Results 91 to 100 of about 13,320 (264)
Numerical Analysis of Convergent-Divergent Angles and Operating Conditions Impact on Rocket Nozzle Performance Parameters [PDF]
INCAS BulletinComprehensive numerical analysis was conducted to elucidate the exhaust performance of rocket engine nozzles. The study focused on unravelling the intricate relationship between convergence and divergence angles and their impact on the exhaust ...
Nabila ALILI +3 more
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Refractory thrust chambers for spacecraft engines Final report [PDF]
Structural reliability tests on pyrolytic graphite and pyrolytic graphite alloys for use in liquid propellant rocket engine thrust chambers and ...
Campbell, J. G., Coulbert, C. D.
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Orbital Maneuvering system design evolution [PDF]
, 1985 Preliminary design considerations and changes made in the baseline space shuttle orbital maneuvering system (OMS) to reduce cost and weight are detailed.
Gibson, C., Humphries, C.
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Numerical Investigation on the Effect of Fuel-Rich Degree in the RBCC Engine under the Ejector Mode
International Journal of Aerospace EngineeringThe ejector mode of the Rocket-Based Combined-Cycle (RBCC) engine is characterized by high fuel consumption. This study is aimed at investigating the influence of the rocket fuel-rich degree on the RBCC engine’s performance under the ejector mode ...
Yizhi Yao +9 more
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Experimental research on the development of an “oxygen (gas) + kerosene” – fueled thruster
Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение, 2018 The results of experimental studies of a rocket engine fueled by gaseous oxygen-kerosene with a thrust of 20N, with four workflow variants are presented.
V. L. Salich
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Numerical Investigation on Effect of Divergent Angle in Convergent-Divergent Rocket Engine Nozzle
Chemical Engineering Transactions, 2018 In rocket, a nozzle is used to control mass flow rate, velocity distribution and pressure of the exhaust gas that emerges out from the combustion chamber. The nozzle is used to alchemize the chemical and thermal energy generated in the combustion chamber
Raghu Ande, Venkata N. Kumar Yerraboina
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Design and Fabrication Development of J-2X Engine Metallic Nozzle Extension [PDF]
Maximized rocket engine performance is in part derived from expanding combustion gasses through the rocket nozzle. For upper stage engines the nozzles can be quite large. On the J-2X engine, an uncooled extension of a regeneratively cooled nozzle is used
Gradl, P., Kopicz, C.
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Recoverable single stage spacecraft booster Patent [PDF]
, 1967 Recoverable, reusable single stage booster capable of injecting large payloads into circular earth ...
Bono, P.
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, 2008 Control over drop size distributions, injection rates, and geometrical distribution of fuel and oxidizer sprays in bi-propellant rocket engines has the potential to produce more efficient, more stable, less polluting rocket engines.
Bramanti, Cristina +4 more
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Design And Optimization Of Aero-Spike Nozzle In Rocket Engine
, 2017 {"references": ["1.\tDumnov, G. E., Nikulin, G. Z., and Ponomaryov, N. B., ''Investigation of Advanced Nozzles for Rocket Engines,'' Space Rocket Engines and Power Plants, Vol. 4, No. 142, NIITP, 1993, pp. 10.12 \u201310.18. 2.\tNguyen, T. V., and Pieper, J. L., ''Nozzle Flow Separation,'' Proceedings of the 5th International Symposium of Propulsion in
M. Thangavelu, A. Karthik
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