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Dissertations / Theses on the topic 'Rocket combustion'

Author: Grafiati

Published: 4 June 2021

Last updated: 4 February 2022

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1

Kutrieb, Joshua M. "Rocket plume tomography of combustion species." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA399398.

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Thesis (M.S. in Astronautical Engineering, Aeronautical and Astronautical Engineer) Naval Postgraduate School, Dec. 2001.<br>Thesis advisors: Christopher Brophy, Jose Sinibaldi, Ashok Gopinath. "December 2001." Includes bibliographical references (p. 73). Also available in print.

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2

Matta, Lawrence Mark. "Investigation of the flow turning loss in unstable solid propellant rocket motors." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/15938.

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3

Noonan, Erin E. (Erin Elizabeth) 1978. "Structural analysis of the MIT Micro Rocket Combustion Chamber." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8127.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2002.<br>"June 2002."<br>Includes bibliographical references (p. 209-211).<br>The micro rocket is one of several power microelectromechanical systems (MEMS) under development at MIT. The micro rocket is experiencing structural failures at operating parameters far below the designed performance level. The deterministic strength of brittle materials, such as silicon, is critically dependent on the local strength and flaw population. Experiments and correlating modeling were used to pursue the root cause

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4

Wall, Neil J. "Characterisation of multiple concentric vortices in hybrid rocket combustion chambers." Thesis, University of Sheffield, 2013. http://etheses.whiterose.ac.uk/4781/.

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Recent developments in hybrid rocket technology involve producing a coaxial bidirectional vortex flow field through use of tangential oxidiser injection at the base of the combustion chamber. This is found to significantly increase engine performance by providing enhanced thermal transfer at the fuel surface, resulting in increased fuel regression rates in addition to more efficient combustion. The double helical path of the flow results in reduced reactant loss at the chamber outlet whilst confining combustion to a high temperature core region defined by the inner vortex. This also results in

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5

Ghosh, Amardip. "The role of density gradient in liquid rocket engine combustion instability." College Park, Md.: University of Maryland, 2008. http://hdl.handle.net/1903/8903.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2008.<br>Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

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6

Ruiz, Anthony. "Unsteady Numerical Simulations of Transcritical Turbulent Combustion in Liquid Rocket Engines." Thesis, Toulouse, INPT, 2012. http://www.theses.fr/2012INPT0009/document.

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Ces cinquantes dernières années, la majorité des paramètres de conception des moteurs cryotechniques ont été ajustés en l'absence d'une compréhension détaillée des phénomènes de combustion, en raison des limites des diagnostiques expérimentaux et des capacités de calcul. L'objectif de cette thèse est de réaliser des simulations numériques instationnaires d'écoulements réactifs transcritiques de haute fidélité, pour permettre une meilleure compréhension de la dynamique de flamme dans les moteurs cryotechniques et finalement guider leur amélioration. Dans un premier temps, la thermodynamique gaz

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7

Kirchberger, Christoph [Verfasser]. "Investigation on Heat Transfer in Small Hydrocarbon Rocket Combustion Chambers / Christoph Kirchberger." München : Verlag Dr. Hut, 2014. http://d-nb.info/1064559999/34.

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8

kaya, mine. "Experimental Study and Numerical Simulation of Methane Oxygen Combustion inside a Low Pressure Rocket Motor." ScholarWorks@UNO, 2016. http://scholarworks.uno.edu/td/2240.

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In this thesis, combustion processes in a laboratory-scale methane based low pressure rocket motor (LPRM) is studied experimentally and numerically. Experiments are conducted to measure flame temperatures and chamber temperature and pressure. Single reaction-four species reacting flow of gaseous methane and gaseous oxygen in the combustion chamber is also simulated numerically using a commercial CFD solver based on 2-D, steady-state, viscous, turbulent and compressible flow assumptions. LPRM geometry is simplified to several configurations, i.e. Channel and Combustion Chamber with Nozzle and F

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9

Savur, Mehmet Koray. "A numerical study of combined convective and radiative heat transfer in a rocket engine combustion chamber." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Dec%5FSavur.pdf.

