Solid Propellant Combustion Mechanism Studies
Progress rept. no. 19, 1 Jan-31 Mar 1965
PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES
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In the combustion of composite solid rocket propellants based on ammonium perchlorate, the important rate determining processes have generally been presumed to occur within the gas phase flame. Recent results obtained in this laboratory suggest that condensed phase processes could also be important, particularly in low pressure combustion. The present research has been designed to study the nature of the processes involved in propellant gasification in the absence of the complicating effects of the gas phase flame. The experimental method being employed in this study permits the measurement of propellant regression rates in the absence of the gas phase flame. An intense radiant flux from an arc-image furnace is substituted for the conductive heat flux generally associated with the flame. The flame itself is eliminated by working at a vacuum below the propellant combustion limit. Two main questions as to the validity of this method are posed. Can variations in solid absorptivity and reflectivity with particle size cause specious effects of particle size on burning rate. Can the rapid variation of flux within the focal region of an arc-image furnace destroy the significance of the burning rates obtained with such a device. The conclusion is reached that both of these problems can be overcome and the method is valid.
- Combustion and Ignition
- Solid Rocket Propellants