Littérature scientifique sur le sujet « Moteur solide »
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Articles de revues sur le sujet "Moteur solide"
Bin, Fabrice. « Le mythe de la summa divisio impôt directs/impôts indirects : le moteur à mouvement perpétuel du débat fiscal ». Gestion & ; Finances Publiques, no 1 (janvier 2021) : 35–42. http://dx.doi.org/10.3166/gfp.2021.1.007.
Texte intégralReddé, Michel. « Le développement économique des campagnes romaines dans le nord de la Gaule et l’île de Bretagne ». Annales. Histoire, Sciences Sociales 77, no 1 (mars 2022) : 105–45. http://dx.doi.org/10.1017/ahss.2022.41.
Texte intégralTozune, Akira, Michio Matsunami et Masafumi Sakamoto. « Reduction of Stepping Moter Vibration by Solid Rotor Use ». IEEJ Transactions on Industry Applications 108, no 2 (1988) : 189. http://dx.doi.org/10.1541/ieejias.108.189.
Texte intégralBouchiba, Bousmaha, Saïd Benaceur, Ismaïl Khalil Bousserhane et Mohamed Habbab. « Réalisation d’un variateur de vitesse d’un MCC dédie au séchoir solaire ». Journal of Renewable Energies 20, no 4 (31 décembre 2017) : 573–79. http://dx.doi.org/10.54966/jreen.v20i4.650.
Texte intégralZaninetti, Jean-Marc. « États-Unis : des dynamiques de population face à des mutations structurelles ». Les Analyses de Population & ; Avenir N° 48, no 1 (13 mars 2024) : 1–24. http://dx.doi.org/10.3917/lap.048.0001.
Texte intégralLe Jeannic, Thomas. « Rôle des migrations dans le peuplement de l'Ile-de-France ». Population Vol. 48, no 6 (1 juin 1993) : 1813–54. http://dx.doi.org/10.3917/popu.p1993.48n6.1854.
Texte intégralDesplanques, Guy, Daniel Courgeau et Brigitte Baccaïni. « Les migrations internes en France de 1982 à 1990. Comparaison avec les périodes antérieures ». Population Vol. 48, no 6 (1 juin 1993) : 1771–89. http://dx.doi.org/10.3917/popu.p1993.48n6.1789.
Texte intégralMeyssonnier, Simone. « Vincent de Gournay (1712-1759) et la «Balance des hommes» ». Population Vol. 45, no 1 (1 janvier 1990) : 87–112. http://dx.doi.org/10.3917/popu.p1990.45n1.0112.
Texte intégralFerreras, Isabelle, Ian MacDonald, Gregor Murray et Valeria Pulignano. « L’expérimentation institutionnelle au travail, pour le meilleur (ou pour le pire) ». Transfer : European Review of Labour and Research 26, no 2 (mai 2020) : 119–25. http://dx.doi.org/10.1177/1024258920926445.
Texte intégralCamargo, Karine Dalla Vecchia, Débora Siniscalchi, Natalia Vilas Boas Fonseca, Maria Luisa Curvelo Silva, Carlos Eduardo Vicente Junior, Déborah Marcia Felipe Rodrigues, Carlos Eduardo Lima et al. « PSXII-26 Effect of Different Supplements Plus Phytogenic Additives on Ruminal Bacterial Community of Grazing Beef Cattle ». Journal of Animal Science 101, Supplement_3 (6 novembre 2023) : 638–40. http://dx.doi.org/10.1093/jas/skad281.743.
Texte intégralThèses sur le sujet "Moteur solide"
Breil, Jérôme. « Modélisation du remplissage en propergol de moteur à propulsion solide ». Bordeaux 1, 2001. http://www.theses.fr/2001BOR10505.
Texte intégralDoisneau, 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.
