustic one is linear, is understood as the driving phenomenon of the Pressure Oscillations thanks to both numerical simulation and stability theory
Hirschberg, Lionel. "Modélisation des oscillations de pression auto-entretenues induites par des tourbillons dans les moteurs à propergol solide". Thesis, Université Paris-Saclay (ComUE), 2019. http://www.theses.fr/2019SACLC001/document.
Pełny tekst źródłaSolid Rocket Motors (SRMs) can display self-sustained acoustic oscillations driven by coupling between hydrodynamic instabilities of the internal flow and longitudinal acoustic standing waves. The hydrodynamic instabilities are triggered by the acoustic standing wave and results in the formation of coherent vortical structures. For nominal ranges of flow conditions the sound waves generated by the interaction between these vortices and the choked nozzle at the end of the combustion chamber reinforces the acoustic oscillation. Most available literature on this subject focuses on the threshold of instability using a linear model. The focus of this work is on the prediction of the limit-cycle amplitude. The limit-cycle is reached due to nonlinear saturation of the source, as a consequence of the formation of large coherent vortical structures. In this case the vortex-nozzle interaction becomes insensitive to the amplitude of the acoustic standing wave. Hence, one can focus on the sound generation of a vortex with the nozzle. Sound production can be predicted from an analytical two-dimensional planar incompressible frictionless model using the so-called Vortex Sound Theory. In this model the vorticity is assumed to be concentrated in a line vortex. Experiments indicate that the volume of cavities around so-called “integrated nozzles” have a large influence on the pulsation amplitude for large SRMs. This is due to the acoustical field normal to the vortex trajectory, induced by the compressibility of the gas in this cavity. As an alternative to the incompressible analytical model a compressible frictionless model with an internal Euler Aeroacoustic (EIA) flow solver is used for simulations of vortex-nozzle interaction. A dedicated numerical simulation study focusing on elementary processes such as vortex-nozzle and entropy spot-nozzle interaction allows a systematic variation of relevant parameters and yields insight which would be difficult by means of limit cycle studies of the full engine. A systematic study of the vortex-nozzle interaction in the case of a choked nozzle has been undertaken. The results are summarized by using a lumped element model for plane wave propagation, which is based on theoretical scaling laws. From EIA simulations it appears that sound due to vortex-nozzle interaction is mainly generated during the approach phase and that for the relevant parameter range there is no impingement of the vortex on the nozzle wall as has been suggested in the literature. Using an energy balance approach, a single fit-parameter model is formulated which qualitatively predicts limit-cycle observations in cold gas-scale experiments reported in the literature. Finally the Euler model is used to compare the sound production by vortex-nozzle interaction with that due to the ingestion of an entropy non-uniformity also called entropy spot. In addition to insight, this study provides a systematic procedure to develop a lumped element model for the sound source due to non-homogeneous flow-nozzle interactions in SRMs. Such lumped models based on experimental data or a limited number of flow simulations can be used to ease the design of SRMs
Touré, Abdou. "Étude théorique et expérimentale d'un moteur Ericsson à cycle de Joule pour conversion thermodynamique de l'énergie solaire ou pour micro-cogénération". Phd thesis, Université de Pau et des Pays de l'Adour, 2010. http://tel.archives-ouvertes.fr/tel-00546852.
Pełny tekst źródłaBinauld, Quentin. "Modélisation et simulation du rayonnement dans les jets de moteurs à propergol solide à haute altitude". Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLC090/document.
