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Artykuły w czasopismach na temat "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, nr 1 (styczeń 2021): 35–42. http://dx.doi.org/10.3166/gfp.2021.1.007.
Pełny tekst źródłaReddé, Michel. "Le développement économique des campagnes romaines dans le nord de la Gaule et l’île de Bretagne". Annales. Histoire, Sciences Sociales 77, nr 1 (marzec 2022): 105–45. http://dx.doi.org/10.1017/ahss.2022.41.
Pełny tekst źródłaTozune, Akira, Michio Matsunami i Masafumi Sakamoto. "Reduction of Stepping Moter Vibration by Solid Rotor Use". IEEJ Transactions on Industry Applications 108, nr 2 (1988): 189. http://dx.doi.org/10.1541/ieejias.108.189.
Pełny tekst źródłaBouchiba, Bousmaha, Saïd Benaceur, Ismaïl Khalil Bousserhane i Mohamed Habbab. "Réalisation d’un variateur de vitesse d’un MCC dédie au séchoir solaire". Journal of Renewable Energies 20, nr 4 (31.12.2017): 573–79. http://dx.doi.org/10.54966/jreen.v20i4.650.
Pełny tekst źródłaZaninetti, Jean-Marc. "États-Unis : des dynamiques de population face à des mutations structurelles". Les Analyses de Population & Avenir N° 48, nr 1 (13.03.2024): 1–24. http://dx.doi.org/10.3917/lap.048.0001.
Pełny tekst źródłaLe Jeannic, Thomas. "Rôle des migrations dans le peuplement de l'Ile-de-France". Population Vol. 48, nr 6 (1.06.1993): 1813–54. http://dx.doi.org/10.3917/popu.p1993.48n6.1854.
Pełny tekst źródłaDesplanques, Guy, Daniel Courgeau i Brigitte Baccaïni. "Les migrations internes en France de 1982 à 1990. Comparaison avec les périodes antérieures". Population Vol. 48, nr 6 (1.06.1993): 1771–89. http://dx.doi.org/10.3917/popu.p1993.48n6.1789.
Pełny tekst źródłaMeyssonnier, Simone. "Vincent de Gournay (1712-1759) et la «Balance des hommes»". Population Vol. 45, nr 1 (1.01.1990): 87–112. http://dx.doi.org/10.3917/popu.p1990.45n1.0112.
Pełny tekst źródłaFerreras, Isabelle, Ian MacDonald, Gregor Murray i Valeria Pulignano. "L’expérimentation institutionnelle au travail, pour le meilleur (ou pour le pire)". Transfer: European Review of Labour and Research 26, nr 2 (maj 2020): 119–25. http://dx.doi.org/10.1177/1024258920926445.
Pełny tekst źródłaCamargo, Karine Dalla Vecchia, Débora Siniscalchi, Natalia Vilas Boas Fonseca, Maria Luisa Curvelo Silva, Carlos Eduardo Vicente Junior, Déborah Marcia Felipe Rodrigues, Carlos Eduardo Lima i in. "PSXII-26 Effect of Different Supplements Plus Phytogenic Additives on Ruminal Bacterial Community of Grazing Beef Cattle". Journal of Animal Science 101, Supplement_3 (6.11.2023): 638–40. http://dx.doi.org/10.1093/jas/skad281.743.
Pełny tekst źródłaRozprawy doktorskie na temat "Moteur solide"
Breil, Jérôme. "Modélisation du remplissage en propergol de moteur à propulsion solide". Bordeaux 1, 2001. http://www.theses.fr/2001BOR10505.
Pełny tekst źródłaDoisneau, 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.
Pełny tekst źródłaIn 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.
Pełny tekst źródłaThe 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.
Pełny tekst źródłaRockets 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.
Pełny tekst źródłaLarge 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.
Pełny tekst źródłaThe 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.
Pełny tekst źródłaBreton, 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.
Pełny tekst źródłaLacassagne, 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.
Pełny tekst źródłaSilvestrini, 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.
Pełny tekst źródłaKsiążki na temat "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.
Znajdź pełny tekst źródłaG, Schirk P., i United States. National Aeronautics and Space Administration., red. Facility design consideration for continuous mix production of class 1.3 propellant. [Washington, DC: National Aeronautics and Space Administration, 1994.