Texte intégralIn solid rocket motors, the internal flow depends strongly on the alumina droplets, which have a high mass fraction. The droplet size distribution, which is wide and spreads up with coalescence, plays a key role. Solving for unsteady polydisperse two- phase flows with high accuracy on the droplet sizes is a challenge for both modeling and scientific computing: (1) very small droplets, e.g. resulting from the combustion of nanoparticles of aluminum fuel, encounter Brownian motion and coalescence, (2) small droplets have their velocity conditioned by size so they coalesce when having different sizes, (3) bigger droplets have an inertial behavior and may cross each other’s trajectory, and (4) all droplets interact in a two-way coupled manner with the carrier phase. As an alternative to Lagrangian approaches, some Eulerian models can describe the disperse phase at a moderate cost, with an easy coupling to the carrier phase and with massively parallel codes: they are well-suited for industrial computations. The Multi- Fluid model allows the detailed description of polydispersity, size/velocity correlations and coalescence by separately solving “fluids” of size-sorted droplets, the so-called sections. In the present work, we assess an ensemble of models and we develop a numerical strategy to perform industrial computations of solid rocket motor flows. (1) The physics of nanoparticles is assessed and included in a polydisperse coalescing model. High order moment methods are then developed: (2) a Two-Size moment method is ex- tended to coalescence to treat accurately the physics of polydispersity and coalescence and the related numerical developments allow to perform applicative computations in the industrial code CEDRE; (3) a second order velocity moment method is developed, together with a second order transport scheme, to evaluate a strategy for a moderately inertial disperse phase, and academic validations are performed on complex flow fields; (4) a time integration strategy is developed and implemented in CEDRE to treat efficiently two-way coupling, in unsteady polydisperse cases including very small particles. The developments are carefully validated, either through purposely derived analytical formulae (for coalescence and two-way acoustic coupling), through numerical cross-comparisons (for coalescence with a Point-Particle DNS, for applicative cases featuring coalescence and two-way coupling with a Lagrangian method), or through available experimental results (for coalescence with an academic experiment, for the overall physics with a sub-scale motor firing). The whole strategy allows to perform applicative computations in a cost effective way. In particular, a solid rocket motor with nanoparticles is computed as a feasibility case and to guide the research effort on motors with nanoparticle fuel propellants
Muller, Mathieu. « Modélisation de la combustion de gouttes d'aluminium dans les conditions d'un moteur fusée à propergol solide ». Thesis, Sorbonne université, 2019. http://www.theses.fr/2019SORUS267.
Texte intégralThe purpose of this thesis is to study the aluminum (Al) droplet combustion in solid rocket motor propellant. We need to model this process to evaluate the burning time and the residues length because their characterization in real conditions is very complex. A combustion model of a single droplet with a multiphysical spherical approach has been developed taking into account various phenomena. This model has been validated and used to study gaseous and surface mechanisms. Simulations in controlled atmospheres were made and the results were compared to experimental data. The study of the combustion of two particle classes (primary particle and agglomerate) under conditions typical for the Ariane 5 solid booster was conducted to evaluate the effect of different heterogeneous surface kinetics on the simulated combustion process. After the integration of the reactive surface model in the ONERA code CEDRE, simulations of the combustion using a two-dimensional axisymmetric approach were made to study the impact of the cap on the droplet surface and the convection velocity of oxidizers. By simulating the established combustion of two droplet classes at two pressures (5 and 9 MPa) in different stages of combustion, we evaluated main characteristics of the combustion and we deducted a global burning law. Finally, the heating of the droplet before an established combustion was studied to complete the characterization
Poubeau, Adèle. « Simulation des émissions d'un moteur à propergol solide : vers une modélisation multi-échelle de l'impact atmosphérique des lanceurs ». Thesis, Toulouse 3, 2015. http://www.theses.fr/2015TOU30039/document.
Texte intégralRockets have an impact on the chemical composition of the atmosphere, and particularly on stratospheric ozone. Among all types of propulsion, Solid-Rocket Motors (SRMs) have given rise to concerns since their emissions are responsible for a severe decrease in ozone concentration in the rocket plume during the first hours after a launch. The main source of ozone depletion is due to the conversion of hydrogen chloride, a chemical compound emitted in large quantities by ammonium perchlorate based propellants, into active chlorine compounds, which then react with ozone in a destructive catalytic cycle, similar to those responsible for the Antartic "Ozone hole". This conversion occurs in the hot, supersonic exhaust plume, as part of a strong second combustion between chemical species of the plume and air. The objective of this study is to evaluate the active chlorine concentration in the far-field plume of a solid-rocket motor using large-eddy simulations (LES). The gas is injected through the entire nozzle of the SRM and a local time-stepping method based on coupling multi-instances of the fluid solver is used to extend the computational domain up to 400 nozzle exit diameters downstream of the nozzle exit. The methodology is validated for a non-reactive case by analyzing the flow characteristics of the resulting supersonic co-flowing under-expanded jet. Then the chemistry of chlorine is studied off-line using a complex chemistry solver applied on trajectories extracted from the LES time-averaged flow-field. Finally, the online chemistry is analyzed by means of the multi-species version of the LES solver using a reduced chemical scheme. To the best of our knowledge, this represents one of the first LES of a reactive supersonic jet, including nozzle geometry, performed over such a long computational domain. By capturing the effect of mixing of the exhaust plume with ambient air and the interactions between turbulence and combustion, LES offers an evaluation of chemical species distribution in the SRM plume with an unprecedented accuracy. These results can be used to initialize atmospheric simulations on larger domains, in order to model the chemical reactions between active chlorine and ozone and to quantify the ozone loss in SRM plumes
Richard, Julien. « Développement d'une chaîne de calcul pour les interactions fluide-structure et application aux instabilités aéro-acoustiques d'un moteur à propergol solide ». Thesis, Montpellier 2, 2012. http://www.theses.fr/2012MON20256/document.
