Relevant bibliographies by topics / Rocket combustion

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Rocket combustion'

Author: Grafiati
Published: 4 June 2021
Last updated: 4 February 2022

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Journal articles on the topic "Rocket combustion"

1

Hu, Jichao, Juntao Chang, and Wen Bao. "Ignition and Flame Stabilization of a Strut-Jet RBCC Combustor with Small Rocket Exhaust." Scientific World Journal 2014 (2014): 1–6. http://dx.doi.org/10.1155/2014/675498.

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A Rocket Based Combined Cycle combustor model is tested at a ground direct connected rig to investigate the flame holding characteristics with a small rocket exhaust using liquid kerosene. The total temperature and the Mach number of the vitiated air flow, at exit of the nozzle are 1505 K and 2.6, respectively. The rocket base is embedded in a fuel injecting strut and mounted in the center of the combustor. The wall of the combustor is flush, without any reward step or cavity, so the strut-jet is used to make sure of the flame stabilization of the second combustion. Mass flow rate of the keros
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Bolivar, Nelson Enrique, and Ivaylo T. Vasilev. "Non-Combustion ⁴He Powered Propulsion." European Journal of Engineering and Technology Research 6, no. 2 (2021): 101–6. http://dx.doi.org/10.24018/ejers.2021.6.2.2283.

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One of the biggest hurdles nowadays rocket propulsion is the large use of fuel. The amount of fuel and the burning efficiency defines how long the rocket engine can work which intimately limits the range and the load capacity of the rockets and spaceships. This according to the Newton third law is unavoidable - in order to move forward you need to leave something behind. There have been several attempts in the past to create an engine which doesn't use fuel in the common sense, like the M drive, but so far all of them were unsuccessful. In this article we attempt to explore a novel principle,
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Li, Chaolong, Zhixun Xia, Likun Ma, Xiang Zhao, and Binbin Chen. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity." Energies 12, no. 7 (2019): 1235. http://dx.doi.org/10.3390/en12071235.

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is dem
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Lee, Y. W., and T. L. Jiang. "Effects of Fuel Impingement-Cooling on the Combustion Flow in a Small Bipropellant Liquid Rocket Thruster." Journal of Mechanics 31, no. 2 (2015): 161–70. http://dx.doi.org/10.1017/jmech.2014.81.

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ABSTRACTIn the present study, a three-dimensional computer code, based on the computer software KIVA-3, was developed for the combustion-flow simulation of a bipropellant liquid rocket thruster. A jets-impingement model is proposed for the unlike-doublet jet impingement issue. The computer code is employed to simulate a small bipropellant liquid rocket engine installed with three unlike-doublet injectors of NTO and MMH as well as six fuel injectors injecting MMH toward the combustor wall for cooling. Effects of the fuel-injection cooling on the combustion flow, combustion efficiency, and wall
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Shi, Lei, Da Gao, Liangliang Xing, Fei Qin, and Guoqiang He. "Numerical Study on Thermal Choke Behaviors Driven by Various Rocket Operations in an RBCC Engine in Ramjet Mode." International Journal of Turbo & Jet-Engines 37, no. 3 (2020): 305–17. http://dx.doi.org/10.1515/tjj-2019-0012.

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AbstractThermal choke is commonly employed in a fixed geometry RBCC combustor to eliminate the need for physically variable exit geometry. This paper proposed detailed numerical studies based on a two-dimensional integration model to characterize thermal choke behaviors driven by various embedded rocket operations in an RBCC engine at Mach 4 in ramjet mode. The influences of different embedded rocket operations as well as the corresponding secondary fuel injection adjustment on thermal choke generation process, the related thermal throat feature, and the engine performance are analyzed. Operat
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Jin, Xuan, Chibing Shen, Rui Zhou, and Xinxin Fang. "Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine." International Journal of Aerospace Engineering 2020 (September 15, 2020): 1–16. http://dx.doi.org/10.1155/2020/8867199.

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LOX/GCH4 pintle injector is suitable for variable-thrust liquid rocket engines. In order to provide a reference for the later design and experiments, three-dimensional numerical simulations with the Euler-Lagrange method were performed to study the effect of the initial particle diameter on the combustion characteristics of a LOX/GCH4 pintle rocket engine. Numerical results show that, as the momentum ratio between the radial LOX jet and the axial gas jet is 0.033, the angle between the LOX particle trace and the combustor axial is very small. Due to the large recirculation zones, premixed comb
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Jiang, Tsung Leo, and Huei-Huang Chiu. "Bipropellant combustion in a liquid rocket combustion chamber." Journal of Propulsion and Power 8, no. 5 (1992): 995–1003. http://dx.doi.org/10.2514/3.23584.

