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Dissertations / Theses on the topic 'Solid propellant rocket'

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Published: 4 June 2021

Last updated: 26 July 2025

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1

Yassin, Jamal Saleh. "Performance of a solid propellent rocket." Connect to this title online, 1986. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1102514752.

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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

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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4

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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5

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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6

Solanki, Niraj. "Effect of external pulse on solid propellant rocket internal ballistics." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape3/PQDD_0028/MQ50491.pdf.

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7

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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8

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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9

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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10

Corvatta, Sarah. "Propellant casting process simulation in a small-scale solid rocket booster." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Small-scale solid rocket motors have been extremely successful among propulsion industries in the last decades for improving the accuracy of thrust-time prediction in new motors in order to reduce the amount of experimental tests needed for the characterization of their internal ballistics behaviour. It is of common knowledge the fact that the ballistic response of solid rocket motors depends on several factors, among which the manufacturing process stands out. It is the grain that defines the quality of the propellant. Therefore, the thrust performance can be affected by heterogeneity of gra

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11

Sankar, Subramanian V. "Investigation of the flame-acoustic wave interaction during axial solid rocket instabilities." Diss., Georgia Institute of Technology, 1987. http://hdl.handle.net/1853/11885.

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12

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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13

Tanaka, Martin Lyn. "Influence of storage environment upon crack opening and growth in composite solid rocket propellant." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-01242009-063016/.

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14

Carro, Rodolphe Valentin. "HIGH PRESSURE TESTING OF COMPOSITE SOLID ROCKET PROPELLANT MIXTURES: BURNER FACILITY CHARACTERIZATION." Master's thesis, University of Central Florida, 2007. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/3204.

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Much Research on composite solid propellants has been performed over the past few decades and much progress has been made, yet many of the fundamental processes are still unknown, and the development of new propellants remains highly empirical. Ways to enhance the performance of solid propellants for rocket and other applications continue to be explored experimentally, including the effects of various additives and the impact of fuel and oxidizer particle sizes on burning behavior. One established method to measure the burning rate of composite propellant mixtures in a controlled laboratory se

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15

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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16

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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17

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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18

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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19

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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20

Bladholm, Viktor. "Organic Fillers for Solid Rocket Fuel." Thesis, KTH, Skolan för kemi, bioteknologi och hälsa (CBH), 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-259589.

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Idag är de vanligaste använda raketerna flytande-bränsle- och fast-bränsle- raketer. Flytande-bränsle-raketer har fördelen att det kan manövreras men de har en komplex design och problem med förvaring. Fast-bränsle-raketer har en enkel design och kan förvaras men de har en miljöpåverkan och bränslet kan vara svårhanterligt. En tredje typ av raketer, hybridraketer, kan kombinera enkelheten från fasta-bränsle-raketer med manövreringsbarheten från vätske-bränsle-raketer. Trots fördelarna med hybridraketer används de inte på grund av att bränslet har låg regressionshastighet och låg densitet. Orga

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21

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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22

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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23

Wang, Lei. "Study of surface cracks in a simulated solid rocket propellant grain with an internal star perforation." Diss., Virginia Tech, 1992. http://hdl.handle.net/10919/38641.

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24

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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25

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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26

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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27

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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28

Toker, Kemal Atilgan. "Three Dimensional Retarding Walls And Flow In Their Vicinity." Phd thesis, METU, 2001. http://etd.lib.metu.edu.tr/upload/12605668/index.pdf.

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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<br>grain burnback calculation&rdquo<br>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 boundari

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29

Ribeiro, Marcos Vinícius Fernandes. "Metodologia de projeto e validação de motores foguete a propelente sólido." Universidade de São Paulo, 2013. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-17052013-145147/.

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Propõe-se aqui uma metodologia de projeto aero-termo-estrutural de motores foguete a propelente sólido. O projeto de um motor foguete deve ser realizado com o objetivo de cumprir requisitos de uma missão. Para cada veículo espacial, com uma nova missão, um novo motor pode ser projetado, necessitando para isso de uma série de ferramentas robustas, capazes de compreender todas as combinações de esforços existentes no funcionamento de um motor, sob condições de altas pressões e temperaturas. A metodologia aqui proposta é testada e validada em bancada de ensaios desenvolvida para este fim. Os resu

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30

Sigvant, John. "Conceptual Design of an Air- launched Multi-stage Launch Vehicle." Thesis, KTH, Fysik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-284355.