Pełny tekst źródłaRadiation from solid propellant rocketplumes is important for the prediction of thermalfluxes on vehicle walls and of plume signature. Athigh altitudes, of approximately 100 km, those plumesare characterized by two-phase compressible flows,highly rarefied in some regions, composed of aluminaparticles and exhaust combustion gases. Radiativetransfer plays an important role in the cooling and thephase change of the particles.In order to carry out numerical simulations of rocketplumes and their radiation, several models have beendeveloped. The radiation of the gas phase is takeninto account using statistical narrow bands models.The supercooling phenomenon has been modeled todeal with the phase change of alumina and to obtaincorrect temperature fields for the different size classesof particles. Finally, a splitting method of the radiativepower has been established to enable the couplingbetween radiation and the flow field under gas/particlethermal non-equelibrium. These models have beenimplemented in a calculation platform, enabling tocouple a Navier-Stokes solver for the gas phase, anEulerian solver dealing with the dispersed phase anda radiative solver based on a Monte Carlo method.The developed numerical tool has been partly validatedcomparing our results with the measurementsobtained during the BSUV2 experiment. In the conditionsof this experiment, particle radiation is shownto be predominant but the contribution of the gasphase is found to be non-negligible. Simulations underdifferent hypotheses have put the emphasis onthe importance of radiative transfer, coupled with thesupercooling phenomenon, for an accurate evaluationof particle temperature fields.The last part of this work focuses on the study ofgas vibrational non-equilibrium and its impact on radiationfrom high altitude plumes. It is shown thatthe slow deexcitation of vibrational levels of the CO2molecule during the plume expansion may increasesignificantly its radiation
Braconnier, Alexandre. "Étude expérimentale de la combustion d’une particule d’aluminium isolée : influence de la pression et de la composition de l’atmosphère oxydante". Thesis, Orléans, 2020. http://www.theses.fr/2020ORLE3140.
Pełny tekst źródłaAluminum powders have interesting energy properties and are currently integrated in some solid propellants to improve the performances of propulsion systems. However, the effects induced by the presence of dispersed particles within the propellant flow can alter the stability of the solid rocket motors (SRM) and the use of the energy potential of the aluminum particles can be optimized to further enhance engine efficiency. Therefore, modeling of the aluminum reaction process is a major issue to improve the predictive numerical tools used for SRM development. However, the understanding of the aluminum combustion is still limited and available experimental data are scarce, especially for SRM applications. Thus, based on a specific setup allowing to levitate a single aluminum particle in a controlled environment, this study has led to interesting results. Essential lines of research were introduced on the reaction phenomenology, mainly on the effects resulting from the accumulation of condensed products on the droplet surface during combustion. Different assumptions have also been discussed concerning the mechanisms involved in this process. In addition, a large amount of data was reported on characteristic combustion parameters, allowing the contribution of the parameters of the reactive environment to be defined. The oxidizing efficiency of O₂, CO₂ and CO has been quantified and carbon monoxide seems to act as an inert gas, as well as N₂. The effect of pressure on the burning time has also been determined and is almost limited. Finally, a new empirical law has been established to estimate the burning time of aluminum droplets according to their initial diameter and ambient conditions, suggesting that the aluminum reaction process cannot be described by the theoretical D² law
Acik, Sevda. "Internal Ballistic Design Optimization Of A Solid Rocket Motor". Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12611981/index.pdf.
Pełny tekst źródłaRacine, John A. "Subscale solid rocket motor infrared signature and particle behavior". Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/26801.
Pełny tekst źródłaGomes, Marc Faria. "Internal ballistics simulation of a solid propellant rocket motor". Master's thesis, Universidade da Beira Interior, 2013. http://hdl.handle.net/10400.6/1980.
Pełny tekst źródłaNa concepção e desenvolvimento de motores foguete sólidos, o uso de ferramentas numéricas capazes de simular, prever e reconstruir o comportamento de um dado do motor em todas as condições operativas ´e particularmente importante, a fim de diminuir todos os custos e planeamento. Este estudo ´e dedicado a apresentar uma abordagem para a simulação numérica de balística interna de um determinado motor foguete de propelente sólido, Naval Air Warfare Center no. 13, durante a fase quasi steady state por meio de uma ferramenta numérica comercial, ANSYS FLUENT. O modelo de balística interna construído neste estudo é um modelo axissimétrico 2-D. Tem por base vários pressupostos. Entre eles, está o pressuposto de que não há contribuição da queima erosiva e da queima dinâmica no modelo da taxa de queima. Os resultados da simulação balística interna são comparados com os resultados encontrados na pesquisa bibliográfica, validando assim, o modelo que foi construído. A validação dos resultados também nos permite concluir que os pressupostos assumidos na construção do modelo são razoáveis. Sugestões e recomendações para um estudo mais aprofundado são delineadas.