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Reardon, Frederick H. "Liquid rocket engine combustion instability." Combustion and Flame 109, no. 3 (1997): 501–3. http://dx.doi.org/10.1016/s0010-2180(96)00180-0.

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Dominiak, Adam, Michał Rąpała, Roman Domański, Bartosz Bartkowiak, and Piotr Darnowski. "Solid-fuel Rocket Engines: Layered Composite Materials Manufacturing and Thermal Diffusivity Measurements." High Temperature Materials and Processes 33, no. 2 (2014): 171–77. http://dx.doi.org/10.1515/htmp-2013-0054.

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AbstractThis communication presents thermal diffusivity measurements of fourteen layered insulating composite materials. Composite materials that were taken under investigation contained matrixes based on epoxy and phenol-formaldehyde resins and reinforcements, such as glass, basalt fiber and wrapping or ceramic paper. They were all prepared by the Rocket Section of the Students Space Association (RS-SSA). Manufacturing process of samples is described. Additional objective of this research was to obtain the quality of such prepared materials and if they are reliable enough to be used in solid-
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Yuan, Lei, and Chibing Shen. "Computational investigation on combustion instabilities in a rocket combustor." Acta Astronautica 127 (October 2016): 634–43. http://dx.doi.org/10.1016/j.actaastro.2016.06.015.

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Dissertations / Theses on the topic "Rocket combustion"

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

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Thesis (M.S. in Astronautical Engineering, Aeronautical and Astronautical Engineer) Naval Postgraduate School, Dec. 2001.<br>Thesis advisors: Christopher Brophy, Jose Sinibaldi, Ashok Gopinath. "December 2001." Includes bibliographical references (p. 73). Also available in print.
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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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Noonan, Erin E. (Erin Elizabeth) 1978. "Structural analysis of the MIT Micro Rocket Combustion Chamber." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8127.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2002.<br>"June 2002."<br>Includes bibliographical references (p. 209-211).<br>The micro rocket is one of several power microelectromechanical systems (MEMS) under development at MIT. The micro rocket is experiencing structural failures at operating parameters far below the designed performance level. The deterministic strength of brittle materials, such as silicon, is critically dependent on the local strength and flaw population. Experiments and correlating modeling were used to pursue the root cause
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Wall, Neil J. "Characterisation of multiple concentric vortices in hybrid rocket combustion chambers." Thesis, University of Sheffield, 2013. http://etheses.whiterose.ac.uk/4781/.

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Recent developments in hybrid rocket technology involve producing a coaxial bidirectional vortex flow field through use of tangential oxidiser injection at the base of the combustion chamber. This is found to significantly increase engine performance by providing enhanced thermal transfer at the fuel surface, resulting in increased fuel regression rates in addition to more efficient combustion. The double helical path of the flow results in reduced reactant loss at the chamber outlet whilst confining combustion to a high temperature core region defined by the inner vortex. This also results in
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Ghosh, Amardip. "The role of density gradient in liquid rocket engine combustion instability." College Park, Md.: University of Maryland, 2008. http://hdl.handle.net/1903/8903.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2008.<br>Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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Ruiz, Anthony. "Unsteady Numerical Simulations of Transcritical Turbulent Combustion in Liquid Rocket Engines." Thesis, Toulouse, INPT, 2012. http://www.theses.fr/2012INPT0009/document.

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Ces cinquantes dernières années, la majorité des paramètres de conception des moteurs cryotechniques ont été ajustés en l'absence d'une compréhension détaillée des phénomènes de combustion, en raison des limites des diagnostiques expérimentaux et des capacités de calcul. L'objectif de cette thèse est de réaliser des simulations numériques instationnaires d'écoulements réactifs transcritiques de haute fidélité, pour permettre une meilleure compréhension de la dynamique de flamme dans les moteurs cryotechniques et finalement guider leur amélioration. Dans un premier temps, la thermodynamique gaz
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Kirchberger, Christoph [Verfasser]. "Investigation on Heat Transfer in Small Hydrocarbon Rocket Combustion Chambers / Christoph Kirchberger." München : Verlag Dr. Hut, 2014. http://d-nb.info/1064559999/34.

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

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In this thesis, combustion processes in a laboratory-scale methane based low pressure rocket motor (LPRM) is studied experimentally and numerically. Experiments are conducted to measure flame temperatures and chamber temperature and pressure. Single reaction-four species reacting flow of gaseous methane and gaseous oxygen in the combustion chamber is also simulated numerically using a commercial CFD solver based on 2-D, steady-state, viscous, turbulent and compressible flow assumptions. LPRM geometry is simplified to several configurations, i.e. Channel and Combustion Chamber with Nozzle and F
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Savur, Mehmet Koray. "A numerical study of combined convective and radiative heat transfer in a rocket engine combustion chamber." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Dec%5FSavur.pdf.