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10

Hewitt, Patrick. "Numerical Modeling of a Ducted Rocket Combustor With Experimental Validation." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/28928.

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The present work was conducted with the intent of developing a high-fidelity numerical model of a unique combustion flow problem combining multi-phase fuel injection with substantial momentum and temperature into a highly complex turbulent flow. This important problem is very different from typical and more widely known liquid fuel combustion problems and is found in practice in pulverized coal combustors and ducted rocket ramjets. As the ducted rocket engine cycle is only now finding widespread use, it has received little research attention and was selected as a representative problem for thi

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11

Harris, Paul. "Experimental evaluation of pulse-triggered nonlinear combustion instability in solid propellant rocket motors." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape3/PQDD_0015/MQ53952.pdf.

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12

Mathias, Spencer D. "Investigation of Thermoplastic Polymers and Their Blends for Use in Hybrid Rocket Combustion." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7416.

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This thesis set out to find a blend of thermoplastics that had better combustion properties than the current ABS (acrylonitrile butadiene styrene) plastic or “Lego TM plastic” used by Utah State University. The current work is in an effort to eliminate toxic propellants from small space applications. High and low density polyethylene plastics were used because they are common plastic waste items. In this way rocket fuel can be made from these items to reduce the waste found in landfills. Three plastics were considered for replacement and as mixture components with the ABS plastic, namely low a

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13

Goh, Sing Huat. "Numerical study of the effect of the fuel film on heat transfer in a rocket engine combustion chamber." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FGoh.pdf.

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Thesis (M.S. in Engineering Science (Mechanical Engineering))--Naval Postgraduate School, December 2003.<br>Thesis advisor(s): Ashok Gopinath, Christopher Brophy. Includes bibliographical references (p. 71-72). Also available online.

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14

Masquelet, Matthieu M. "Simulations of a Sub-scale Liquid Rocket Engine: Transient Heat Transfer in a Real Gas Environment." Thesis, Available online, Georgia Institute of Technology, 2006, 2006. http://etd.gatech.edu/theses/available/etd-11102006-082702/.

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15

Masquelet, Matthieu Marc. "Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/47522.

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The understanding and prediction of transient phenomena inside Liquid Rocket Engines (LREs) have been very difficult because of the many challenges posed by the conditions inside the combustion chamber. This is especially true for injectors involving liquid oxygen LOX and gaseous hydrogen GH₂. A wide range of length scales needs to be captured from high-pressure flame thicknesses of a few microns to the length of the chamber of the order of a meter. A wide range of time scales needs to be captured, again from the very small timescales involved in hydrogen chemistry to low-frequency longitudina

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16

Potier, Luc. "Large Eddy Simulation of the combustion and heat transfer in sub-critical rocket engines." Thesis, Toulouse, INPT, 2018. http://www.theses.fr/2018INPT0043/document.

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La combustion cryogénique dans les moteurs de fusée dits à propulsion liquide utilise généralement un couple d'ergols, le plus couramment composé d'hydrogène/oxygène (H2/O2). Privilégiée pour le fort pouvoir calorifique du dihydrogène, cette combustion à haute pression, induit des températures de fonctionnement très élevées et nécessite l'intégration d'un système de refroidissement. La prédiction des flux thermiques aux parois est donc un élément essentiel de la conception d'une chambre de combustion de moteur fusée. Ces flux sont le résultat d'écoulements fortement turbulents, compressibles,

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17

Perovšek, Jaka. "Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71277.

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A visualisation procedure was developed which predicts excited hydroxyl (OH*) radiation from the Computational Fluid Dynamics (CFD) solutions of cryogenic hydrogen-oxygen rocket flames. The model of backward ray tracing through inhomogeneous media with a continuously changing refractive index was implemented. It obtains the optical paths of light rays that originate in the rocket chamber, pass through the window and enter a simulated camera. Through the use of spectral modelling, the emission and absorption spectra eλ and κλ are simulated on the ray path from information about temperature, pre

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18

Carrier, Denis Joseph Gaston. "Automatic measurement of particles from holograms taken in the combustion chamber of a rocket motor." Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/22924.

