<p>The increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in fullscale, due to the uncertainties involved in modeling andpredicting the flow phenomena involved.</p><p>In the present work the causes of unsteady and unsymmetricalflow separation and resulting side-loads in rocket enginenozzles are investigated. This involves the use of acombination of analytical, numerical and experimental methods,which all are presented in the thesis. A main part of the workis based on sub-scale testing of model nozzles operated withair. Hence, aspects on how to design sub-scale models that areable to capture the relevant physics of full-scale rocketengine nozzles are highlighted. Scaling laws like thosepresented in here are indispensable for extracting side-loadcorrelations from sub-scale tests and applying them tofull-scale nozzles.</p><p>Three main types of side-load mechanisms have been observedin the test campaigns, due to: (i) intermittent and randompressure fluctuations, (ii) transition in separation patternand (iii) aeroelastic coupling. All these three types aredescribed and exemplified by test results together withanalysis. A comprehensive, up-to-date review of supersonic flowseparation and side-loads in internal nozzle flows is givenwith an in-depth discussion of different approaches forpredicting the phenomena. This includes methods for predictingshock-induced separation, models for predicting side-loadlevels and aeroelastic coupling effects. Examples are presentedto illustrate the status of various methods, and theiradvantages and shortcomings are discussed.</p><p>A major part of the thesis focus on the fundamentalshock-wave turbulent boundary layer interaction (SWTBLI) and aphysical description of the phenomenon is given. Thisdescription is based on theoretical concepts, computationalresults and experimental observation, where, however, emphasisis placed on the rocket-engineering perspective. This workconnects the industrial development of rocket engine nozzles tothe fundamental research of the SWTBLI phenomenon and shows howthese research results can be utilized in real applications.The thesis is concluded with remarks on active and passive flowcontrol in rocket nozzles and directions of futureresearch.</p><p>The present work was performed at VAC's Space PropulsionDivision within the framework of European spacecooperation.</p><p><b>Keywords:</b>turbulent, boundary layer, shock wave,interaction, overexpanded,rocket nozzle, flow separation,control, side-load, experiments, models, review.</p>

This work is motivated by the Variable Specific Impulse Magnetoplasma Rocket (VASIMR) experiment. This device uses a helicon antenna to generate a plasma inside a dielectric tube, which is radially confined and directed towards the rocket nozzle by an axial magnetic field. An ion cyclotron heating antenna further heats the ions, and a magnetic nozzle accelerates the plasma along the confining magnetic field as it leaves the rocket, ultimately allowing it to detach from the magnetic field and produce thrust. The experimental research presented here provides insight into the physical mechanisms of power flow in a helicon system by providing an overall system power balance in the form of heat flux measurements, and exploring changes in the heat fluxes in different parts of the system in response to varying operational parameters. An infrared (IR) camera measures the total heat flux into the dielectric tube surface, and axially scanned bolometer and UV photodiode probes measure the radial power loss from particles and radiation. Results from IR camera measurements on three different helicon systems are presented: the VASIMR VX-50 experiment, the VASIMR VX-CR experiment, and the University of Texas at Austin (UT) helicon experiment. These results demonstrate the development of the IR camera diagnostic for use on helicon systems of varying scale and geometry, and show reasonable agreement as to the fraction of input power lost to the dielectric tube walls. On the UT experiment, the results presented account for essentially all of the input power, providing a full system power balance. The data from all three experiments indicate that radial transport of ions to the interior wall is the dominant mechanism of power loss, with UV radiation contributing a small percentage. Additional experiments on the UT helicon explore energy and particle transport to the wall due to capacitive coupling of ions near the antenna. These experiments show clear damage to the dielectric tube surface directly under the antenna, due to physical plasma etching of the surface by bombarding ions that are accelerated into the wall by local electric fields from the antenna. / text

The performance prediction of solid propellant rocket motor depends on the calculation of internal aerodynamics of the motor through its operational life. In order to obtain the control volume, in which the solutions will be carried out, a process called &ldquo / grain burnback calculation&rdquo / is required. During the operation of the motor, as the interface between the solid and gas phases moves towards the solid propellant in a direction normal to the surface, the combustion products are generated and added into the control volume. This phenomenon requires handling of moving boundaries as the solution proceeds. In this thesis, Fast Marching Method is implemented to the problem of grain burnback. This method uses the upwinding nature of the propellant interface motion and solves the Eikonal type equations on a fixed three-dimensional tetrahedron mesh. The control volume is coupled to a one-dimensional and a three-dimensional Euler aerodynamic solver in order to obtain the performance of the engine. The speed by which the interface moves depends on the static pressure on the surface of the propellant and comes from the solver. Therefore an iterative method has been proposed between the interface capturing algorithms and the flow solver. Both of the calculation results, which are obtained from one-dimensional and three-dimensional solvers are compared with actual rocket firing data and validated.

