Beckstead, M. W. and Mathes, H. B. and Price, E. W. and Culick, F. E. C. (1969) Combustion instability of solid propellants. Symposium (International) on Combustion, 12 (1). pp. 203-211. ISSN 0082-0784. http://resolver.caltech.edu/CaltechAUTHORS:20101221-114030246
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Experimental data has been obtained from two T-burners and an L^* burner over a range of frequencies from 10 cps to 8000 cps and from 25 psia to 1000 psia. From these data the response of the propellants to a pressure perturbation has been calculated and has been found to be consistent between burners. The results have been interpreted as a response function surface with burning rate and frequencies as independent variables. The data indicates that for a given pressure level the response function has a peak value at a frequency that increases as pressure increases. The magnitude of this peak height varies with pressure so that there is a localized peak in the response function surface for a given propellant. The results are in qualitative agreement with theoretical studies in that the models also predict a maximum value in the response function. However, they also predict that this magnitude should be approximately a constant and not dependent on the pressure and frequency to the extent observed in the present study. The results obtained for an aluminized propellant indicate that presence of metal in the combustion zone greatly influences both the magnitude of the response function peak as well as its location.
|Additional Information:||© 1969 Published by Elsevier B.V. Available online 27 April 2007. This work was performed under National Aeronautics and Space Administration Work Order No. 6030 and Naval Ordnance Systems Command Task No. ORD-088 108/200 I/F009-06-01 PA No.8.|
|Group:||Guggenheim Jet Propulsion Center|
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|Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Ruth Sustaita|
|Deposited On:||23 Dec 2010 17:43|
|Last Modified:||26 Dec 2012 12:47|
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