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Dissertations / Theses on the topic 'Solid Rocket Motors'

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Published: 4 June 2021
Last updated: 25 July 2025

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1

Hovland, Douglas Lyle. "Particle sizing in solid rocket motors." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26153.

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Particle size distribution measurements were made with a Malvern 2600c forward laser light diffraction system across the exhaust nozzle entrance and exhaust plume of a small two-dimensional rocket motor. The solid propellants tested were GAP propellants containing 2.0% and 4.69% aluminum. Surface agglomeration of the aluminum, indicated by the in-motor results, was found to decrease as the motor chamber pressures were increased. At low pressures, increasing the aluminum loading with fixed total solids decreased the mean particle size at the nozzle entrance. Exhaust plume particle size was prac
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2

McCrorie, J. David. "Particle behavior in solid propellant rocket motors and plumes." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/24002.

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3

Puskulcu, Gokay. "Analysis Of 3-d Grain Burnback Of Solid Propellant Rocket Motors And Verification With Rocket Motor Tests." Master's thesis, METU, 2004. http://etd.lib.metu.edu.tr/upload/12605270/index.pdf.

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Solid propellant rocket motors are the most widely used propulsion systems for military applications that require high thrust to weight ratio for relatively short time intervals. Very wide range of magnitude and duration of the thrust can be obtained from solid propellant rocket motors by making some small changes at the design of the rocket motor. The most effective of these design criteria is the geometry of the solid propellant grain. So the most important step in designing the solid propellant rocket motor is determination of the geometry of the solid propellant grain. The performance p
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4

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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5

Romano, Federico. "Q1D unsteady ballistic model for solid rocket motors performance prediction." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021.

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The simulation tool ROBOOST, in use at the Alma Propulsion Lab of the University of Bologna – Forlì Campus, exploits a hybrid ballistic model 0D-1D. The need of a complete Q1D model for the entire combustion time, from motor start-up to burn out arised. The present work is devoted to the development and test of a Q1D unsteady ballistic model for solid rocket motors performance prediction. The newly developed code, called SOL1D, is written in Matlab environment and is capable of predicting the time and space evolution of all the main thermodynamic variables during the solid rocket motor combust
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6

Yakin, Bülent. "Combustor and nozzle effects on particulate behavior in solid rocket motors /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA277304.

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7

Yakin, Bulent. "Combustor and nozzle effects on particulate behavior in solid rocket motors." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39764.

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Approved for public release; distribution is unlimited.<br>An investigation was conducted using a subscale solid rocket motor to measure the effect of nozzle residence time on the behavior of Al203 particles to assess the applicability of subscale motor data to full-scale motors and to measure the effects of nozzle entrance particle size distribution on the slag accumulated with submerged nozzles. Although particles as large as 140 micrometers were present at the nozzle entrance, most of the particulate mass was contained in much smaller particles. This observation is in good agreement with th
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8

Mini, Stefano <1991&gt. "Analysis of the main phenomena affecting solid rocket motors internal ballistics." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amsdottorato.unibo.it/9878/1/PhD_Thesis.pdf.

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In solid rocket motors, the absence of combustion controllability and the large amount of financial resources involved in full-scale firing tests, increase the importance of numerical simulations in order to asses stringent mission thrust requirements and evaluate the influence of thrust chamber phenomena affecting the grain combustion. Among those phenomena, grain local defects (propellant casting inclusions and debondings), combustion heat accumulation involving pressure peaks (Friedman Curl effect), and case-insulating thermal protection material ablation affect thrust prediction in terms o
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9

Hasanoglu, Mehmet Sinan. "Storage Reliability Analysis Of Solid Rocket Propellants." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/2/12609897/index.pdf.

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Solid propellant rocket motor is the primary propulsion technology used for short and medium range missiles. It is also commonly used as boost motor in many di_erent applications. Its wide spread usage gives rise to diversity of environments in which it is handled and stored. Ability to predict the storage life of solid propellants plays an important role in the design and selection of correct protective environments. In this study a methodology for the prediction of solid propellant storage life using cumulative damage concepts is introduced. Finite element mesh of the solid propellant grain
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10

Vernacchia, Matthew T. "Development of low-thrust solid rocket motors for small, fast aircraft propulsion." Thesis, Massachusetts Institute of Technology, 2020. https://hdl.handle.net/1721.1/127069.