Achim, Pascal. "Simulation de collisions, coalescence et rupture de gouttes par une approche lagrangienne : application aux moteurs à propergol solide". Rouen, 1999. http://www.theses.fr/1999ROUES039.
Pełny tekst źródłaQian, Xin. "Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor". Thesis, This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-03122009-040826/.
Pełny tekst źródłaDupays, Joël. "Contribution à l'étude du rôle de la phase condensée dans la stabilité d'un propulseur à propergol solide pour lanceur spatial". Toulouse, INPT, 1996. http://www.theses.fr/1996INPT063H.
Pełny tekst źródłaIssa, May. "Etude théorique et expérimentale de l'oxydation catalytique du noir de carbone : Influence du contact entre solides". Mulhouse, 2008. https://www.learning-center.uha.fr/opac/resource/etude-theorique-et-experimentale-de-loxydation-catalytique-du-noir-de-carbone-influence-du-contact-e/BUS4168757.
Pełny tekst źródłaStringent standards have been imposed to reduce the emisions of soot particulates known by their danger for human health and environnment. DPF (Diesel particulate filter), enables to collect soot particulates in the exhaust gas, should be regernerated periodically by soot combustion. This regeneration could be active or passive. Passive regeneration uses catalysts in the filter to promote soot oxidation at lower temperatures (400-500°C). Therefore, this investigation was dedicated to the effect of contact between carbon black (model of diesel soot) and catalyst (cerium oxide) and its influence on carbon black oxidation in the presence of oxygen. A correlation between the morphology of mixtures of carbon black and cerium oxide and the reactivity of carbon black was established. Mathematical models (1D and 3D) were developped. These models predict soot oxidation taking into account different parameters based on experimental results. In partiuclar, the three dimensionnai model represents the studied mixtures considering that catalyst is composed of agregates with different sizes. These agregates, distributed randomly in the system, are composed of isometric elementary volumes of 200 nm of length. This representation enables to estimate the effect of the contact between carbon black and catalyst on carbon black oxidation. The model determines the catalytic neighberhood of each elementary volume of carbon black. A good agreement was obtained between experimental results and calculated ones by the model. Indeed, a three dimensionnai model based on geometrical representation of DPF was developped to get a better insight on the phenomena occuring during the regeneration process
Touré, Abdou. "Etude théorique et expérimentale d'un moteur Ericsson à cycle de Joule pour conversion thermodynamique de l’énergie solaire ou pour micro-cogénération". Pau, 2010. http://www.theses.fr/2010PAUU3012.
Pełny tekst źródłaAn Ericsson engine is an external heat supply engine working according to a Joule thermodynamic cycle. Such engines have separated compression and expansion cylinders, a recuperator, and a monophasic gaseous working fluid. First of all, in this thesis we have developed an original theoretical model of a volumetric hot air Joule cycle engine. The theoretical results are presented and analyzed. Then, we have tested a prototype of the 'hot' part of an open cycle Ericsson engine developed by our laboratory. Experimental results for the ‘engine mode’ and the ‘driven engine mode’ are presented and analyzed. The performances of the prototype are in agreement with previous modeling results and assumptions. Therefore it has been decided to build and add the compression part to the prototype so that to allow the test of a complete Ericsson engine
Griffond, Jérôme. "Instabilité pariétale et accrochage aéroacoustique dans les conduits à parois débitantes simulant les moteurs à propergol solide d'Ariane 5". Toulouse, ENSAE, 2001. http://www.theses.fr/2001ESAE0006.
