Results 181 to 190 of about 29,920 (238)

Experimental solid rocket combustion instability

Symposium (International) on Combustion, 1965
Experience with oscillatory combustion of solid rocket propellants is classified into three categories referred to as high-, intermediate-, and low-frequency instability. In the frequency range 1000 cps and up, instability (a) is usually encountered in transverse modes of the rocket motor; (b) results from interaction between acoustic pressure and the
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Towards Affordable LES of Rocket Combustion Engines

2018
Due 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, Grader, Martin, Gerlinger, Peter, Aigner, Manfred   +3 more
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Combustion termination of solid rocket motors

Journal of Spacecraft and Rockets, 1965
To 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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L*-Combustion Instability in Solid Propellant Rocket Combustion

1985
An analysis of the L*-combustion instability in solid propellant rockets is formulated to include (1) secondary or residual combustion in the rocket chamber and (2) the change of the mean chamber pressure. The aim was to explore if these factors might remedy the failure of the many transient heat-transfer theories with quasi-steady gaseous-phase ...
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Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability

2012
Abstract : 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, Stephen D. Heister, William E. Anderson   +2 more
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Solid Rocket Motor Combustion Chamber Aeroacoustics

AIAA Journal, 1978
ASOURCE of solid rocket motor vibration is investigated by treating the problem of pressure fluctuations inside the motor cavity. Theoretical aeroacoustics is applied to the cavity gases and imbedded burning metal agglomerates. Several critical experiments are performed to provide numerical input to the theory.
Warren C. Strahle, John C. Handley
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Combustion Instability in Solid Propellant Rockets.

1987
Abstract : 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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On Destructive Liquid Rocket Resonant Combustion

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2008
*Experience indicates that the most destructive form of liquid rocket combustion instability is characterized by a steep-fronted, high-amplitude pressure wave sweeping through the combustion chamber in the form of a spinning tangential mode resonance.
Ron Litchford, Weiwei Luo
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Hybrid rocket combustion with prevaporized zone

Aircraft Engineering and Aerospace Technology, 2013
PurposeLow combustion completeness has been the main defect of hybrid rockets. The present study tries to address the problem by bringing up the setup of the precombustion zone, which do not increase the manufacture cost and complexity.Design/methodology/approachA precombustion zone can provide a space for the liquid oxidizer to vaporize before ...
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Comprehensive analysis of liquid rocket combustion

6th Propulsion Joint Specialist Conference, 1970
Abstract : A comprehensive method for analyzing liquid rocket engine combustion is introduced, which utilizes and unifies the results of analytical and experimental research in the fields of liquid propellant injection and combustion. A system of 3-dimensional, time-dependent, nonlinear conservation equations is derived and the necessary expressions ...
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