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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, May, 2020<br>Cataloged from the official PDF of thesis.<br>Includes bibliographical references (pages 281-289).<br>Small, uncrewed aerial vehicles (UAVs) are expanding the capabilities of aircraft systems. However, a gap exists in the size and capability of aircraft: no small aircraft are capable of sustained fast flight. A small, fast aircraft requires a propulsion system which is both miniature and high-power, requirements which current UAV propulsion technologies do not meet. Solid propellant
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11

Stabroth, Sebastian. "Dust particle impacts due to re-entry firings of solid rocket motors." Aachen Shaker, 2009. http://d-nb.info/995125457/04.

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12

Fadigati, Luca. "Numerical investigation of charring thermal protection pyrolysis and ablation in solid rocket motors." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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The solid rocket propulsion is a simple and reliable system, it is less complex than liquid propulsion because it does not require tanks, pumps and the propellant is already stored into the combustion chamber. The main issues are the lower propulsive performance and the lack of controllability. The solid rocket motor thrust can be controlled only moving the nozzle direction of few degrees while its magnitude can not be controlled, therefore it is very important to well know the thrust profile because there is no possibility to control its magnitude during the flight. The thrust shape can be ob
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13

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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14

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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15

Stabroth, Sebastian [Verfasser]. "Dust Particle Impacts due to Re-entry Firings of Solid Rocket Motors / Sebastian Stabroth." Aachen : Shaker, 2009. http://d-nb.info/1156518237/34.

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16

Spirnak, Jonathan R. "Development, modeling and testing of thermal protection systems in small, slow-burning solid rocket motors." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/118689.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2018.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 59-60).<br>Currently, a void exists in the development of small, unmanned aerial vehicles (UAVs) that can fly at speeds faster than 100 meters per second while maximizing endurance. Operating in such a regime requires the use of a slow-burning solid rocket motor. To achieve long burn times, an end-burning grain configuration is required in addition to a burn rate suppressant. Such a propulsion system presents uni
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17

Li, Hung-Peng. "Investigation of the Stability of Metallic/Composited-Cased Solid Propellant Rocket Motors under External Pressure." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/29323.

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Solid rocket motors consist of a thin metallic or composite shell filled with a soft rubbery propellant. Such motors are vulnerable and prone to buckling due to sudden external pressures produced by nearby detonation. The stability conditions of rocket motors subjected toaxisymmetric, external pressure loading are examined. The outer cases of motors are considered as isotropic (metallic) or anisotropic (composite), thin and high-strength shells, which are the main structures of interest in the stability analyses. The inner, low-strength elastic cores are modeled as linear and nonlinear el
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18

Andriulli, Raoul. "Development of an OpenFOAM solver for particle migration in the casting process of solid rocket motors." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amslaurea.unibo.it/24352/.

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The aim of this thesis work is the study the solid particles migration phenomenon in concentrated suspension and the development of an OpenFOAM solver able to successfully predict the behaviour of such event. It is, in fact, common knowledge how the solid particles will tend to spread into an heterogeneous arrangement when the fluid is subjected to a non-uniform shear flow. As a consequence, the viscosity field will become uneven as well, giving rise to a non-Newtonian behaviour of the flow. In order to approach the problem, the OpenFOAM transient solver pimpleFoam has been modified, changin
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19

Doisneau, 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.

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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 gout
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20

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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21

Salvioli, Emanuel. "Simulazione di una combustione non isotropa in motori a propellente solido." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2021.

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Lo scopo principale di questo scritto è indagare in dettaglio la combustione non isotropa nei motori a propellente solido, nota come fattore di Hump, che provoca un discostamento tra il profilo di pressione sperimentale e teorico. Sulla base di studi che tentano di legare tali variazioni a fenomeni fisici si sono sviluppati dei codici numerici in ambiente Matlab per generare delle mappe delle anisotropie del rateo di combustione. In seguito coi modelli realizzati sono state condotte delle simulazioni con ROBOOST, un software sviluppato dall'Università di Bologna in collaborazione con Avio S.p.
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22

Anil, Kumar K. R. "Computational Studies On Certain Problems Of Combustion Instability In Solid Propellants." Thesis, Indian Institute of Science, 2001. https://etd.iisc.ac.in/handle/2005/244.