Texte intégralLarge solid propellant rocket motors may be subjected to aero-acoustic instabilities arising from a coupling between the burnt gas flow and the acoustic eigenmodes of the combustion chamber. These instabilities lead to large pressure oscillations in the combustion chamber. These pressure oscillations cause vibrations which might jeopardize the payload if they happen to be larger than a certain threshold. Given the size and cost of any single firing test or launch, it is of first importance to rely on numerical tools able to predict these instabilities so that they can be avoided at the design level. The first purpose of this thesis is to build a numerical tool in order to evaluate how the coupling of the fluid flow and the whole structure of the motor influences the amplitude of the aeroacoustic oscillations living inside the rocket. A particular attention was paid to the coupling algorithm between the fluid and the solid solvers in order to ensure the best energy conservation through the interface.The numerical chain is applied to a sub-scaled configuration of Ariane 5 solid rocket motor in two studies. The first relates to the impact of vibration of the structure on aeroacoustic instabilities. The effect of a crossover frequency between the longitudinal modes of the structure and the acoustic modes of the combustion chamber is assessed. The second study examines the effect of thermal protection oscillations in the flow. An increased of the flow organisation and a significant strengthening of pressure oscillations are highlighted
Kiyoshi, Shimote Wilson. « Modélisation des phénomènes d'ablation de l'insert d'une tuyère de moteur-fusée à propergol solide. Approche expérimentale et numérique ». Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2016. http://www.theses.fr/2016ESMA0028/document.
Texte intégralThe main objective of this study is understand the ablation mechanisms in the presence of a critical environment in pressure and temperature within a solid propellant rocket motor. The well-known parameters, aluminum percentage in the flow, adiabatic flame temperature and the consequent heat flux in front of the geometry of the insert and its thermochemical properties are studied from anumerical and experimental strategy. The ablation phenomenon, which occurs at the nozzle insert during the operation of the solid propellant rocket motor, is th us studied and results of tests of the small and full-scale motors are presented as well as numerically simulated. Indeed, tests carried-out provide results on the conditions of the material of the insert before and after firing tests, do not allow is to provide a complete analysis of the development of the mechanisms involved during the running time of the engines. To introduce these rather complex physical phenomena a strategy of progressive development is followed. Initially, a 1D model treated the heat transfer equations using a multi-block numerical discretization technique. From the 1D method, simple expressions to represent the evolution of the ablation and pyrolysis fronts are defined. These expressions are then used directly on the treatment of axisymmetric problems and confronted with simulations of the scale motor. Finally, the immersed boundary method is applied to tackle coupling between flow and heat transfer on the insert, highlighting the phenomenon of ablation. The numerical simulations reproduce the experimental results and show a robust numerical methodology, corresponding to expectations in what concerns the evaluation of the ablation phenomenon within a solid propellant rocket motor nozzle
Pascal, Jérôme. « Vitesse de combustion d'un propergol solide composite en présence d'oscillations de la vitesse de l'écoulement ». Paris 11, 1987. http://www.theses.fr/1987PA112066.
Texte intégralBreton, Mélanie. « Détection de l'allumage d'un moteur-fusée à propergol solide avec une matrice linéaire de filtres holographiques et par diffraction conique ». Thesis, Université Laval, 2007. http://www.theses.ulaval.ca/2007/24914/24914.pdf.
Texte intégralLacassagne, 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.
Texte intégralSilvestrini, 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.
Texte intégralLivres sur le sujet "Moteur solide"
Panel, North Atlantic Treaty Organization Research and Technology Organization Applied Vehicle Technology. Internal aerodyamics in solid rocket propulsion : L'ae rodynamique interne de la propulsion par moteurs-fuse es a propergois solides. Neuilly-sur-Seine Cedex, France : North Atlantic Treaty Organisation, Research and Technology Organisation, 2004.