Thesis (MEng)--Stellenbosch University, 2014. / ENGLISH ABSTRACT: Recent years have seen a decline in the rate of space exploration due to the inefficiency of chemical rockets. Therefore alternative fuel efficient propulsion methods are being sought to enable cost effective deep space exploration. The high fuel efficiency of electric thrusters enable a spacecraft to travel further, faster and cheaper than any other propulsion technology available. Thus electric propulsion has become the propulsion of choice for scientists and engineers. A typically electric thruster contains some sort of electrode to ionise the propellant. Although this is feasible for short space missions, it becomes impractical for more ambitious space missions as electrodes erode over time. The alternative is to ionise the propellant using electromagnetic fields, which eliminates lifespan issues associated with electrode based thrusters. In order to examine methods of improving the lifespan and performance of electric thrusters, this thesis aimed to study the method of microwave discharge ionisation for an electric thruster. This includes the design of an RF Ion Thruster with extraction and acceleration grids to generate thrust. A 600 W 2.45 GHz magnetron (obtained from a conventional microwave oven), coupled to circular TM010 resonant cavity, was used to ionise neutral argon gas. The process of electron cyclotron resonance (ECR) was used to ensure the efficient ionisation of a high density plasma. The thrust was achieved with a three-grid system biased at high voltages to accelerate positively charged argon ions to high exhaust velocities. Results yielded the success of the designed electromagnetic based thruster, measuring approximatively 1.78 mN of thrust with a specific impulse of Isp = 3786 seconds. The ECR process produced a high plasma density with a plasma absorption rate of approximately 77% of the total input microwave power. The final results obtained were found to match the predicted results extremely well and resembled results found in literature. This demonstrates the efficiency of the RF ion thruster that was designed in this project and the future use in space exploration activities. However, future research needs to be undertaken on a controlled feedback system that will ensure optimal operating conditions for maximum performance. In addition, the method of grid-less acceleration needs to be studied to achieve maximum thrust and specific impulse. / AFRIKAANSE OPSOMMING: In onlangse jare het ’n afname in die tempo van die verkenning van die ruimte dit te danke aan die ondoeltreffendheid van chemiese vuurpyle. Derhalwe moet alternatiewe brandstof aandrywing metodes ondersoek word, om koste-effektiewe diep ruimte-eksplorasie moontlik te maak. Die hoë brandstof-doeltreffendheid van elektriese ontbranders stel ’n ruimtetuig in staat om verder, vinniger en goedkoper te reis as enige ander aandrywing tegnologie wat tans beskikbaar is. Dus het elektriese aandrywing metodes die aandrywings keuse vir wetenskaplikes en ingenieurs geword. ’n Tipies elektriese vuurpyl/aandrywer bevat ’n vorm van elektrode om die brandstof (argon gas) te ioniseer. Alhoewel hierdie elektrode proses van ionisasie effektief is vir kort ruimte missies, word dit onprakties vir meer ambisieuse ruimte missies as gevolg van verweering van elektrodes met verloop van tyd. ’n Alternatief is om die dryfmiddel/brandstof te ioniseer deur gebruik te maak van elektromagnetiese velde. Die elekromagnetiese velde sal die lewensduur van die vuurpyl vermeerder deur die verweering van elektrodes, wat geassosieer word met tipiese elektrieses vuurpyle, te elimineer. Hierdie tesis se doelwit is om die metode van mikrogolf ontslag ionisasie vir ’n elektriese vuurpyl/aandrywer te bestudeer om ten einde die lewensduur en doeltreffendheid van elektriese vuurpyl/aandrywer te ondersoek. Dit sluit in die ontwerp van ’n radio frekewensie ioon vuurpyl/aandrywer met ’n ontginning en versnelling matriks/rooster om stukrag te genereer. ’n 2,45 GHz magnetron (verkry vanaf ’n konvensionele mikrogolfoond), gekoppel aan ’n TM010 resonante holte, was gebruik om neutrale argon gas te ioniseer. Die proses van elektron siklotron resonansie (ESR) was gebruik om die doeltreffende ionisasie van ’n hoë digtheid plasma te verseker. Die aandrywing/stukrag was behaal met ’n drie-matriks-stelsel, bevoordeel deur hoë spannings om die positief-gelaaide argon ione te versnel. Resultate opgelewer, het die sukses van die ontwerp van ’n elektromagnetiese gebaseerde vuurpyl/aandrywer met ’n benaderde meting van ongeveer 1.78 mN van stukrag/aandrywing met ’n spesifieke impuls van Isp = 3786 sekondes bewys. Die ECR proses het ’n hoë plasma digtheid geproduseer met ’n plasma opname persentasie van ongeveer 77% van die totale inset mikrogolf energie. Die finale uitslae wat verkry was, het bevind dat die voorspelde resultate baie goed inpas met resultate in beskikbare literatuur. Dit dui op die doeltreffendheid van die RF ioon vuurpyl/aandrywer wat ontwerp is in hierdie projek vir die toekomstige gebruik in ruimte eksplorasie-aktiwiteite. Toekomstige navorsing moet op ’n beheerde terugvoer sisteem onderneem word, wat optimale werktoestande verseker vir maksimum prestasie. Daarbenewens moet die metode van matriks-lose versnelling bestudeer word, om maksimum versnelling/stukrag en spesifieke impuls te verseker.