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This thesis presents the results and analyses of computational studies on certain problems of combustion instability in solid propellants. Specifically, effects of relaxing certain assumptions made in previous models of unsteady burning of solid propellants are investigated. Knowledge of unsteady burning of solid propellants is essential in studying the phenomenon of combustion instability in solid propellant rocket motors. In Chapter 1, an introduction to different types of unsteady combustion investigated in this thesis, such as 1) intrinsic instability, 2) pressure-driven dynamic burning,
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23

Anil, Kumar K. R. "Computational Studies On Certain Problems Of Combustion Instability In Solid Propellants." Thesis, Indian Institute of Science, 2001. http://hdl.handle.net/2005/244.

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This thesis presents the results and analyses of computational studies on certain problems of combustion instability in solid propellants. Specifically, effects of relaxing certain assumptions made in previous models of unsteady burning of solid propellants are investigated. Knowledge of unsteady burning of solid propellants is essential in studying the phenomenon of combustion instability in solid propellant rocket motors. In Chapter 1, an introduction to different types of unsteady combustion investigated in this thesis, such as 1) intrinsic instability, 2) pressure-driven dynamic burning, 3
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24

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.

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Les gouttes d’oxyde d’aluminium présentes en masse dans l’écoulement interne des moteurs-fusées à propergol solide ont tendance à influerde façon importante sur l’écoulement et sur le fonctionnement du moteur quel que soit le régime. L’objectif de la thèse est d’améliorerles modèles diphasiques eulériens présents dans le code de calcul semi-industriel pour l’énergétique de l’ONERA, CEDRE, en y incluant lapossibilité d’une dispersion locale des particules en vitesse en plus de la dispersion en taille déjà présente dans le code, tout en gardant unestructure mathématique bien posée du système d’é
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25

Lacassagne, 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.

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Les oscillations de pression sont un enjeu majeur dans le design des moteurs à propergol solide car de faibles oscillations de pression (ODP) dans la chambre entraînent de fortes oscillations de poussée ce qui conduit à des vibrations néfastes pour les structures et les satellites embarqués. Les ODP sont encore aujourd'hui un vaste sujet de recherche et la simulation numérique est un outil indispensable dans leur analyse. De nombreux travaux ont permis de mettre en évidence divers mécanismes générateurs d'oscillations, mais la conception des nouveaux moteurs favorise la formation d'une instabi
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26

Wang, Lei. "Investigations into deep cracks in rocket motor propellant models." Thesis, Virginia Tech, 1990. http://hdl.handle.net/10919/42146.

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Star grain configuration design has been widely used in solid rocket applications for several decades. Although a large number of surface cracks are detected in the rocket motor propellants, the mechanism of these cracks is sull not well known due to the complex geometry of the grain. A stress-freezing photoelastic investigation has been performed to study the deep cracks which emanate from the fingertips of the star-shaped cutout cylinders. Using three-dimensional photoelasticity and proper algorithms in fracture mechanics, the stress intensity factors (SIF's) and the stress singularity ord
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27

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.

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Design process of a solid rocket motor with the objective of meeting certain mission requirements can be specified as a search for a best set of design parameters within the overall design constraints. In order to ensure that the best possible design amongst all achievable designs is being achieved, optimization is required during the design process. In this thesis, an optimization tool for internal ballistic design of solid rocket motors was developed. A direct search method Complex algorithm is used in this study. The optimization algorithm changes the grain geometric parameters and nozz
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28

Racine, John A. "Subscale solid rocket motor infrared signature and particle behavior." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/26801.

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29

Gomes, 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.

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In the design and development of solid propellant rocket motors, the use of numerical tools able to simulate, predict and reconstruct the behaviour of a given motor in all its operative conditions is particularly important in order to decrease all the planning and costs. This study is devoted to present an approach to the numerical simulation of a given SPRM internal ballistics, NAWC no. 13, during the quasi steady state by means of a commercial numerical tool, ANSYS FLUENT. The internal ballistics model constructed in this study is a 2-D axisymmetric model, based on several assumption
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30

Qian, 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/.