Znajdź pełny tekst źródłaSilhouettes. Street soldier 2. Deer Park, NY: Urban Books, 2012.
Znajdź pełny tekst źródłaAngulo, Teresa Cárdenas. Letters to my mother. Toronto: Groundwood Books/House of Anansi Press, 2006.
Znajdź pełny tekst źródła[Cooke, Chauncey H. Soldier boy's letters to his father and mother, 1862-1965. Independence, WI: Rainbow Press, 2004.
Znajdź pełny tekst źródłaD, Smith S., Myruski Brian L i United States. National Aeronautics and Space Administration., red. Radiation from advanced solid rocket motor plumes. Huntsville, AL: SECA, Inc., 1994.
Znajdź pełny tekst źródłaD, Smith S., Myruski Brian L i United States. National Aeronautics and Space Administration., red. Radiation from advanced solid rocket motor plumes. Huntsville, AL: SECA, Inc., 1994.
Znajdź pełny tekst źródłaKatz, Rothman Barbara, red. Centuries of solace: Expressions of maternal grief in popular literature. Philadelphia: Temple University Press, 1992.
Znajdź pełny tekst źródłaL, Doyle M., red. A promise fulfilled: My life as a wife and mother, soldier and general officer. [United States]: [CreateSpace Independent Pub. Platform], 2013.
Znajdź pełny tekst źródłaYuhno, Natal'ya. Mathematics. ru: INFRA-M Academic Publishing LLC., 2021. http://dx.doi.org/10.12737/1002604.
Pełny tekst źródłaCzęści książek na temat "Moteur solide"
Ostaševičius, Vytautas, Vytautas Bagdonas, Sigitas Tamulevičius i V. Grigaliūnas. "Analysis of a Microelectrostatic Motor". W Solid State Phenomena, 185–89. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.185.
Pełny tekst źródłaWohlhart, K. "Motor Tensor Calculus". W Solid Mechanics and Its Applications, 93–102. Dordrecht: Springer Netherlands, 1995. http://dx.doi.org/10.1007/978-94-011-0333-6_10.
Pełny tekst źródłaZhou, Jian Jun, Yu Liang Pan i Min Huang. "A Novel Magnetostrictive Drive Rotary Motor". W Solid State Phenomena, 1203–6. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/3-908451-30-2.1203.
Pełny tekst źródłaMracek, Maik, Tobias Hemsel, Piotr Vasiljev i Jörg Wallaschek. "Self Configuration of a Novel Miniature Ultrasonic Linear Motor". W Solid State Phenomena, 167–72. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.167.
Pełny tekst źródłaChang, Yoon Suk, H. K. Kim, Jae Boong Choi i Young Jin Kim. "Structural Stress Based Fatigue Life Evaluation for Heat Exchanger Motor Operated Valve". W Solid State Phenomena, 39–44. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-15-9.39.
Pełny tekst źródłaVasiljev, Piotr, S. Borodinas, R. Bareikis, L. Vasiljeva i A. Irzhikevichius. "The Stator of Rotating Type Piezo-Motor Based on "Shaking Beam" Actuator". W Solid State Phenomena, 203–6. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.203.
Pełny tekst źródłaYoun, Jeong Il, i Young Jig Kim. "Application of Semi-Solid Process for Production of the Induction Motor Squirrel Cage". W Solid State Phenomena, 730–33. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-26-4.730.
Pełny tekst źródłaAmano, Ryoichi S., Yi-Hsin Yen i Michael L. Hamman. "Solid-Fuel Rocket Motor Efficiency Improvement Scheme". W 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.
Pełny tekst źródłaGečys, S., S. Gudžius, L. Markevičius i A. Morkvėnas. "Critical Slip in Maximum Electromagnetic Power of a Motor for Borehole Prospecting Mechatronic Devices". W Solid State Phenomena, 55–60. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.55.
Pełny tekst źródłaBaskys, A., R. Rinkevičienė, S. Jegorov i Andrius Petrovas. "Modeling of a Mechatronic System with the AC Induction Motor Supplied by the Frequency Converter". W Solid State Phenomena, 19–24. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/3-908451-21-3.19.
Pełny tekst źródłaStreszczenia konferencji na temat "Moteur solide"
Pandey, Ashutosh, Bharath Madduri, Chin-Yuan Perng, Chiranth Srinivasan i Sujan Dhar. "Multiphase Flow and Heat Transfer in an Electric Motor". W ASME 2022 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/imece2022-96801.