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In the present thesis, the objective was to find the maximum amount of payload mass that can be put into a 500 km polar orbit by a 1400 kg air-launched multi-stage rocket launched from a fighter jet platform. To fulfill the objective an algorithm incorporating several modules was developed. The modules performed calculations based on theoretical models and literature values to arrive at optimal design variables. From the design the maximum payload mass was able to be derived and it was concluded that a three-stage launch vehicle was able to deliver a 22.0 kg payload to the desired orbit.<br>I

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31

Silvestrini, Jorge Hugo. "Simulation des grandes échelles des zones de mélange : application à la propulsion solide des lanceurs spatiaux." Grenoble INPG, 1996. http://www.theses.fr/1996INPG0104.

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On presente le formalisme de la simulation des grandes echelles (les) pour l'etude des ecoulements turbulents incompressibles et compressibles, puis les modeles sous-maille qui tiennent compte des echelles plus petites que la maille de calcul. Des tests, en configuration de couche de melange temporelle, permettent de mettre en evidence le comportement de differents modeles. Ensuite, des les des couches de melanges tridimensionnelles temporelles et spatiales sont presentees. Dans le deux cas, on teste deux types de perturbations sur la condition initiale (condition d'entree pour le probleme spa

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32

Yesilirmak, Yener. "Determination Of Degree Of Mixing In Solid Rocket Propellants." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/2/12607751/index.pdf.

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Composite propellants are mainly composed of: crystalline oxidizer, metallic fuel, and polymeric binder. Additives, such as plasticizers, catalysts, bonding agents and curing agents may also be incorporated to propellant compositions in small amounts. These ingredients should be mixed rigorously in order to obtain a uniform microstructure throughout the cast propellant profile. The quality of the propellant mixture has to be determined quantitatively to improve the product quality and to reduce costs. In this study, it was aimed to develop an easy, cost effective and rapid test method for de

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33

Chakravarthy, Satyanarayanan R. "The role of surface layer processes in solid propellant combustion." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/13264.

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34

Perez, Daniel Lizarraga. "Scientific predictability of solid rocket performance: Analyses of the processing parameters." Diss., The University of Arizona, 1992. http://hdl.handle.net/10150/185817.

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The objective of this dissertation is to present a computational model of the suspensions composing uncured composite solid propellant. The work examined highly concentrated suspensions of more than 50% solid volume, with attention to bimodal mixtures. Investigation of propellant processing was conducted to determine how this model can be applied to processing. Experimental work was conducted to supply data for comparison to the computational results. This involved data gathered from an orifice viscometer on viscosity and flow behavior. This model is a tool to investigate goodness of mixing th

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35

Dyer, John David Hartfield Roy J. "Aerospace design optimization using a real coded genetic algorithm." Auburn, Ala, 2008. http://repo.lib.auburn.edu/EtdRoot/2008/SPRING/Aerospace_Engineering/Thesis/Dyer_John_31.pdf.

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36

Rasmussen, Måns. "Conceptual Design of an Air-Launched Three-Staged Orbital Launch Vehicle." Thesis, KTH, Rymdteknik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-302775.

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The objective of this study was to design a launch vehicle capable of deploying a nanosatellite into a Sun-synchronous orbit at 500 km orbital altitude from the JAS 39E/F Gripen fighter aircraft. This was achieved by first performing theoretical calculations for the required nozzles and solid propellant grain configurations for the first two solid stages, followed by the necessary liquid propellant configuration for the third stage. Lastly, two methods were investigated in solving the trajectory ascent problem for the launch vehicle design. First, by stating the trajectory problem as an initia

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37

Barnard, Paul Werner. "The prediction of the emission spectra of flares and solid propellant rockets." Thesis, Stellenbosch : University of Stellenbosch, 2003. http://hdl.handle.net/10019.1/16254.

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Thesis (MScIng)--University of Stellenbosch, 2003.<br>ENGLISH ABSTRACT: It was shown in an earlier study that it is possible to predict the spectral radiance of rocket combustion plumes directly from the propellant composition and motor parameters. Little is published in the open literature on this subject, but the current trend is to use determinative methods like computational fluid dynamics and statistical techniques to simulate wide band radiance based on blackbody temperature assumptions. A limitation of these methods is the fact that they are computationally expensive and rather co

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38

Metts, Jonathan Glen Hartfield Roy J. "Determination of key parameters for reverse engineering solid rocket powered missiles." Auburn, Ala, 2006. http://repo.lib.auburn.edu/2006%20Fall/Theses/METTS_JONATHAN_49.pdf.

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39

Fahlenkamp, Keith B. "Direct observation of two phase flow generated by an alumina seeded grain in high aspect ratio channels." Thesis, Monterey, California : Naval Postgraduate School, 2010. http://edocs.nps.edu/npspubs/scholarly/theses/2010/Jun/10Jun%5FFahlenkamp.pdf.