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31

Hainline, 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.

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The work presented in this thesis deals with the application of optimization tools to the design of solid rocket motor grains per internal ballistic requirements. Research concentrated on the development of an optimization strategy capable of efficiently and consistently optimizing virtually an unlimited range of radial burning solid rocket motor grain geometries. Optimization tools were applied to the design process of solid rocket motor grains through an optimization framework developed to interface optimization tools with the solid rocket motor design system. This was done within a programm
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32

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.

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33

Boyer, 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.

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Cette thèse vise à modéliser les instabilités hydrodynamiques générant des détachements tourbillonnaires pariétaux (ou VSP) responsables des Oscillations De Pression dans les moteurs à propergol solide longs et segmentés par interaction avec l’acoustique du moteur. Ces instabilités sont modélisées en tant que modes de stabilité linéaire globaux de l’écoulement d’un conduit à parois débitantes. En supposant que les structures pariétales émergent d’une perturbation de l’écoulement de base, des modes discrets et indépendants du maillage utilisé sont calculés. Dans ce but, une discrétisation par c
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34

Yilmaz, Okan. "Service Life Assessment Of Solid Rocket Propellants Considering Random Thermal And Vibratory Loads." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614555/index.pdf.

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In this study, a detailed service life assessment procedure for solid propellant rockets under random environmental temperature and transportation loads is introduced. During storage and deployment of rocket motors, uncontrolled thermal environments and random vibratory loads due to transportation induce random stresses and strains in the propellant which provoke mechanical damage. In addition, structural capability degrades due to environmental conditions and induced stresses and strains as well as material capability parameters have inherent uncertainties. In this proposed probabilistic serv
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35

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.

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As advances in solid rocket technology push rocket motors to more extreme operating speeds and temperatures, it becomes increasingly important to have well-designed material systems capable of surviving these harsh conditions. One common component in these systems is the use of a fiber- and particle-reinforced EPDM insulation layer between the motor casing and the solid fuel to shield the casing from the temperatures of the burning fuel and from the high velocity of gas particles traveling within the motor. This work studies several insulation materials to determine which exhibits the highes
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36

Squire, Daniel E. "Flow study of the nozzle region of the space shuttle solid rocket motor." Thesis, This resource online, 1988. http://scholar.lib.vt.edu/theses/available/etd-04122010-083741/.

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37

Snaza, Clay J. "Investigation of the effects of solid rocket motor propellant composition on plume signature." Thesis, Monterey, California. Naval Postgraduate School, 1994. http://hdl.handle.net/10945/28309.

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Approved for public release, distribution is unlimited<br>Three propellants with aluminum/silicon weight percentages of 18/0%, 13.5/4.5%, and 12/6% were fired in a subscale motor to determine if the plume infrared signature could be reduced without a significant loss in specific impulse. Spectral measurements from 2.5 to 5.5 micrometers and thermal measurements from 3.5 to 5.0 micrometers were made. Plume particle size measurements showed that only particles with small diameters (less than 1.93 micrometers) were present with any significant volume. Replacing a portion of the aluminum in a high
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38

Kertadidjaja, Abubakar. "Particle sizing in a solid rocket motor using the measurement of scattered light." Thesis, Monterey, California. Naval Postgraduate School, 1985. http://hdl.handle.net/10945/21483.

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39

Mathesius, Kelly J. "Manufacturing methods for a solid rocket motor propelling a small, fast flight vehicle." Thesis, Massachusetts Institute of Technology, 2019. https://hdl.handle.net/1721.1/122377.

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This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.<br>Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2019<br>Cataloged from student-submitted PDF version of thesis.<br>Includes bibliographical references (pages 97-100).<br>A gap exists in the design space for aircraft mass and speed: no flight vehicles with a mass of less than 10 kg and speed greater than 100 m/s are available. The small, fast "Firefly" flight vehicle is being developed to explore the
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40

Manser, John R. "Solid rocket motor plume particle size measurements using multiple optical techniques in a probe." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA296046.

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41

Scholtz, Kelly Burchell. "Optimisation of solid rocket motor blast tube and nozzle assemblies using computational fluid dynamics." Thesis, Cape Peninsula University of Technology, 2017. http://hdl.handle.net/20.500.11838/2487.