Pełny tekst źródłaJONES, KENNETH, i LOWELL ZOLLER. "Advanced solid rocket motor". W 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2621.
Pełny tekst źródłaKamm, Yair, i Alon Gany. "Solid Rocket Motor Optimization". W 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.
Pełny tekst źródłaHaglind, Fredrik, Henrik Edefur i Stefan Olsson. "Design of a Solid Propellant Air Turbo Rocket for a Tactical Air-Launched Missile". W ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27826.
Pełny tekst źródłaOsborne, Eric, Robert Light, David Hardy i Matt Steele. "Solid rocket motor random vibration". W 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3925.
Pełny tekst źródłaMCDONALD, ALLAN. "Redesigned solid rocket motor enhancements". W 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2620.
Pełny tekst źródłaSmit, Gideon J., Johannes Knoetze, Francois Steyn, Charle W. Rousseau i Erhardt R. De Kock. "Rapid Solid Rocket Motor Design". W 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.
Pełny tekst źródłaMITCHELL, ROYCE. "The Advanced Solid Rocket Motor". W Space Programs and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1655.
Pełny tekst źródłaWiedemann, Carsten, Maren Homeister, Michael Oswald, Sebastian Stabroth, Heiner Klinkrad i Peter Vörsmann. "Additional Historical Solid Rocket Motor Burns". W 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.
Pełny tekst źródłaDi Giacinto, Maurizio, i Ferruccio Serraglia. "Modeling of solid motor start-up". W 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3448.
Pełny tekst źródłaRaporty organizacyjne na temat "Moteur solide"
Fry, Ronald S. Solid Propellant Test Motor Scaling. Fort Belvoir, VA: Defense Technical Information Center, wrzesień 2001. http://dx.doi.org/10.21236/ada386366.
Pełny tekst źródłaKo, Malcolm, Run-Lie Shia, Debra Weisenstein, Jose Rodriguez i Nien-Dak Sze. Global Stratospheric Impact of Solid Rocket Motor Launchers. Fort Belvoir, VA: Defense Technical Information Center, wrzesień 1999. http://dx.doi.org/10.21236/ada413823.
Pełny tekst źródłaChelner, Herbert. Embedded Sensor Technology for Solid Rocket Motor Health Monitoring. Fort Belvoir, VA: Defense Technical Information Center, lipiec 2002. http://dx.doi.org/10.21236/ada405070.
Pełny tekst źródłaChelner, Herbert. Embedded Sensor Technology for Solid Rocket Motor Health Monitoring. Fort Belvoir, VA: Defense Technical Information Center, luty 2003. http://dx.doi.org/10.21236/ada412607.
Pełny tekst źródłaReaugh, J., E. Lee i J. Maienschein. The Production of Airblast From Solid Rocket Motor Fallbacks. Office of Scientific and Technical Information (OSTI), wrzesień 2012. http://dx.doi.org/10.2172/1053686.
Pełny tekst źródłaAguilo Valentin, Miguel Alejandro, Steven W. Bova i David R. Noble. Solid Rocket Motor Design using a Low-Dimensional Fluid Model. Office of Scientific and Technical Information (OSTI), luty 2019. http://dx.doi.org/10.2172/1496883.
Pełny tekst źródłaHyde, R. S. A Solid Rocket Motor Manufacturer's View of Sensors and Aging Surveillance. Fort Belvoir, VA: Defense Technical Information Center, czerwiec 2002. http://dx.doi.org/10.21236/ada406078.
Pełny tekst źródłaKoo, J. H., O. A. Ezekoye, M. C. Bruns i J. C. Lee. Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation. Fort Belvoir, VA: Defense Technical Information Center, wrzesień 2009. http://dx.doi.org/10.21236/ada564427.
Pełny tekst źródłaKoo, J. H., i O. D. Ezekoye. Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation. Fort Belvoir, VA: Defense Technical Information Center, wrzesień 2006. http://dx.doi.org/10.21236/ada589776.
Pełny tekst źródłaDolan, K. W., G. M. Curnow, D. E. Perkins, D. J. Schneberk, B. W. Costerus, M. J. La Chapell, D. E. Turner i 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), marzec 1994. http://dx.doi.org/10.2172/10151773.
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