Trouver le texte intégralG, Schirk P., et United States. National Aeronautics and Space Administration., dir. Facility design consideration for continuous mix production of class 1.3 propellant. [Washington, DC : National Aeronautics and Space Administration, 1994.
Trouver le texte intégralSilhouettes. Street soldier 2. Deer Park, NY : Urban Books, 2012.
Trouver le texte intégralAngulo, Teresa Cárdenas. Letters to my mother. Toronto : Groundwood Books/House of Anansi Press, 2006.
Trouver le texte intégral[Cooke, Chauncey H. Soldier boy's letters to his father and mother, 1862-1965. Independence, WI : Rainbow Press, 2004.
Trouver le texte intégralD, Smith S., Myruski Brian L et United States. National Aeronautics and Space Administration., dir. Radiation from advanced solid rocket motor plumes. Huntsville, AL : SECA, Inc., 1994.
Trouver le texte intégralD, Smith S., Myruski Brian L et United States. National Aeronautics and Space Administration., dir. Radiation from advanced solid rocket motor plumes. Huntsville, AL : SECA, Inc., 1994.
Trouver le texte intégralKatz, Rothman Barbara, dir. Centuries of solace : Expressions of maternal grief in popular literature. Philadelphia : Temple University Press, 1992.
Trouver le texte intégralCleckley, Julia. A promise fulfilled : My life as a wife and mother, soldier and general officer. [United States] : [CreateSpace Independent Pub. Platform], 2013.
Trouver le texte intégralYuhno, Natal'ya. Mathematics. ru : INFRA-M Academic Publishing LLC., 2021. http://dx.doi.org/10.12737/1002604.
Texte intégralChapitres de livres sur le sujet "Moteur solide"
Ostaševičius, Vytautas, Vytautas Bagdonas, Sigitas Tamulevičius et V. Grigaliūnas. « Analysis of a Microelectrostatic Motor ». Dans Solid State Phenomena, 185–89. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.185.
Texte intégralWohlhart, K. « Motor Tensor Calculus ». Dans Solid Mechanics and Its Applications, 93–102. Dordrecht : Springer Netherlands, 1995. http://dx.doi.org/10.1007/978-94-011-0333-6_10.
Texte intégralZhou, Jian Jun, Yu Liang Pan et Min Huang. « A Novel Magnetostrictive Drive Rotary Motor ». Dans Solid State Phenomena, 1203–6. Stafa : Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/3-908451-30-2.1203.
Texte intégralMracek, Maik, Tobias Hemsel, Piotr Vasiljev et Jörg Wallaschek. « Self Configuration of a Novel Miniature Ultrasonic Linear Motor ». Dans Solid State Phenomena, 167–72. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.167.
Texte intégralChang, Yoon Suk, H. K. Kim, Jae Boong Choi et Young Jin Kim. « Structural Stress Based Fatigue Life Evaluation for Heat Exchanger Motor Operated Valve ». Dans Solid State Phenomena, 39–44. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-15-9.39.
Texte intégralVasiljev, Piotr, S. Borodinas, R. Bareikis, L. Vasiljeva et A. Irzhikevichius. « The Stator of Rotating Type Piezo-Motor Based on "Shaking Beam" Actuator ». Dans Solid State Phenomena, 203–6. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.203.
Texte intégralYoun, Jeong Il, et Young Jig Kim. « Application of Semi-Solid Process for Production of the Induction Motor Squirrel Cage ». Dans Solid State Phenomena, 730–33. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-26-4.730.
Texte intégralAmano, Ryoichi S., Yi-Hsin Yen et Michael L. Hamman. « Solid-Fuel Rocket Motor Efficiency Improvement Scheme ». Dans Novel Combustion Concepts for Sustainable Energy Development, 535–60. New Delhi : Springer India, 2014. http://dx.doi.org/10.1007/978-81-322-2211-8_23.
Texte intégralGečys, S., S. Gudžius, L. Markevičius et A. Morkvėnas. « Critical Slip in Maximum Electromagnetic Power of a Motor for Borehole Prospecting Mechatronic Devices ». Dans Solid State Phenomena, 55–60. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.55.
Texte intégralBaskys, A., R. Rinkevičienė, S. Jegorov et Andrius Petrovas. « Modeling of a Mechatronic System with the AC Induction Motor Supplied by the Frequency Converter ». Dans Solid State Phenomena, 19–24. Stafa : Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.19.