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Thesis (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2017.<br>A framework for optimising a tactical solid rocket motor nozzle is established and investigated within the ANSYS Workbench environment. Simulated results are validated against thrust measurements from the static bench firing of a full-scale rocket. Grid independence is checked and achieved using inflation based meshing. A rocket nozzle contour is parametrized using multiple control points along a spline contour. The design of experiments table is populated by a central composite design method and th
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42

Hetreed, Christopher F. "Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/46038.

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<p>Cold-flow tests were conducted in mediums of air and water to investigate the internal flow field about the nozzle region of a proposed solid rocket motor (SRM) configuration that would potentially replace the current external boosters on NASA's Space Shuttle. One-eighth-scale clear acrylic models of the proposed submerged aft-dome and aft finned grain elements were constructed to simulate the aft segment of the SRM at ignition and 35 seconds into the firing sequence. Pressure, velocity, and turbulence profiles were obtained during cold air testing, while air bubbles and dye were used f
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43

Yildirim, Cengizhan. "Analysis Of Grain Burnback And Internal Flow In Solid Propellant Rocket Motor In 3-dimensions." Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/2/12608283/index.pdf.

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In this thesis, Initial Value Problem of Level-set Method is applied to solid propellant combustion to find the grain burnback. For the performance prediction of the rocket motor, 0-D, 1-D or 3-D flow models are used depending on the type of thre grain configuration.
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44

Grant, Edwin H. "A study of the ignition process of composite solid propellants in a small rocket motor." Princeton University, 2013.

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45

Jung, Jackson H. (Jackson Hoa-Wai). "Modeling, and classical and advanced control of a solid rocket motor thrust vector control system." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12473.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 1993.<br>Includes bibliographical references (leaves 119-124).<br>by Jackson H. Jung.<br>M.S.
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46

Ward, Jami. "REDUCTION OF VORTEX-DRIVEN OSCILLATIONS IN A SOLID ROCKET MOTOR COLD FLOW SIMULATION THROUGH ACTIVE CONTROL." Master's thesis, University of Central Florida, 2006. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4310.

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Control of vortex-driven instabilities was demonstrated via a scaled-down, cold-flow simulation that modeled closed-end acoustics. When vortex shedding frequencies couple with the natural acoustic modes of a choked chamber, potentially damaging low-frequency instabilities may arise. Although passive solutions can be effective, an active control solution is preferable. An experiment was performed to demonstrate an active control scheme for the reduction of vortex-driven oscillations. A non-reacting experiment using a primary flow of air, where both the duct exit and inlet are choked, simulated
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47

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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48

Tóth, Balázs. "Two-phase flow investigation in a cold-gas solid rocket motor model through the study of the slag accumulation process." Doctoral thesis, Universite Libre de Bruxelles, 2008. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210575.

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The present research project is carried out at the von Karman Institute for Fluid Dynamics (Rhode-Saint-Genèse, Belgium) with the financial support of the European Space Agency.<p><p>The first stage of spacecrafts (e.g. Ariane 5, Vega, Shuttle) generally consists of large solid propellant rocket motors (SRM), which often consist of segmented structure and incorporate a submerged nozzle. During the combustion, the regression of the solid propellant surrounding the nozzle integration part leads to the formation of a cavity around the nozzle lip. The propellant combustion generates liquefied alum
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49

Genot, Aurélien. "Instabilités thermoacoustiques dans les moteurs à propergol solide." Thesis, Université Paris-Saclay (ComUE), 2019. http://www.theses.fr/2019SACLC032/document.

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Dans un moteur à propergol solide, des instabilités thermoacoustiques auto-entretenues, induites par le couplage de la dynamique de la combustion des gouttes d’aluminium, libérées par la combustion du propergol, avec le champ acoustique peuvent induire des oscillations de pression.L’analyse menée tout au long de ce manuscrit repose sur un ensemble d’hypothèses simplificatrices: (i) la réponse de la combustion de gouttes d’aluminium aux perturbations acoustiques est contrôlée par l’écoulement local autour de la goutte, (ii) le processus de combustion peut être supposé quasi stationnaire pour la
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50

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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