Denna rapport behandlar en radarsensors förmåga att upptäcka 107 mm raketerberoende på hur sensorn positioneras i förhållande till skyddsobjektet.Fältförsök, underrättelser och stridserfarenheter har visat att dessa raketer ärvanligt förekommande samt svåra att detektera med radarsensorer. En modell för hur räckviddsökning beror på olika sensorpositioner har skapats genom att använda dokument från USA och forna Sovjetunionen beskrivande ballistik tillsammans med teorier för hur räckvidd påverkas av radarmålarea (RCS) samten beskrivning av RCS tillhandahållen av FOI. Resultat från körningar iMATLAB visar att sensorpositioner inom 300 meter från skyddsobjektet ärfördelaktiga vid en skottvidd av 3000 meter. Som tumregel för att uppnå maximal sensorprestanda bör strävan vara att placera sensorn på ett avståndfrån skyddsobjektet understigande 10% av förväntad skottvidd.

Les systèmes de combustion sont sujets aux instabilités de combustion (IC). Elles résultent d'un couplage constructif entre le taux de dégagement de chaleur instationnaire et des modes acoustiques du système. Les IC peuvent mettre en danger la performance et l'intégrité des systèmes de combustion. Même si ces phénomènes sont connus depuis plus d'un siècle, éviter quelles aient lieux dans les chambres de combustions industrielles reste difficile. Les objectifs de cette thèse sont les suivants : (1) étudier la dynamique des modes acoustiques, (2) analyser la réponse de flamme d'un moteur de fusée à propergol liquide H2/O2 (appelé "BKD"), sujet aux IC, à l'aide de la Simulation aux Grandes Echelles (SGE) et (3) dériver, utiliser et étudier des conditions limites permettant d'imposer des impédances acoustiques complexes en SGE. / Combustion devices are prone to combustion instabilities. They arise from a constructive coupling between the unsteady heat release rate of the flame and the resonant acoustic modes of the entire system. The occurence of such instabilities can pose a threat to both performance and integrity of combustion systems. Although these phenomena have been known for more than a century, avoiding their appearance in industrial engines is still challenging. The objective of this thesis is threefold: (1) study the dynamics of the resonant acoustic modes, (2) investigate the flame response of a liquid rocket engine under unstable conditions using Large Eddy Simulation(LES) and (3) derive, use and study Time Domain Impedance Boundary Conditions (TDIBCs), i.e. boundary conditions modeling complex acoustic impedances.

Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-12T23:01:48Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-22T14:06:59Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-22T18:09:14Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-22T18:12:24Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-22T19:44:22Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-23T11:57:15Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-23T12:57:56Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-23T13:16:32Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-23T13:34:45Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-23T17:24:54Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-23T17:29:02Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-24T12:05:25Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-24T12:39:45Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-24T16:47:39Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-24T17:31:21Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-27T11:40:49Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-27T12:31:51Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-27T13:03:16Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-27T18:08:08Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-28T12:13:07Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-28T14:22:46Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-28T14:31:58Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Submitted by GILBERTO CAETANO DA SILVA JÚNIOR null (gilcaju@ig.com.br) on 2017-11-28T14:37:46Z No. of bitstreams: 1 versão definitiva.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Approved for entry into archive by Adriana Aparecida Puerta null (dripuerta@rc.unesp.br) on 2017-11-28T18:25:00Z (GMT) No. of bitstreams: 1 silvajunior_gc_me_rcla.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) / Made available in DSpace on 2017-11-28T18:25:00Z (GMT). No. of bitstreams: 1 silvajunior_gc_me_rcla.pdf: 1724008 bytes, checksum: c953406384f7a6ee2d78df6e9f2ae70b (MD5) Previous issue date: 2017-10-18 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Neste trabalho, apresentamos um relato de experimento realizado junto aos alunos de ensino fundamental de uma escola pública municipal e efetuamos o ajuste de curva dos dados observados por meio do método dos mínimos quadrados. Para tanto, discutimos a concepção e aplicação desse método a partir de resultados oriundos do cálculo diferencial, da álgebra linear e alguns conceitos estatísticos. Do cálculo diferencial estudamos a minimização dos erros de aproximação por meio da investigação dos pontos de mínimo da função erro. Da álgebra linear determinamos os parâmetros da função ajustada através da discussão e solução de um sistema de equações lineares resultante do conjunto de derivadas parciais nulas que estabelecem o ponto crítico da função erro. Da estatística utilizamos alguns conceitos e formulações que tratam da intensidade da relação entre as variáveis, bem como, das incertezas na variável dependente e nos parâmetros da função ajustada. / In this work, we present a report of an experiment carried out with elementary school students of a municipal public school, and we performed the curve adjustment of the observed data through the least squares method. For this, we discuss the conception and application of this method from results derived from differential calculus, linear algebra and some statistical concepts. From the differential calculation, we study the minimization of approximation errors by investigating the minimum points of the error function. From linear algebra, we determine the parameters of the adjusted function through the discussion and solution of a system of linear equations resulting from the set of null partial derivatives that establish the critical point of the error function. From statistics, we use some concepts and formulations that deal with the intensity of the relationship between variables, as well as the uncertainties in the dependent variable and the parameters of the adjusted function.

La prédiction de l'émission infrarouge des jets de propulseurs composites aluminisés nécessite principalement trois étapes : le calcul des grandeurs aérothermochimiques du jet, la conversion de ces grandeurs en propriétés optiques (coefficient d'absorption, coefficient de diffusion, fonction de phase) puis la résolution de l'équation de transfert radiatif. Cette thèse,essentiellement consacrée à cette troisième étape, propose de nouvelles voies pour l'application des modèles de bande aux cas de milieux biphasiques et diffusants.D'une part, nous avons étendu ces modèles aux cas de milieux caractérisés par un déséquilibre thermique entre gaz et particules. D'autre part, nous avons proposé une méthode de séparation de la luminance en deux contributions, appelées respectivement non diffusée et diffusée, à partir d'une idée originale de Liu et al. La contribution non diffusée est solution de l'équation de transfert radiatif obtenue en ignorant les effets de la diffusion. Par conséquent, elle peut être résolue par une formulation en modèles de bande. Cette approche permet de réduire les erreurs de corrélations spectrales au seul terme de luminance diffusée.Nous avons montré l'intérêt de ces approches par comparaison avec une résolution de l'équation de transfert radiatif en raie par raie, sur des milieux représentatifs de situations de télédétection de jets. / Prediction of infrared emission of exhaust plumes from aluminized composite rocket, follows mainly three steps : calculating aero-thermo-chemical values in the plume, converting those valuesto optical properties (absorption coefficient, scattering coefficient and phase function) and resolving the radiative transfer equation. This thesis is mostly devoted to this third step, and proposes new ways to use band models on two-phases and scattering media.Firstly, we extended band models to cases with thermic non equilibrium between gas and particles. Secondly, we proposed a method consisting in splitting radiance in two parts, one called un-scattered and the other scattered, from an original idea of Liu et al. The un-scattered part is solution of the radiative transfer equation obtained by ignoring scattering. As a result, the unscattered radiance can be found by using band models. By this approach, errors on spectral correlations are only present on the scattered radiance.We show the interest of thoses approches by comparing them with a line by line resolutionof the radiative transfer equation, on media representative of remote sensing cases of rocket exhaust plumes.

