Littérature scientifique sur le sujet « Rocket engine nozzle »
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Articles de revues sur le sujet "Rocket engine nozzle"
Strelnikov, G. A., A. D. Yhnatev, N. S. Pryadko et S. S. Vasyliv. « Gas flow control in rocket engines ». Technical mechanics 2021, no 2 (29 juin 2021) : 60–77. http://dx.doi.org/10.15407/itm2021.02.060.
Texte intégralJéger, Csaba, et Árpád Veress. « Novell Application of CFD for Rocket Engine Nozzle Optimization ». Periodica Polytechnica Transportation Engineering 47, no 2 (10 janvier 2018) : 131–35. http://dx.doi.org/10.3311/pptr.11490.
Texte intégralGuram, Sejal, Vidhanshu Jadhav, Prasad Sawant et Ankit Kumar Mishra. « Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine ». 1 2, no 1 (1 mars 2023) : 4–14. http://dx.doi.org/10.46632/jame/2/1/2.
Texte intégralZAGANESCU, Nicolae-Florin, Rodica ZAGANESCU et Constantin-Marcian GHEORGHE. « Wernher Von Braun’s Pioneering Work in Modelling and Testing Liquid-Propellant Rockets ». INCAS BULLETIN 14, no 2 (10 juin 2022) : 153–61. http://dx.doi.org/10.13111/2066-8201.2022.14.2.13.
Texte intégralBogoi, Alina, Radu D. Rugescu, Valentin Ionut Misirliu, Florin Radu Bacaran et Mihai Predoiu. « Inviscid Nozzle for Aerospike Rocket Engine Application ». Applied Mechanics and Materials 811 (novembre 2015) : 152–56. http://dx.doi.org/10.4028/www.scientific.net/amm.811.152.
Texte intégralSultanov, T. S., et G. A. Glebov. « Numerical Computation of Specific Impulse and Internal Flow Parameters in Solid Fuel Rocket Motors with Two-Phase Сombustion Products ». Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no 3 (138) (septembre 2021) : 98–107. http://dx.doi.org/10.18698/0236-3941-2021-3-98-107.
Texte intégralBruce Ralphin Rose, J., et J. Veni Grace. « Performance analysis of lobed nozzle ejectors for high altitude simulation of rocket engines ». International Journal of Modeling, Simulation, and Scientific Computing 05, no 04 (29 septembre 2014) : 1450019. http://dx.doi.org/10.1142/s1793962314500196.
Texte intégralShustov, S. A., I. E. Ivanov et I. A. Kryukov. « Numerical study of the separation of a turbulent boundary in rocket engine nozzles with an optimized supersonic part ». Journal of Physics : Conference Series 2308, no 1 (1 juillet 2022) : 012015. http://dx.doi.org/10.1088/1742-6596/2308/1/012015.
Texte intégralVasyliv, S. S., et H. O. Strelnykov. « Rocket engine thrust vector control by detonation product injection into the supersonic portion of the nozzle ». Technical mechanics 2020, no 4 (10 décembre 2020) : 29–34. http://dx.doi.org/10.15407/itm2020.04.029.
Texte intégralKumar, S. Senthil, et M. Arularasu. « Advanced Computational Flow Analysis - Rocket Engine Nozzle ». Asian Journal of Research in Social Sciences and Humanities 6, no 11 (2016) : 1219. http://dx.doi.org/10.5958/2249-7315.2016.01265.x.
Texte intégralThèses sur le sujet "Rocket engine nozzle"
Östlund, Jan. « Supersonic flow separation with application to rocket engine nozzles ». Doctoral thesis, KTH, Mechanics, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3793.
Texte intégralThe increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in fullscale, due to the uncertainties involved in modeling andpredicting the flow phenomena involved.
In the present work the causes of unsteady and unsymmetricalflow separation and resulting side-loads in rocket enginenozzles are investigated. This involves the use of acombination of analytical, numerical and experimental methods,which all are presented in the thesis. A main part of the workis based on sub-scale testing of model nozzles operated withair. Hence, aspects on how to design sub-scale models that areable to capture the relevant physics of full-scale rocketengine nozzles are highlighted. Scaling laws like thosepresented in here are indispensable for extracting side-loadcorrelations from sub-scale tests and applying them tofull-scale nozzles.