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

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

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Dranovsky, Mark L. Combustion Instabilities in Liquid Rocket Engines. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/4.866906.

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Quentmeyer, Richard J. Rocket combustion chamber life-enhancing design concepts. National Aeronautics and Space Administration, Lewis Research Center, 1990.

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Wang, Zhen-Guo. Internal Combustion Processes of Liquid Rocket Engines. John Wiley & Sons Singapore Pte Ltd, 2016. http://dx.doi.org/10.1002/9781118890035.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. AGARD, 1991.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. AGARD, 1991.

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Green, James M. A premixed hydrogen/oxygen catalytic igniter. National Aeronautics and Space Administration, 1989.

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Dranovsky, Mark L. Combustion instabilities in liquid rocket engines: Testing and development practices in Russia. American Institute of Aeronautics and Astronautics, 2007.

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Etele, Jason. Computational study of variable area ejector rocket flowfields. University of Toronto, Institute for Aerospace Studies], 2004.

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Arbib, H. A. Heavy hydrocarbon main injector technology program: Final report. Rocketdyne Division of Rockwell International Corporation, 1991.

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Greatrix, David R. A study of combustion and flow behaviour in solid-propellant rocket motors. [Institute for Aerospace Studies], 1987.

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Book chapters on the topic "Rocket combustion"

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Seitz, Timo, Ansgar Lechtenberg, and Peter Gerlinger. "Rocket Combustion Chamber Simulations Using High-Order Methods." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_24.

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Abstract High-order spatial discretizations significantly improve the accuracy of flow simulations. In this work, a multi-dimensional limiting process with low diffusion (MLP$$^\text {ld}$$) and up to fifth order accuracy is employed. The advantage of MLP is that all surrounding volumes of a specific volume may be used to obtain cell interface values. This prevents oscillations at oblique discontinuities and improves convergence. This numerical scheme is utilized to investigate three different rocket combustors, namely a seven injector methane/oxygen combustion chamber, the widely simulated PennState preburner combustor and a single injector chamber called BKC, where pressure oscillations are important.
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Cheng, S. I. "L*-Combustion Instability in Solid Propellant Rocket Combustion." In Recent Advances in the Aerospace Sciences. Springer US, 1985. http://dx.doi.org/10.1007/978-1-4684-4298-4_13.

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Armbruster, Wolfgang, Justin S. Hardi, and Michael Oschwald. "Experimental Investigation of Injection-Coupled High-Frequency Combustion Instabilities." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_16.

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Abstract Self-excited high-frequency combustion instabilities were investigated in a 42-injector cryogenic rocket combustor under representative conditions. In previous research it was found that the instabilities are connected to acoustic resonance of the shear-coaxial injectors. In order to gain a better understanding of the flame dynamics during instabilities, an optical access window was realised in the research combustor. This allowed 2D visualisation of supercritical flame response to acoustics under conditions similar to those found in European launcher engines. Through the window, high-speed imaging of the flame was conducted. Dynamic Mode Decomposition was applied to analyse the flame dynamics at specific frequencies, and was able to isolate the flame response to injector or combustion chamber acoustic modes. The flame response at the eigenfrequencies of the oxygen injectors showed symmetric and longitudinal wave-like structures on the dense oxygen core. With the gained understanding of the BKD coupling mechanism it was possible to derive LOX injector geometry changes in order to reduce the risks of injection-coupled instabilities for future cryogenic rocket engines.
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Rashkovskiy, Sergey A., Yury M. Milyokhin, and Alexander V. Fedorychev. "Combustion of Solid Propellants with Energetic Binders." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_16.

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Babuk, Valery A. "Formulation Factors and Properties of Condensed Combustion Products." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_13.

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Peichl, Jonas, Andreas Schwab, Markus Selzer, Hannah Böhrk, and Jens von Wolfersdorf. "Innovative Cooling for Rocket Combustion Chambers." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_3.

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Abstract Transpiration cooling in combination with permeable ceramic-matrix composite materials is an innovative cooling method for rocket engine combustion chambers, while providing high cooling efficiency as well as enhancing engine life time as demanded for future space transportation systems. In order to develop methods and tools for designing transpiration cooled systems, fundamental experimental investigations were performed. An experimental setup consisting of a serial arrangement of four porous carbon fiber reinforced carbon (C/C) samples is exposed to a hot gas flow. Perfused with cold air, the third sample is unperfused in order to assess the wake flow development over the uncooled sample as well as the rebuilding of the coolant layer. Hereby, the focus is on the temperature boundary layer, using a combined temperature/pitot probe. Additionally, the sample surface temperature distribution was measured using IR imaging. The experiments are supported by numerical simulations which are showing a good agreement with measurement data for low blowing ratios.
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Weiser, Volker, Andrea Franzin, Luigi T. DeLuca, et al. "Combustion Behavior of Aluminum Particles in ADN/GAP Composite Propellants." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_10.