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Approved for public release; distribution is unlimited<br>This thesis describes the procedure used for the automatic measurement of particles from hologram taken in the combustion chamber of a rocket motor while firing. It describes the investigation done on two averaging techniques used to reduce speckle noise, capturing the image focused on a spinning mylar disk and software averaging of several image frames. The spinning disk technique proved superior for this application. The Kolmogorov-Smirnov two-sample test is applied to different particle samples in order to find an estimate of

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19

D'Elia, Christopher. "Development of Local Transient Heat Flux Measurements in an Axisymmetric Hybrid Rocket Nozzle." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1349.

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A method of performing local transient heat flux measurements in an uncooled axisymmetric hybrid rocket nozzle is presented. Surface temperatures are collected at various axial locations during short duration tests and post processed using finite difference techniques to determine local transient heat fluxes and film coefficients. Comparisons are made between the collected data and the complete Bartz model. Although strong agreement is observed in certain sections of the nozzle, ideal steady state conditions are not observed to entirely validate the Bartz model for hybrid rocket nozzles. An ex

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20

Tini, Vivian [Verfasser]. "Lifetime prediction of a typical rocket combustion chamber by means of viscoplastic damage modeling / Vivian Tini." Aachen : Shaker, 2014. http://d-nb.info/1063265657/34.

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21

Silvestri, Simona [Verfasser]. "Investigation on Heat Transfer and Injector Design Criteria for Methane/Oxygen Rocket Combustion Chambers / Simona Silvestri." München : Verlag Dr. Hut, 2019. http://d-nb.info/1200754840/34.

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22

Quinlan, John Mathew. "Investigation of driving mechanisms of combustion instabilities in liquid rocket engines via the dynamic mode decomposition." Diss., Georgia Institute of Technology, 2015. http://hdl.handle.net/1853/54343.

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Combustion instability due to feedback coupling between unsteady heat release and natural acoustic modes can cause catastrophic failure in liquid rocket engines and to predict and prevent these instabilities the mechanisms that drive them must be further elucidated. With this goal in mind, the objective of this thesis was to develop techniques that improve the understanding of the specific underlying physical processes involved in these driving mechanisms. In particular, this work sought to develop a small-scale, optically accessible liquid rocket engine simulator and to apply modern, high-s

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23

Langford, Lester A. "Optical Spectroscopy to Determine Intermediate Combustion Product Radicals in a Hydrocarbon Fueled Rocket Engine Exhaust Plume." ScholarWorks@UNO, 2006. http://scholarworks.uno.edu/td/493.

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With the prospect of hydrocarbon-fueled rocket engines, such as Rocket Propellant 1 (RP-1) or methane (CH4) fueled engines being considered for use in future space flight systems, the contributions of intermediate or final combustion products resulting from these hydrocarbon fuels are of great interest. The effect of several diatomic molecular radicals, such as Carbon Monoxide, Molecular Carbon, Methylene Radical, Cyanide or Cyano Radical, Hydroxyl, and Nitric Oxide, needs to be identified and the effects of their band systems on the spectral region from 300 nm to 850 nm determined. This

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24

Cengiz, Kenan. "Development Of An Iterative Method For Liquid-propellant Combustion Chamber Instability Analysis." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12612753/index.pdf.

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Controlling unsteady combustion induced gas flow fluctuations and the resultant motor vibrations is a very significant step in rocket motor design. It occurs when the unsteady heat release due to combustion happens to feed the acoustic oscillations of the closed duct forming a feed-back system. The resultant vibrations concerned may even lead to total failure of the rocket system unless analysed and tested thoroughly. This thesis aims developing a linear numerical analysis method for the growth rate of instabilities and possible mode shape of a liquid-propelled chamber geometry. In particular,

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25

McDonald, Brian Anthony. "The Development of an Erosive Burning Model for Solid Rocket Motors Using Direct Numerical Simulation." Diss., Georgia Institute of Technology, 2004. http://hdl.handle.net/1853/4973.