Dans un moteur à propergol solide, l’écoulement dépend fortement des gouttes d’alumine en suspension, dont la fraction massique est élevée. La distribution en taille des gouttes, qui s’élargit avec la coalescence, joue un rôle clef. Or résoudre des écoulements diphasiques polydisperses instationnaires avec une bonne précision sur la taille est un défi à la fois sur le plan de la modélisation et du calcul scientifique: (1) de très petites gouttes, par exemple résultant de la combustion de nanoparticules d’aluminium, subissent mouvement brownien et coalescence, (2) de petites gouttes ont leur vitesse conditionnée par leur taille de sorte qu’elles coalescent lorsqu’elles ont des tailles différentes, (3) des gouttes plus grosses peuvent se croiser par effet d’inertie et (4) toutes les gouttes interagissent de manière fortement couplée avec la phase porteuse. En complément des approches lagrangiennes, des modèles eulériens ont été développés pour décrire la phase dispersée à un coût raisonnable, et ils permettent un couplage aisé avec la phase porteuse ainsi que la parallélisation massive des codes: les approches eulériennes sont bien adaptées aux calculs industriels. Le modèle Multi-Fluide permet la description détaillée de la polydispersion, des coreélations taille/vitesse et de la coalescence, en résolvant séparément des “fluides” de gouttes triées par taille, appelés sections. Un ensemble de modèles est évalué dans cette thèse et une stratégie numérique est développée pour effectuer des calculs industriels de moteurs à propergol solide. (1) La physique des nanoparticules est évalué et incluse dans un modèle de coalescence complet. Des méthodes de moments d’ordre élevé sont ensuite développées: (2) une méthode à deux moments en taille est étendue à la coalescence pour traiter la physique de la polydispersion et les développements numériques connexes permettent d’effectuer des calculs applicatifs dans le code industriel CEDRE; (3) une méthode basée sur les moments en vitesse du deuxième ordre, un schéma de transport à l’ordre deux sur maillages structurés ainsi qu’un modèle de coalescence sont développés. Des validations académiques de la stratégie pour gouttes d’inertie modérée sont effectuées sur des écoulements complexes puis avec de la coalescence; (4) une stratégie d’intégration en temps est développée et mise en œuvre dans CEDRE pour traiter efficacement le couplage fort, dans des cas instationnaires et polydisperses incluant de très petites particules. L’ensemble des développements est soigneusement validé: soit par des formules analytiques ad hoc pour la coalescence et pour le couplage fort d’une onde acoustique; soit par des comparaisons numériques croisées avec une DPS pour la coalescence et avec des simulations lagrangiennes de cas applicatifs, coalescents et fortement couplés; soit par des résultats expérimentaux disponibles sur une configuration académique de coalescence et sur un tir de moteur à échelle réduite. La stratégie complète permet des calculs applicatifs à un coût raisonnable. En particulier, un cal- cul de moteur avec des nanoparticules permet d’évaluer la faisabilité de l’approche et d’orienter les efforts de recherche sur les propergols chargés de nanoparticules. / In 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.

O sistema de controle por alocação dos pólos com filtro foi utilizado para controlar a atitude de um modelo de veículo lançador de satélites. Com este intuito, foram confeccionados um modelo e uma base de fixação que permite a movimentação nos três graus de liberdade. Utilizando a resposta à entrada degrau em conjunto com um sistema de controle PID obtido de forma empírica para estabilizar o sistema, as características da planta foram identificadas e então o sistema de controle por alocação de pólos foi projetado. Este sistema apresentou uma oscilação em torno da referência com amplitude menor do que 0,5° e tempo de pico para a entrada degrau na ordem de 2,17 segundos. Um segundo controlador PID foi projetado de forma analítica para se obter uma referência, porém apresentou resposta com características inferiores ao controlador por alocação de pólos. Os dois sistemas de controle projetados conseguem manter o modelo estável mesmo quando um dos motores é desligado. / Pole placement control system with filter was implemented to control the attitude of a satellite launch vehicle model. With this purpose, a model and a fixing base with three degrees of freedom was made. Utilizing the system response to step input with PID controller empirically designed to stabilize the system, the model characteristics were identified and the pole placement control system was designed. This system oscillated around the reference with amplitude smaller than 0.5° and peak time around 2.17 seconds. Another PID controller was designed analytically for reference, however the pole placement controller had better response characteristics than the PID controller. Both controllers can stabilize the system even when one engine is shut off.