Pełny tekst źródłaMahé, Laurent. "Usure du polytetrafluoroethylène (PTFE) charge : approche par les débits de troisième corps solide : Application aux segments de piston de compresseur". Lyon, INSA, 2000. http://www.theses.fr/2000ISAL0040.
Pełny tekst źródłaNowadays, the existing wear laws can not predict the contact lifetime when the third body is not a fluid. That the case of contacts between piston rings and cylinder in some air compressors. The main cause comes from the non consideration of the set of parameters which control the flows, therefore wear. The objective of this work is to build the scenario of contact life in term of third body flows and to estimate the contribution of each tribological triplet element on the flows activation. In our case, the tribological triplet is the following: the mechanism (compressor), the first body in contact (rings/cylinder) and the third body. Our approach is composed of the following steps: the state of the art of knowledge on the piston rings from the compressorists point of view, the using of the " conceptual tribological tools " to the studied contacts, the individual study of the triplet elements, the reconstitution of the tribological circuit and the scenario of the contact life in the compressor and then the taking into account the interactions of the triplet elements. This reconstitution is based on dynamic instrumentation of compressor, tests on simulators with in-vivo visualization flows tests, and thermal and mechanical modelings. It leads to the establishment of a phenomenological equation of the third body flows in the contacts rings/cylinder, and the identification of mechanical, materials and physico-chemical parameters which control the t1ows
Goncalves, de Miranda Fabienne. "Étude numérique de l'écoulement instationnaire diphasique dans les propulseurs à propergol solide d'Ariane 5". Toulouse, ENSAE, 2000. http://www.theses.fr/2000ESAE0021.
Pełny tekst źródłaSimoes, Marine. "Modélisation eulérienne de la phase dispersée dans les moteurs à propergol solide, avec prise en compte de la pression particulaire". Phd thesis, Toulouse, INPT, 2006. http://oatao.univ-toulouse.fr/7473/1/simoes.pdf.
Pełny tekst źródłaSimoes, Marine Simonin Olivier. "Modélisation eulérienne de la phase dispersée dans les moteurs à propergol solide, avec prise en compte de la pression particulaire". Toulouse : INP Toulouse, 2006. http://ethesis.inp-toulouse.fr/archive/00000320.
Pełny tekst źródłaHainline, Roger. "DESIGN OPTIMIZATION OF SOLID ROCKET MOTOR GRAINS FOR INTERNAL BALLISTIC PERFORMANCE". Master's thesis, University of Central Florida, 2006. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2838.
Pełny tekst źródłaM.S.
Department of Mechanical, Materials and Aerospace Engineering;
Engineering and Computer Science
Mechanical Engineering
Wu, Jenq-dah. "Time-dependent, mixed-mode fracture of solid rocket motor bondline systems /". Digital version accessible at:, 1999. http://wwwlib.umi.com/cr/utexas/main.
Pełny tekst źródłaMoro, Tanguy. "Contribution à l'analyse mécano-fiabiliste des problèmes de contact entre solides déformables : application aux moteurs piézo-électriques". Besançon, 2000. http://www.theses.fr/2000BESA2030.
Pełny tekst źródłaSibra, Alaric. "Modélisation et étude de l’évaporation et de la combustion de gouttes dans les moteurs à propergol solide par une approche eulérienne Multi-Fluide". Thesis, Université Paris-Saclay (ComUE), 2015. http://www.theses.fr/2015SACLC019/document.