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A method for developing an erosive burning model for use in solid propellant design-and-analysis interior ballistics codes is described and evaluated. Using Direct Numerical Simulation, the primary mechanisms controlling erosive burning (turbulent heat transfer, and finite rate reactions) have been studied independently through the development of models using finite rate chemistry, and infinite rate chemistry. Both approaches are calibrated to strand burn rate data by modeling the propellant burning in an environment with no cross-flow, and adjusting thermophysical properties until the predi

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26

Fiala, Thomas [Verfasser]. "Radiation from High Pressure Hydrogen-Oxygen Flames and its Use in Assessing Rocket Combustion Instability / Thomas Fiala." München : Verlag Dr. Hut, 2015. http://d-nb.info/1076437737/34.

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27

Yi, Jianwen. "Large eddy probability density function (LEPDF) simulations for turbulent reactive channel flows and hybrid rocket combustion investigations." Diss., The University of Arizona, 1995. http://hdl.handle.net/10150/187273.

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A new numerical simulation methodology, Large Eddy Probability Density Function (LEPDF), and corresponding numerical code have been developed for turbulent reactive flow systems. In LEPDF, large scale of turbulent motion is resolved accurately. Small scale of motion is taken care of by a modified Smagorinsky subgrid scale model. Chemical reaction terms are resolved exactly without modeling. A numerical scheme to generate inflow boundary conditions has been proposed for spatial simulations of turbulent flows. Monte-Carlo scheme is used to resolve filtered PDF (Probability Density Function) evol

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28

Mari, Raphaël. "Influence of heat transfer on high pressure flame structure and stabilization in liquid rocket engines." Phd thesis, Toulouse, INPT, 2015. http://oatao.univ-toulouse.fr/15616/1/Mari_1.pdf.

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This research work deals with the problem of the flame stabilization in the context of high pressure liquid rocket engines. Flame stabilization in a rocket engine is a critical feature. An instability can lead to important damages of the engine or the destruction of the launcher and the satellite. The engines (Vulcain 2 and Vinci) of the Ariane 5, and the future Ariane 6, use the hydrogen/oxygen propellants. One characteristic of this couple is its high specific impulse. The launcher performance is linked to the ratio of the payload to the total mass of propellants. For volume reasons the prop

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29

Méry, Yoann. "Mécanismes d'instabilités de combustion haute-fréquence et application aux moteurs-fusées." Thesis, Châtenay-Malabry, Ecole centrale de Paris, 2010. http://www.theses.fr/2010ECAP0012.

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Cette thèse présente une étude des instabilités haute-fréquence dans les moteurs-fusées. Ce phénomène, qui a posé de nombreux problèmes dans les programmes de développement de moteur, est abordé de trois façons complémentaires : expérimentalement, théoriquement et numériquement. Premièrement, des expériences sont menées afin d’identifier les principaux processus et d’apporter les mécanismes ayant lieu lorsque le moteur devient instable. Pour parvenir à ce stade, un nouveau modulateur (VHAM), capable de créer des ondes acoustiques représentatives de ce qui se produit dans un moteur réel, est co

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30

Keshav, Saurabh. "Using Plasmas for High-Speed Flow Control and Combustion Control." The Ohio State University, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=osu1222026159.

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31

Capatina, Allen A. C. "AXISYMMETRIC BI-PROPELLANT AIR AUGMENTED ROCKET TESTING WITH ANNULAR CAVITY MIXING ENHANCEMENT." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1493.

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Performance characterization was undertaken for an air augmented rocket mixing duct with annular cavity configurations intended to produce thrust augmentation. Three mixing duct geometries and a fully annular cavity at the exit of the nozzle were tested to enable thrust comparisons. The rocket engine used liquid ethanol and gaseous oxygen, and was instrumented with sensors to output total thrust, mixing duct thrust, combustion chamber pressure, and propellant differential pressures across Venturi flow measurement tubes. The rocket engine was tested to thrust maximum, with three different mixin

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32

Foss, David T. "Development and modeling of a dual-frequency microwave burn rate measurement system for solid rocket propellant." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/45962.