Three main types of side-load mechanisms have been observedin the test campaigns, due to: (i) intermittent and randompressure fluctuations, (ii) transition in separation patternand (iii) aeroelastic coupling. All these three types aredescribed and exemplified by test results together withanalysis. A comprehensive, up-to-date review of supersonic flowseparation and side-loads in internal nozzle flows is givenwith an in-depth discussion of different approaches forpredicting the phenomena. This includes methods for predictingshock-induced separation, models for predicting side-loadlevels and aeroelastic coupling effects. Examples are presentedto illustrate the status of various methods, and theiradvantages and shortcomings are discussed.
A major part of the thesis focus on the fundamentalshock-wave turbulent boundary layer interaction (SWTBLI) and aphysical description of the phenomenon is given. Thisdescription is based on theoretical concepts, computationalresults and experimental observation, where, however, emphasisis placed on the rocket-engineering perspective. This workconnects the industrial development of rocket engine nozzles tothe fundamental research of the SWTBLI phenomenon and shows howthese research results can be utilized in real applications.The thesis is concluded with remarks on active and passive flowcontrol in rocket nozzles and directions of futureresearch.
The present work was performed at VAC's Space PropulsionDivision within the framework of European spacecooperation.
Keywords:turbulent, boundary layer, shock wave,interaction, overexpanded,rocket nozzle, flow separation,control, side-load, experiments, models, review.
Östlund, Jan. « Flow Processes in Rocket Engine Nozzles with Focus on Flow Separation and Side-Loads ». Licentiate thesis, KTH, Mechanics, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-1452.
Texte intégralWahlström, Dennis. « Probabilistic Multidisciplinary Design Optimization on a high-pressure sandwich wall in a rocket engine application ». Thesis, Umeå universitet, Institutionen för fysik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:umu:diva-138480.
Texte intégralBulut, Jane. « Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application ». Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.
Trouver le texte intégralGarby, Romain. « Simulations of flame stabilization and stability in high-pressure propulsion systems ». Phd thesis, Toulouse, INPT, 2013. http://oatao.univ-toulouse.fr/9706/1/garby.pdf.
Texte intégralDenton, Brandon Lee. « Design and analysis of rocket nozzle contours for launching pico-satellites / ». Online version of thesis, 2008. http://hdl.handle.net/1850/6003.
Texte intégral(6927776), Alexis Joy Harroun. « Investigation of Nozzle Performance for Rotating Detonation Rocket Engines ». Thesis, 2019.
Trouver le texte intégralLivres sur le sujet "Rocket engine nozzle"
United States. National Aeronautics and Space Administration., dir. Comparison of two procedures for predicting rocket engine nozzle performance. [Washington, DC] : National Aeronautics and Space Administration, 1987.
Trouver le texte intégralMarable, R. W. Design, fabrication, and test of the RL10 derivative II chamber/primary nozzle. [West Palm Beach, Fla : Pratt and Whitney Aircraft, 1989.
Trouver le texte intégralLeonard, Schoenman, et United States. National Aeronautics and Space Administration., dir. Advanced small rocket chambers option 3 : 110 1bf Ir-Re rocket. [Washington, DC] : National Aeronautics and Space Administration, 1995.
Trouver le texte intégralJ, Sovie Amy, Haag Thomas W et United States. National Aeronautics and Space Administration., dir. Arcjet nozzle design impacts. [Washington, DC] : National Aeronautics and Space Administration, 1989.
Trouver le texte intégralMilton, Lamb, et United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20. [Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.
Trouver le texte intégralM, Kim Y., Shang H. M et United States. National Aeronautics and Space Administration., dir. Turbulence modelling of flow fields in thrust chambers : Final technical report for the period June 10, 1991 through September 13, 1992. [Huntsville, Ala.] : Research Institute, the University of Alabama in Huntsville, 1993.
Trouver le texte intégralM, Kim Y., Shang H. M et United States. National Aeronautics and Space Administration., dir. Turbulence modelling of flow fields in thrust chambers : Final technical report for the period June 10, 1991 through September 13, 1992. [Huntsville, Ala.] : Research Institute, the University of Alabama in Huntsville, 1993.
Trouver le texte intégralJ, Pavli Albert, Kacynski Kenneth J et United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., dir. Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m℗ø(350 psia). [Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.
Trouver le texte intégralGeorge C. Marshall Space Flight Center., dir. Flight motor set 360H005 (STS-28R). Brigham City, UT : Thiokol Corp., Space Operations, 1990.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration., dir. Calculation of propulsive nozzle flowfields in multidiffusing chemically recating environments. [Washington, DC] : National Aeronautics and Space Administration, 1994.