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Traxinger, Christoph, Julian Zips, Christian Stemmer, and Michael Pfitzner. "Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_13.

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Abstract The design and development of future rocket engines severely relies on accurate, efficient and robust numerical tools. Large-Eddy Simulation in combination with high-fidelity thermodynamics and combustion models is a promising candidate for the accurate prediction of the flow field and the investigation and understanding of the on-going processes during mixing and combustion. In the present work, a numerical framework is presented capable of predicting real-gas behavior and nonadiabatic combustion under conditions typically encountered in liquid rocket engines. Results of Large-Eddy Simulations are compared to experimental investigations. Overall, a good agreement is found making the introduced numerical tool suitable for the high-fidelity investigation of high-pressure mixing and combustion.
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Pei, Jiangfeng, Fengqi Zhao, Ying Wang, Siyu Xu, Xiuduo Song, and Xueli Chen. "Energy and Combustion Characteristics of Propellants Based on BAMO-GAP Copolymer." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_14.

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Park, Kyung-Su, Yang Na, and Changjin Lee. "Internal Flow Characteristics and Low-Frequency Instability in Hybrid Rocket Combustion." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_23.

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Conference papers on the topic "Rocket combustion"

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TAMURA, HIROSHI, FUMIEI ONO, AKINAGA KUMAKAWA, and NOBUYUKI YATSUYANAGI. "LOX/methane staged combustion rocket combustor investigation." In 23rd Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1856.

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STRAND, L., R. RAY, and N. COHEN. "Hybrid rocket combustion study." In 29th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-2412.

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Thomas, M., and A. Leonard. "Air-Turbo-Rocket combustion." In 33rd Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-813.

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Doulatov, Renat, Victor Beliy, and Igor Rossikhin. "Bifurcation of liquid rocket combustion." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3512.

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Frey, Manuel, Thomas Aichner, Josef Görgen, Blazenko Ivancic, Björn Kniesner, and Oliver Knab. "Modeling of Rocket Combustion Devices." In 10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-4329.

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Lemcherfi, Aaron I., Rohan Gejji, Tristan L. Fuller, William E. Anderson, and Carson D. Slabaugh. "Investigation of Combustion Instabilities in a Full Flow Staged Combustion Model Rocket Combustor." In AIAA Propulsion and Energy 2019 Forum. American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3948.

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Morita, Takakazu, Saburo Yuasa, Toru Shimada, and Shigeru Yamaguchi. "Model of Hybrid Rocket Combustion in Classical Hybrid Rocket Motors." In 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-4134.

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Litchford, Ron, and Weiwei Luo. "On Destructive Liquid Rocket Resonant Combustion." In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-5115.

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LITCHFORD, RON, and SAN-MOU JENG. "Liquid rocket spray combustion stability analysis." In 28th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3227.

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Hald, Hermann, Markus Ortelt, Ingo Fischer, Dirk Greuel, and O. Haidn. "Effusion Cooled CMC Rocket Combustion Chamber." In AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-3229.

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Reports on the topic "Rocket combustion"

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Jenkins, R. A., C. W. Nestor, C. V. Thompson, et al. Characterization of rocket propellant combustion products. Office of Scientific and Technical Information (OSTI), 1991. http://dx.doi.org/10.2172/5712917.

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Williams, Forman A. Fundamental Studies of Liquid-Propellant Rocket Combustion. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada425218.

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Anderson, William E., Stephen D. Heister, and Steven S. Son. Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability. Defense Technical Information Center, 2015. http://dx.doi.org/10.21236/ad1001343.

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Anderson, William E., Stephen D. Heister, and Steven S. Son. Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability. Defense Technical Information Center, 2013. http://dx.doi.org/10.21236/ada577052.

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Anderson, William E., Steven F. Son, and Stephen D. Heister. Fuel Chemistry and Combustion Distribution Effects on Rocket Engine Combustion Stability. Defense Technical Information Center, 2012. http://dx.doi.org/10.21236/ada566310.

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Gundersen, Martin A. Plasma-Enhanced Combustion for Reduction of Rocket Plume Soot. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada397824.

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Williams, Forman A. Combustion Processes and Instabilities in Liquid-Propellant Rocket Engines. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada420091.

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Jenkins, R. A. Characterization of rocket propellant combustion products: Description of sampling and analysis methods for rocket exhaust characterization studies. Office of Scientific and Technical Information (OSTI), 1990. http://dx.doi.org/10.2172/6524606.

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Micci, Michael M. Contributions of Atomization, Vaporization and Combustion to Liquid Rocket Acoustic Energy. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada329776.

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Yang, Vigor. Liquid-Propellant Rocket Engine Injector Dynamics and Combustion Processes at Supercritical Conditions. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada428947.

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