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<p>A dual-frequency microwave bum rate measurement system for solid rocket motors has been developed and is described. The system operates in the X-band (8.2-12.4 Ghz) and uses two independent frequencies operating simultaneously to measure the instantaneous bum rate in a solid rocket motor. Modeling of the two frequency system was performed to determine its effectiveness in limiting errors caused by secondary reflections and errors in the estimates of certain material properties, particularly the microwave wavelength in the propellant. Computer simulations based upon the modeling were perfo

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33

Nelson, Lauren May. "Rayleigh Flow of Two-Phase Nitrous Oxide as a Hybrid Rocket Nozzle Coolant." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/284.

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The Mechanical Engineering Department at California Polytechnic State University in San Luis Obispo currently maintains a lab-scale hybrid rocket motor for which nitrous oxide is utilized as the oxidizer in the combustion system. Because of its availability, the same two-phase (gas and liquid) nitrous oxide that is used in the combustion system is also routed around the throat of the hybrid rocket’s converging-diverging nozzle as a coolant. While this coolant system has proven effective empirically in previous tests, the physics behind the flow of the two-phase mixture is largely unexplained.

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34

Douasbin, Quentin. "Acoustic waves in combustion devices : interactions with flames and boundary conditions." Phd thesis, Toulouse, INPT, 2018. http://oatao.univ-toulouse.fr/20204/7/douasbin_quentin.pdf.

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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 rock

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35

Laurent, Charlelie. "Low-order modeling and high-fidelity simulations for the prediction of combustion instabilities in liquid rocket engines and gas turbines." Thesis, Toulouse, INPT, 2020. http://www.theses.fr/2020INPT0038.

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Au cours des dernières décennies, les instabilités de combustion ont constitué un important défi pour de nombreux projets industriels, en particulier dans la conception de moteurs-fusées à ergols liquide et de turbines à gaz. L'atténuation de leurs effets nécessite une solide compréhension scientifique de l'interaction complexe entre la dynamique de flamme et les ondes acoustiques qu'elles impliquent. Au cours de cette thèse, plusieurs directions ont été explorées pour fournir une meilleure compréhension de la dynamique des flammes dans les moteurs-fusées cryogéniques, ainsi que des méthodes n

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36

Arvanetes, Jason. "DESIGN AND IMPLEMENTATION OF AN EMISSION SPECTROSCOPY DIAGNOSTIC IN A HIGH-PRESSURE STRAND BURNER FOR THE STUDY OF SOLID PROPELL." Master's thesis, University of Central Florida, 2006. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2820.

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The application of emission spectroscopy to monitor combustion products of solid rocket propellant combustion can potentially yield valuable data about reactions occurring within the volatile environment of a strand burner. This information can be applied in the solid rocket propellant industry. The current study details the implementation of a compact spectrometer and fiber optic cable to investigate the visible emission generated from three variations of solid propellants. The grating was blazed for a wavelength range from 200 to 800 nm, and the spectrometer system provides time resolutions

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Singh, Sajan B. "A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core." ScholarWorks@UNO, 2013. http://scholarworks.uno.edu/td/1766.

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Two mathematical models (a one and a three-dimensional) were adopted to study, numerically, the thermal hydrodynamic behavior of flow inside a single cooling channel of a Nuclear Thermal Rocket (NTR) engine. The first model assumes the flow in the cooling channel to be one-dimensional, unsteady, compressible, turbulent, and subsonic. The working fluid (GH2) is assumed to be compressible. The governing equations of the 1-D model are discretized using a second order accurate finite difference scheme. Also, a commercial CFD code is used to study the same problem. Numerical experiments, using both

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Girardello, Carlo. "Optical Analysis of Plasma : Flame Emission in Cryogenic Rocket Engines." Thesis, Luleå tekniska universitet, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-76097.