Texte intégralActes de conférences sur le sujet "Moteur solide"
Pandey, Ashutosh, Bharath Madduri, Chin-Yuan Perng, Chiranth Srinivasan et Sujan Dhar. « Multiphase Flow and Heat Transfer in an Electric Motor ». Dans ASME 2022 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/imece2022-96801.
Texte intégralJONES, KENNETH, et LOWELL ZOLLER. « Advanced solid rocket motor ». Dans 25th Joint Propulsion Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2621.
Texte intégralKamm, Yair, et Alon Gany. « Solid Rocket Motor Optimization ». Dans 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4695.
Texte intégralHaglind, Fredrik, Henrik Edefur et Stefan Olsson. « Design of a Solid Propellant Air Turbo Rocket for a Tactical Air-Launched Missile ». Dans ASME Turbo Expo 2007 : Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27826.
Texte intégralOsborne, Eric, Robert Light, David Hardy et Matt Steele. « Solid rocket motor random vibration ». Dans 37th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3925.
Texte intégralMCDONALD, ALLAN. « Redesigned solid rocket motor enhancements ». Dans 25th Joint Propulsion Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2620.
Texte intégralSmit, Gideon J., Johannes Knoetze, Francois Steyn, Charle W. Rousseau et Erhardt R. De Kock. « Rapid Solid Rocket Motor Design ». Dans 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-3789.
Texte intégralMITCHELL, ROYCE. « The Advanced Solid Rocket Motor ». Dans Space Programs and Technologies Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1655.
Texte intégralWiedemann, Carsten, Maren Homeister, Michael Oswald, Sebastian Stabroth, Heiner Klinkrad et Peter Vörsmann. « Additional Historical Solid Rocket Motor Burns ». Dans 57th International Astronautical Congress. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.iac-06-b6.2.07.
Texte intégralDi Giacinto, Maurizio, et Ferruccio Serraglia. « Modeling of solid motor start-up ». Dans 37th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3448.
Texte intégralRapports d'organisations sur le sujet "Moteur solide"
Fry, Ronald S. Solid Propellant Test Motor Scaling. Fort Belvoir, VA : Defense Technical Information Center, septembre 2001. http://dx.doi.org/10.21236/ada386366.
Texte intégralKo, Malcolm, Run-Lie Shia, Debra Weisenstein, Jose Rodriguez et Nien-Dak Sze. Global Stratospheric Impact of Solid Rocket Motor Launchers. Fort Belvoir, VA : Defense Technical Information Center, septembre 1999. http://dx.doi.org/10.21236/ada413823.
Texte intégralChelner, Herbert. Embedded Sensor Technology for Solid Rocket Motor Health Monitoring. Fort Belvoir, VA : Defense Technical Information Center, juillet 2002. http://dx.doi.org/10.21236/ada405070.
Texte intégralChelner, Herbert. Embedded Sensor Technology for Solid Rocket Motor Health Monitoring. Fort Belvoir, VA : Defense Technical Information Center, février 2003. http://dx.doi.org/10.21236/ada412607.
Texte intégralReaugh, J., E. Lee et J. Maienschein. The Production of Airblast From Solid Rocket Motor Fallbacks. Office of Scientific and Technical Information (OSTI), septembre 2012. http://dx.doi.org/10.2172/1053686.
Texte intégralAguilo Valentin, Miguel Alejandro, Steven W. Bova et David R. Noble. Solid Rocket Motor Design using a Low-Dimensional Fluid Model. Office of Scientific and Technical Information (OSTI), février 2019. http://dx.doi.org/10.2172/1496883.
Texte intégralHyde, R. S. A Solid Rocket Motor Manufacturer's View of Sensors and Aging Surveillance. Fort Belvoir, VA : Defense Technical Information Center, juin 2002. http://dx.doi.org/10.21236/ada406078.
Texte intégralKoo, J. H., O. A. Ezekoye, M. C. Bruns et J. C. Lee. Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation. Fort Belvoir, VA : Defense Technical Information Center, septembre 2009. http://dx.doi.org/10.21236/ada564427.
Texte intégralKoo, J. H., et O. D. Ezekoye. Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation. Fort Belvoir, VA : Defense Technical Information Center, septembre 2006. http://dx.doi.org/10.21236/ada589776.
Texte intégralDolan, K. W., G. M. Curnow, D. E. Perkins, D. J. Schneberk, B. W. Costerus, M. J. La Chapell, D. E. Turner et P. W. Wallace. Real-time radiography of Titan IV Solid Rocket Motor Upgrade (SRMU) static firing test QM-2. Office of Scientific and Technical Information (OSTI), mars 1994. http://dx.doi.org/10.2172/10151773.
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