Trouver le texte intégralChapitres de livres sur le sujet "Rocket engine nozzle"
Ludescher, Sandra, et Herbert Olivier. « Film Cooling in Rocket Nozzles ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 65–78. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_4.
Texte intégralAlamu, Samuel O., Marc J. Louise Caballes, Yulai Yang, Orlyse Mballa et Guangming Chen. « 3D Design and Manufacturing Analysis of Liquid Propellant Rocket Engine (LPRE) Nozzle ». Dans Advances in Intelligent Systems and Computing, 968–80. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-32523-7_73.
Texte intégralBarfusz, Oliver, Felix Hötte, Stefanie Reese et Matthias Haupt. « Pseudo-transient 3D Conjugate Heat Transfer Simulation and Lifetime Prediction of a Rocket Combustion Chamber ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 265–78. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_17.
Texte intégralSansica, A., J. Ch Robinet, Eric Goncalves et J. Herpe. « Three-Dimensional Instability of Shock-Wave/Boundary-Layer Interaction for Rocket Engine Nozzle Applications ». Dans 31st International Symposium on Shock Waves 2, 523–30. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_67.
Texte intégralSansica, A., J. Ch Robinet, Eric Goncalves et J. Herpe. « Correction to : Three-Dimensional Instability of Shock-Wave/Boundary-Layer Interaction for Rocket Engine Nozzle Applications ». Dans 31st International Symposium on Shock Waves 2, C1. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_148.
Texte intégralDecher, Reiner. « More Components : Inlets, Mixers, and Nozzles ». Dans The Vortex and The Jet, 137–54. Singapore : Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8028-1_13.
Texte intégralMorgenweck, Daniel, Jutta Pieringer et Thomas Sattelmayer. « Numerical Determination of Nozzle Admittances in Rocket Engines ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 579–86. Berlin, Heidelberg : Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14243-7_71.
Texte intégral« Rocket Engine Nozzle Concepts ». Dans Liquid Rocket Thrust Chambers, 437–67. Reston ,VA : American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/5.9781600866760.0437.0467.
Texte intégralActes de conférences sur le sujet "Rocket engine nozzle"
MCAMIS, R., D. LANKFORD et W. PHARES. « Theoretical liquid rocket engine nozzle flow fields ». Dans 28th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3730.
Texte intégralRobles, Luis R., Johnny Ho, Bao Nguyen, Geoffrey Wagner, Jeremy Surmi, Khulood Faruqui, Ashley Carter et al. « Conceptual Regenerative Nozzle Cooling Design for a Hydroxyl-Terminated Polybutadiene and Oxygen Hybrid Rocket Engine ». Dans ASME 2017 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/detc2017-68396.
Texte intégralAmano, Ryoichi S., et Yi-Hsin Yen. « Design of Solid Rocket Engine ». Dans ASME 2015 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/detc2015-48092.
Texte intégralHall, Joshua, Carl Hartsfield, Joseph Simmons et Richard Branam. « Optimized Dual-Expander Aerospike Nozzle Upper Stage Rocket Engine ». Dans 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-419.
Texte intégralManski, Detlef, et Gerald Hagemann. « Influence of rocket design parameters on engine nozzle efficiencies ». Dans 30th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2756.
Texte intégralStewart, Kyle J., Periklis Papadopoulos et Jordan Pollard. « Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle ». Dans AIAA Propulsion and Energy 2020 Forum. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3841.
Texte intégralMatveev, Valeriy, Vasilii Zubanov, Leonid Shabliy et Anastasia Korneeva. « Optimization of Nozzle Shape of Hydrogen-Oxygen Rocket Engine ». Dans 8th International Conference on Simulation and Modeling Methodologies, Technologies and Applications. SCITEPRESS - Science and Technology Publications, 2018. http://dx.doi.org/10.5220/0006890003650370.
Texte intégralKozlov, Alexander, Jose Hinckel et Adalberto Comiran. « Investigation of a nozzle tap-off liquid rocket engine scheme ». Dans 32nd Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-3118.
Texte intégralBesnard, Eric, Hsun Hu Chen, Tom Mueller et John Garvey. « Design, Manufacturing and Test of a Plug Nozzle Rocket Engine ». Dans 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-4038.
Texte intégralDAVIDIAN, KENNETH. « Comparison of two procedures for predicting rocket engine nozzle performance ». Dans 23rd Joint Propulsion Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2071.
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