Results 181 to 190 of about 678 (224)
Numerical Analysis of Nozzle Material Thermochemical Erosion in Hybrid Rocket Engines [PDF]
Journal of Propulsion and Power, 2012 Ablative materials are commonly used to protect the nozzle metallic housing and to provide the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because of interaction with hot gas, these materials are chemically eroded during rocket firing, with a resulting nominal performance reduction.
BIANCHI, DANIELE, NASUTI, Francesco
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Performance of the aerobell extendible nozzle rocket engine
7th Aerospace Sciences Meeting, 1969Aerobell extendible nozzle rocket engine design and performance, cold flow and simulated hot flow test ...
G. HOSACK, R. STROMSTA
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Performance prediction and optimization for liquid rocket engine nozzle
Aerospace Science and Technology, 2007Summary: An optimization approach, based on computational fluid dynamics methodology, is investigated for the performance prediction and optimization of liquid rocket engine nozzle. The CFD code employs implicit Lower-Upper decomposition (LU) scheme for solving the two-dimensional axisymmetric Navier-Stokes (NS) equations and species transport ...
Cai, Guobiao +3 more
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Numerical Determination of Nozzle Admittances in Rocket Engines
2010A numericalmethod in the time domain is introduced to assess the stability with respect to the nozzle’s geometry in liquid rocket engines. A boundary condition for the injector plane in a combustion chamber is presented, where the mass flow fluctuations are set to zero. Thus the acoustic flux over the injector plane is zero even when there is mean flow
Daniel Morgenweck +2 more
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Optimized Dual-Expander Aerospike Nozzle Upper Stage Rocket Engine
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011The Air Force Institute of Technology (AFIT) is researching the cryogenic DualExpander Aerospike Nozzle (DEAN) upper stage rocket engine. The objectives for the DEAN design are 50,000 pounds-force (222 kilonewtons) vacuum thrust, 464 seconds of vacuum specific impulse and a thrust-to-weight ratio of 106.5.
Joshua Hall +3 more
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Design, Manufacturing and Test of a Plug Nozzle Rocket Engine
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002The paper presents the design, manufacture and test of a small 1000 lbf ablative annular plug nozzle rocket engine. The engine was developed by students with the help from faculty and industry professionals as part of the California Launch Vehicle Education Initiative (CALVEIN).
Eric Besnard +3 more
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Thermal Analysis of Nozzle Cooling for Liquid Rocket Engines
54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law, 2003cp =heat capacity Abstract For the thermal protection against high temperature gas stream in thrust chamber and nozzle for liquid rocket engines, film cooling is employed inside the nozzle structure in addition to regenerative cooling by liquid fuel, for example.
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Thrust augmentation nozzle (TAN) concept for rocket engine booster applications
Acta Astronautica, 2006Abstract Aerojet used the patented thrust augmented nozzle (TAN) concept to validate a unique means of increasing sea-level thrust in a liquid rocket booster engine. We have used knowledge gained from hypersonic Scramjet research to inject propellants into the supersonic region of the rocket engine nozzle to significantly increase sea-level thrust ...
Scott Forde, Mel Bulman, Todd Neill
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Radiative Heat Transfer in Film-Cooled Liquid Rocket Engine Nozzles
Journal of Thermophysics and Heat Transfer, 2003A radiation model has been implemented in a Navier-Stokes flow solver to investigate the importance of thermal radiation in film-cooled liquid hydrogen/liquid oxygen rocket engine thrust chambers. Two running conditions were computed: high-altitude and sea-level conditions.
T. Badinand, T. H. Fransson
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Investigation of Nozzle Performance for Rotating Detonation Rocket Engines
2019Progress in conventional rocket engine technologies, based on constant pressure combustion, has plateaued in the past few decades. Rotating detonation engines (RDEs) are of particular interest to the rocket propulsion community as pressure gain combustion may provide improvements to specific impulse relevant to booster applications.
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