Pełny tekst źródłaThe addition of a significant mass fraction of aluminum particle in the propellant of Solid Rocket Motors improves performance through an increase of the temperature in the combustion chamber. The distributed combustion of aluminum droplets in a portion of the chamber yields a massive amount of disperse aluminum oxide residues with a large size spectrum, called a polydisperse spray, in the entire volume. The spray can have a significant impact on the motor behavior and in particular on the onset/damping of instability. When dealing with aeroacoustical and thermoacoustical instabilities, the faithful prediction of the interactions between the gaseous phase and the spray is a determining step for understanding the physical mechanisms and for future solid rocket motor optimization. In such a harsh environment, experimental measurements have a hard time providing detailed explanation of the physical mechanisms and one has to resort to numerical simulation. For such a purpose, the distributed combustion zone and thermal profile therein, the heat generated by the combustion of the dispersed droplets and the large size distribution of the aluminum oxide residues and its coupling with he gaseous phase hydrodynamic and acoustic fields have to be accurately reproduced through a proper level of modeling and a high fidelity simulation including a precise resolution of size polydispersity, which is a key parameter.In this contribution, we choose a kinetic approach for the description of polydisperse sprays. The Williams-Boltzmann Equation is used to model the disperse phase and we derive a fully Eulerian approach through moment methods. The Multi-Fluid (MF) methods naturally treat droplet size evolution through phenomena such as evaporation and coalescence. These methods rely on the conservation of size moments on fixed intervals called sections and yield systems of conservation laws for a set of "fluids" of droplet of various sizes, which is strongly coupled with the gas phase via source terms. We derive a new optimal and flexible Two Size Moment MF method based on a family of polynomial reconstruction functions to describe the size distribution in the sections, which is second order accurate and particularly efficient at describing accurately the evolution of the size distribution with a moderate number of sections. An original work is also conducted in order to extend this approach to two-component droplets. For size moment MF methods, realizability of the moments is a crucial issue. Thus, we have developed innovative schemes for integrating source terms in moment conservation equations describing transport in phase space. This method enables the use of more representative aluminum droplet combustion models, and leads to more advanced studies of the distributed combustion zone. Moreover, for unsteady two-phase flow simulations, we have developed a robust and accurate coupling strategy between phases that are modeled by a fully Eulerian approach based on operator splitting in order to treat such spatial and temporal very multi-scale problems with reasonable computational time. All the proposed developments have been carried out following two criteria : 1- an attractive cost/accuracy ratio for industrial simulations in the context of high fidelity simulations 2- a preservation of industrial code legacy. Verification of the models and methods have been conducted first using an in-house reseach code and then in the context of a two-phase acoustic study thus emphasizing the relevance of the splitting technique to capture accurately spray-acoustic interactions
Dupif, Valentin. "Modélisation et simulation de l’écoulement diphasique dans les moteurs-fusées à propergol solide par des approches eulériennes polydispersées en taille et en vitesse". Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLC050/document.
Pełny tekst źródłaThe massive amount of aluminum oxide particles carried in the internal flow of solid rocket motors significantly influences their behavior.The objective of this PhD thesis is to improve the two-phase flow Eulerian models available in the semi-industrial CFD code for energeticsCEDRE at ONERA by introducing the possibility of a local velocity dispersion in addition to the size dispersion already taken into accountin the code, while keeping the well-posed characteristics of the system of equations. Such a new feature enables the model to treat anisotropicparticle trajectory crossings, which is a key issue of Eulerian models for droplets of moderately large inertia.In addition to the design and detailed analysis of a class of models based on moment methods, the conducted work focuses on the resolution ofthe system of equations for industrial configurations. To do so, a new class of accurate and realizable numerical schemes for the transport ofthe particles in both the physical and the phase space is proposed. It ensures the robustness of the simulation despite the presence of varioussingularities (including shocks, -shocks, zero pressure area and vacuum...), while keeping a second order accuracy for regular solutions. Thesedevelopments are conducted in two and three dimensions, including the two dimensional axisymmetric framework, in the context of generalunstructured meshes.The ability of the numerical schemes to maintain a high level of accuracy in any condition is a key aspect in an industrial simulation of theinternal flow of solid rocket motors. In order to assess this, the in-house code SIERRA, originally designed at ONERA in the 90’s for solidrocket simulation purpose, has been rewritten, restructured and augmented in order to compare two generations of models and numericalschemes, to provide a basis for the integration of the features developed in CEDRE. The obtained results assess the efficiency of the chosennumerical strategy and confirm the need to introduce a new specific boundary condition in the context of axisymmetric simulations. Inparticular, it is shown that the model and numerical scheme can have an impact in the context of the simulation of the internal flow ofsolid rocket motors and their instabilities. Through our approach, the shed light on the links between fundamental aspects of modeling andnumerical schemes and their consequences on the applications
Tran, Phu Ho. "Analyse numérique des écoulements internes au sein des moteurs à propergol solide. Vers une prise en compte des mécanismes instationnaires couplés". Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2013. http://www.theses.fr/2013ESMA0030/document.