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Thesis (Mechanical Engineer and M.S. in Mechanical Engineering)--Naval Postgraduate School, June 2010.<br>Thesis Advisor(s): Brophy, Christopher ; Second Reader: Gannon, Anthony. "June 2010." Description based on title screen as viewed on July 13, 2010. Author(s) subject terms: Solid rocket propellant, two phase flow, erosive burning, alumina agglomeration, laser imaging Includes bibliographical references (p. 87). Also available in print.

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40

Chiang, Hau-Jei. "An experimental investigation of the leading edge of diffusion flames." Diss., Georgia Institute of Technology, 1990. http://hdl.handle.net/1853/12346.

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41

Chen, Tzengyuan. "Driving of axial acoustic fields by sidewall stabilized diffusion flames." Diss., Georgia Institute of Technology, 1990. http://hdl.handle.net/1853/12969.

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42

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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43

Lee, James H. "Modeling of crack initiation and growth in solid rocket propellants using macromechanics and micromechanics theories." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1996. http://handle.dtic.mil/100.2/ADA319521.

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Thesis (M.S. in Mechanical Engineering) Naval Postgraduate School, September 1996.<br>Thesis advisor(s): Young W. Kwon. "September 1996." Includes bibliographical references (p. 85-86). Also available online.

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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

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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46

McDavid, Brian Robert Hartfield Roy J. "Launch vehicle performance enhancement using aerodynamic assist." Auburn, Ala, 2008. http://repo.lib.auburn.edu/EtdRoot/2008/SUMMER/Aerospace_Engineering/Thesis/Mcdavid_Brian_9.pdf.

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47

Anthoine, Jérôme P. L. R. "Experimental and numerical study of aeroacoustic phenomena in large solid propellant boosters." Doctoral thesis, Universite Libre de Bruxelles, 2000. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/211712.

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The present research is an experimental and numerical study of aeroacoustic phenomena occurring in large solid rocket motors (SRM) as the Ariane 5 boosters. The emphasis is given to aeroacoustic instabilities that may lead to pressure and thrust oscillations which reduce the rocket motor performance and could damage the payload. The study is carried out within the framework of a CNES (Centre National d'Etudes Spatiales) research program. <p><p>Large SRM are composed of a submerged nozzle and segmented propellant grains separated by inhibitors. During propellant combustion, a cavity appears aro

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48

Marcantoni, Matteo. "Sviluppo dell'interfaccia per il caricamento della geometria iniziale del propellente solido di un modello balistico." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2015. http://amslaurea.unibo.it/9635/.

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Il presente lavoro di tesi, nell’ambito della simulazione balistica di razzi a propellente solido, è volto alla creazione di un’interfaccia che permetta il caricamento delle geometrie dei motori desiderati, in formato SPP, nel codice di simulazione balistica ROBOOST come richiesto da Avio Spa. In particolare saranno descritte le procedure attraverso le quali tale interfaccia è stata realizzata e verranno analizzati i passaggi mediante i quali è possibile ottenere una mesh 3D del motore a propellente solido partendo dalla sua geometria in formato SPP. Si analizzerà inoltre il processo di chiusu

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Bernigaud, Pierre. "Modélisation de la combustion des matériaux énergétiques nouvelle génération." Electronic Thesis or Diss., Institut polytechnique de Paris, 2023. http://www.theses.fr/2023IPPAE017.

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Employés dans les moteurs fusée civiles et militaires, les propergols composites sont caractérisés par une structure hétérogène au niveau microscopique. Ils sont constitués principalement de particules oxydantes insérées au sein d’une matrice de polymère, appelée liant. Le liant maintient l’intégralité structurelle du propergol, et fournit par sa pyrolyse des gaz dont la combustion est responsable de la majorité du dégagement de chaleur dans la flamme. Les produits de combustion des particules oxydantes permettent l’oxydation du fuel généré par la pyrolyse du liant.Le perchlorate d'ammonium (P

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50

Chang, Hao-Ming, and 張皓閔. "Measurement of the Burning Rate of Solid Sugar Rocket Propellant." Thesis, 2015. http://ndltd.ncl.edu.tw/handle/61403447630811437350.

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碩士<br>國立交通大學<br>機械工程系所<br>104<br>Solid rocket is nearly impossible for throttling capability, therefore designing a motor which can produce a desired thrust curve is necessary. In order to precisely predict a thrust curve, a realistic burning rate correlation is very important. The burning rate is a function of combustor pressure and is described by the burning rate equation (r = a*Pn). The parameters “a” and “n” is generally obtained from experimental data. Usually, there are two methods of measurements, which include Crawford strand burner and Ballistic Evaluation Motor (BEM). Crawford stran

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