The low pressure deflagration limit of controllable solid rocket propellants was experimentally investigated using low pressure combustion chambers and micro video recorders. The deflagration limit is affected by the specimen size, and this scale effect is explained by heat losses from the burning propellant to the surroundings. The effect of compositional variables of the propellant on subatmospheric combustion and the deflagration limit were studied. The variables were oxidizer blend ratio, binder types, oxidizer-fuel mixture ratio, aluminum content, mean particle diameter of the oxidizers and the size of aluminum powders. (Author)
Low-Pressure Deflagration Limit of Controllable Solid Rocket Propellants
1973
17 pages
Report
No indication
English
Control of pressure deflagration limits of composite solid propellants
Engineering Index Backfile | 1967
|Online Contents | 1996
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