Pełny tekst źródłaCharacterization and simulation of internaI flow within the solid rocket motors, considering the physicalmechanisms strongly coupled, are the main focus of this thesis objective. In this context, the conjunctionbetween fluid/regression surface/fluid coupling structure imposed deploy c1ean during the development ofnumerical modeling strategy. Indeed, the model incorporates treatment coupled with an immersed boundarytracking moving boundary in order to realize the tremendous internai geometric variation experienced during ashot. Fluid side, an automatic mesh is required and the management of the latter is based on a recursivehierarchical structure development with type 2" tree. Particular attention was paid to the solver itself with anexplicit approach to time and a numerical scheme based on the approach of Roe with flow limiter in the secondorder. Tests cases were conducted to validate the sol ver and different boundary conditions introduced, inc1udingspecific conditions developed for the purpose of simulation. The first results emphasize the interest of theproposed and unless our error model, for the first time, the analysis of the sources responsible vortex instabilitiesin these engines has been studied by incorporating the effects of continuous change in geometry. Finally, thefeasibility of a strong interaction between fluid and solid solver was conducted on a simplified model of a multiengine.AlI the developments allows access to complex mechanisms coupled and strong interactions in solidrocket motors and off ers new insights into the characterization of strongly coupled mechanisms
Tran, Ho Phu. "Analyse numérique des écoulements internes au sein des moteurs à propergol solide. Vers une prise en compte des mécanismes instationnaires couplés". Phd thesis, ISAE-ENSMA Ecole Nationale Supérieure de Mécanique et d'Aérotechique - Poitiers, 2013. http://tel.archives-ouvertes.fr/tel-00951242.
Pełny tekst źródłaMathieu, Antoine. "Contribution à la conception et à l'optimisation thermodynamique d'une microcentrale solaire thermo-électrique". Thesis, Université de Lorraine, 2012. http://www.theses.fr/2012LORR0027/document.
Pełny tekst źródłaAs a new millenium begins, 1.4 Billion people worldwide earn less than 2 dollars daily and have no access to the power grid. The need of electric power of these people represent small energy amounts but is very important regarding to the usage : acces to healthcare and education, communication, local economic development. In reponse to the situation, since 2009, Schneider Electric Industries takes up the challenge to design and realize micro solar power plants, competitive with other solutions, to supply these people with reliable and environment-friendly electricity. Dealing with this project, this work has been realized under contract, so it follows the development sequence of the industrial project. The first part is a State of the Art of the actual solar thermodynamical technologies. This task is extended to a qualitative evaluation of various technologies, as a contribution to select adapted technologies: concentrating solar thermal receivers, sensible heat thermal storage and Stirling engine. The secon step is a preliminary thermodynamics analysis of the whole system, that allowed to evaluate key features: the size of the solar receivers area, the thermal storage volume, and overall energy performance. This task is streched by a sensitivity analysis of the sizing and performances, according to various energy losses parameters, that shows the technical hard spots of the design. Finally, an exergy-based dynamical analysis of stationary operating solar receivers and Stirling engines leads to a propostion of basis methods and criteria for the optimal control of power, in order to maximize the energy performances of the system and to enhance its competitiveness
Kyriakides, Steven Alan. "Characterization of Shear Strengths and Microstructures for Solid Rocket Motor Insulation Materials". Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/35974.
Pełny tekst źródłaMaster of Science