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This thesis contains the results of optical flame emission measurements of the Vulcain 2.1engine and the plasma emission spectroscopy of the Lumen Project engine. The plume spectroscopyis analyzed, ordered and studied in detail to offer the best possible molecular composition.The main focus relied on the hydroxide radical, blue radiation and other moleculesanalysis of the intensities encountered during the tests. The plasma emission spectroscopy isfocused on the determination of the plasma temperature value in LIBS measurements. Thehydrogen plasma temperature determination of the local thermod

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Heiner, Mark C. "Development and Testing of a Hydrogen Peroxide Injected Thrust Augmenting Nozzle for a Hybrid Rocket." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7630.

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During a rocket launch, the point at which the most thrust is needed is at lift-off where the rocket is the heaviest since it is full of propellant. Unfortunately, this is also the point at which rocket engines perform the most poorly due to the relatively high atmospheric pressure at sea level. The Thrust Augmenting Nozzle (TAN) investigated in this paper provides a solution to this dilemma. By injecting extra propellant into the nozzle but downstream of the throat, the internal nozzle pressure is raised and the thrust is increased, and the nozzle efficiency, or specific impulse is potentiall

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Brennen, Peter Alexander. "SIMULATION OF AN OXIDIZER-COOLED HYBRID ROCKET THROAT: METHODOLOGY VALIDATION FOR DESIGN OF A COOLED AEROSPIKE NOZZLE." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/166.

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A study was undertaken to create a finite element model of a cooled throat converging/diverging rocket nozzle to be used as a tool in designing a cooled aerospike nozzle. Using ABAQUS, a simplified 2D axisymmetric model was created featuring only the copper throat and stainless steel support ring, which were brazed together for the experimental test firings. This analysis was a sequentially coupled thermal/mechanical model. The steady state thermal data matched closely to experimental data. The subsequent mechanical model predicted a life of over 300 cycles using the Manson-Halford fatigue

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Sporschill, Gustave. "Numerical approach of a hybrid rocket engine behaviour : Modelling the liquid oxidizer injection using a Lagrangian solver." Thesis, KTH, Mekanik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-217231.

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To access and operate in space, a wide range of propulsion systems has been developed, from high-thrust chemical propulsion to low-thrust electrical propulsion, and new kind of systems are considered, such as solar sails and nuclear propulsion. Recently, interest in hybrid rocket engines has been renewed due to their attractive features (safe, cheap, flexible) and they are now investigated and developed by research laboratories such as ONERA.This master’s thesis work is in line with their development at ONERA and aims at finding a methodology to study numerically the liquid oxidizer injection

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Rousseau, Charle Werner. "Establishing a cost effective method to quantify and predict the stability of solid rocket motors using pulse tests." Thesis, Stellenbosch : University of Stellenbosch, 2011. http://hdl.handle.net/10019.1/6793.

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Hamp, Niko. "The modelling of IR emission spectra and solid rocket motor parameters using neural networks and partial least squares." Thesis, Stellenbosch : University of Stellenbosch, 2003. http://hdl.handle.net/10019.1/16334.

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Thesis (MScIng)--University of Stellenbosch, 2003.<br>ENGLISH ABSTRACT: The emission spectrum measured in the middle infrared (IR) band from the plume of a rocket can be used to identify rockets and track inbound missiles. It is useful to test the stealth properties of the IR fingerprint of a rocket during its design phase without needing to spend excessive amounts of money on field trials. The modelled predictions of the IR spectra from selected rocket motor design parameters therefore bear significant benefits in reducing the development costs. In a recent doctorate study it was found

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Kirchberger, Christoph Ulrich [Verfasser], Oskar J. [Akademischer Betreuer] Haidn, and Stefan [Akademischer Betreuer] Schlechtriem. "Investigation on Heat Transfer in Small Hydrocarbon Rocket Combustion Chambers / Christoph Ulrich Kirchberger. Gutachter: Oskar J. Haidn ; Stefan Schlechtriem. Betreuer: Oskar J. Haidn." München : Universitätsbibliothek der TU München, 2014. http://d-nb.info/1064383122/34.

