Results 161 to 170 of about 412,817 (220)
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Analysis of hybrid rocket combustion
Acta Astronautica, 1980Abstract The problem involving flow of a turbulent boundary layer with mass injection and combustion is studied to investigate the hydrid rocket combustion. Because of the presence of combustion, the momentum equation is coupled to the energy and species equations.
Cherng, D. L., Tao, C. C.
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Hybrid rocket combustion study
29th Joint Propulsion Conference and Exhibit, 1993The objectives of this study of 'pure' or 'classic' hybrids are to (1) extend our understanding of the boundary layer combustion process and the critical engineering parameters that define this process, (2) develop an up-to-date hybrid fuel combustion model, and (3) apply the model to correlate the regression rate and scaling properties of potential ...
L. STRAND, R. RAY, N. COHEN
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Nonlinear longitudinal combustion instability in rocket motors
11th Aerospace Sciences Meeting, 1973A new analytical technique for the solution of nonlinear longitudinal combustion instability problems in rocket combustors is developed. Using relatively little computation time, this technique is capable of predicting the transient and limit cycle behavior of the combustion instability oscillations as well as the disturbance amplitude required to ...
MANUEL E. LORES, BEN T. ZINN
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Combustion of metal agglomerates in a solid rocket core flow
Acta Astronautica, 2013Abstract The need for access to space may require the use of solid propellants. High thrust and density are appealing features for different applications, spanning from boosting phase to other service applications (separation, de-orbiting, orbit insertion).
MAGGI, FILIPPO +2 more
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TURBULENT BOUNDARY LAYER COMBUSTION IN THE HYBRID ROCKET
Symposium (International) on Combustion, 1963In this paper an effort has been made to survey recent theoretical and experimental work related to several aspects of the hybrid combustion process. It has been found that hybrid combustion is controlled by the rate at which heat can be delivered to the fuel surface, rather than by the surface reaction rates.
G. Marxman, M. Gilbert
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The Sampling of Rocket Combustion Gases
The Journal of the Royal Aeronautical Society, 1964Summary:—In the past, attempts have been made to evaluate injectors for rocket engine combustion chambers by the use of water analogy rigs and model combustion systems that simulated the injection and combustion phase change occurring in the actual engine.
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Combustion termination of solid rocket motors
Journal of Spacecraft and Rockets, 1965To explore the feasibility of terminating combustion without the hazardous flame and debris associated with venting, a series of sixteen 5-in.-diam motors was fired. Two techniques were investigated: 1) injection of liquid into the combustion chamber, and 2) explosive discharge of coolants from a canister located inside the chamber.
H. J. TABACK, E. E. DAY, T. P. BROWNE
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Towards Affordable LES of Rocket Combustion Engines
2018Due to the large disparity of length and time scales in rocket combustors corresponding LES are highly time consuming. Steps towards simulating rocket combustion engines with affordable LES with the compressible, implicit combustion code TASCOM3D are presented.
Keller, Roman +3 more
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Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability
2012Abstract : The goal of the project was to understand how changes in the rate of energy addition can be used to alter the combustion instability characteristics of liquid rocket engines. Fuels with increased energy, either due to higher heats of formation or energetic additives, presumably result in higher performance. This study seeks to understand how
Steven S. Son +2 more
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Combustion Instability in Solid Propellant Rockets.
1987Abstract : This report constitutes the principal of a book on combustion stability in solid propellant rockets. The present report contains nine chapters that are each substantially complete except for some editorial, bibliographical and art work in some chapters.
G. A. Flandro, E. W. Price
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