Proceedings ArticleDOI
Effect of pressure oscillation on the burning rate of solid propellant
A. Morita,T. Nagaoka,H. Isoda +2 more
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The article was published on 1981-07-27. It has received 2 citations till now. The article focuses on the topics: Burn rate (chemistry) & Propellant.read more
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Proceedings ArticleDOI
High Pressure Testing Of Composite Solid Rocket Propellant Mixtures: Burner Facility Characterization
Rodolphe Carro,Matthew Stephens,Jason Arvanetes,Andreiev Powell,Eric L. Petersen,Christopher Smith +5 more
TL;DR: In this article, the authors have installed and characterized a new strand burner facility at the University of Central Florida to provide high-pressure burn rate data at pressures up to 360 atm, and two common HTPB/Ammonium Perchlorate (AP) propellant mixtures containing 7/3 and 5/5 bimodal AP distributions were tested in the burner.
Journal ArticleDOI
Acoustic pressure oscillation effects on mean burning rates of plateau propellants
TL;DR: In this paper, the effects of acoustic pressure oscillations on mean burning rates of non-aluminized and aluminized propellants which exhibit low pressure exponent index (n) in the burning rate trends were investigated.
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Journal ArticleDOI
Depressurization induced extinction of burning solid propellant.
TL;DR: In this paper, the results of a combined theoretical and experimental study of the process in which solid-propellant combustion is terminated by a rapid drop in pressure were presented. And the results were then compared to the predictions of the theoretical model that was based on the assumption that extinction occurs when the heat absorption by the solid propellant exceeds the heat transfer to the solid- propellant from the combustion gas.
Journal ArticleDOI
Effect of Acoustic Environment on the Burning Rate of Solid Propellants
J. E. Crump,E. W. Price +1 more
TL;DR: In this article, it was found that burning rate is decreased by acoustic pressure and increased by acoustic velocity (double base propellants), the two effects being of comparable magnitude, and the fluctuations in equilibrium pressure during unstable rocket motor and vented vessel firings were readily explainable in terms of the burning-rate effects obtained from the interrupted burning tests.