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Kirchberger, Christoph [Verfasser], Oskar J. [Akademischer Betreuer] Haidn, and Stefan [Akademischer Betreuer] Schlechtriem. "Investigation on Heat Transfer in Small Hydrocarbon Rocket Combustion Chambers / Christoph Ulrich Kirchberger. Gutachter: Oskar J. Haidn ; Stefan Schlechtriem. Betreuer: Oskar J. Haidn." München : Universitätsbibliothek der TU München, 2014. http://nbn-resolving.de/urn:nbn:de:bvb:91-diss-20141021-1221918-0-6.

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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.

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Les lanceurs ont un impact sur la composition de l'atmosphere, et en particulier sur l'ozone stratospherique. Parmi tous les types de propulsion, les moteurs à propergol solide ont fait l'objet d'une attention particulière car leurs émissions sont responsables d'un appauvrissement significatif d'ozone dans le panache des lanceurs lors des premières heures suivant le lancement. Ce phénomène est principalement dû à la conversion de l'acide chlorhydrique, un composé chimique présent en grandes quantités dans les émissions de ce type de moteur, en chlore actif qui réagit par la suite avec l'ozone

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Ertugrul, Suat Erdem. "The Effects Of Geometric Design Parameters On The Flow Behavior Of A Dual Pulse Solid Rocket Motor During Secondary Firing." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12615184/index.pdf.

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The ability of a propulsion system is very crucial for the capability of a missile or a rocket system. Unlike liquid propellant rocket motors, the only control mechanism of the thrust value is the propellant geometry in solid propellant rocket motors. When the operation of solid propellant rocket motor has started, it cannot be stopped anymore. For this main reason the advance of dual pulse motor technology has started. The aim of this study is to investigate the geometrical effects of design parameters on the flow behavior of a dual pulse solid propellant rocket motor by using commercial Comp

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Cordesse, Pierre. "Contribution to the study of combustion instabilities in cryotechnic rocket engines : coupling diffuse interface models with kinetic-based moment methods for primary atomization simulations." Thesis, université Paris-Saclay, 2020. http://www.theses.fr/2020UPASC016.

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Gardiens de l’espace, les lanceurs de fusée font l’objet d’une amélioration continue et concurrentielle, grâce à des campagnes de tests expérimentaux et numériques. Les simulations prédictives sont devenues indispensables pour accroître notre compréhension de la physique. Ajustables, elles se prêtent parfaitement à la conception et l’optimisation, en particuliers de la chambre de combustion, pour garantir la sureté et maximiser l’efficacité. L’atomisation primaire est l’un des phénomènes déterminants de la combustion du combustible et de l’oxydant, pilotant à la fois la distribution de gouttes

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Lowe, Steven. "Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows." Thesis, University of Cambridge, 2018. https://www.repository.cam.ac.uk/handle/1810/277375.

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This thesis is concerned with the development and application of laser induced thermal grating spectroscopy (LITGS) as a tool for thermometry in reacting and non-reacting flows. LITGS signals, which require resonant excitation of an absorbing species in the measurement region to produce a thermal grating, are acquired for systematic measurements of temperature in high pressure flames using OH and NO as target absorbing species in the burned gas. The signal obtained in LITGS measurements appears in the form of a time-based signal with a characteristic frequency proportional to the value or the

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Weber, Fabian. "Optical Analysis of the Hydrogen Cooling Film in High Pressure Combustion Chambers." Thesis, Luleå tekniska universitet, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-76872.

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For performance optimisation of modern liquid cryogenic bipropellant rocket combustion chambers, one component which plays an important role in reducing the wall side heat flux, is the behaviour of the cooling film. At the Institute of Space Propulsion of the German Aerospace Center (DLR) in Lampoldshausen, hot test runs have been performed using the experimental combustion chamber BKM, to investigate the wall side heat flux which is -- among other factors -- dependent on cooling film properties. To gain more insight into the film behaviour under real rocket-like conditions, optical diagnostic

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