An Elementary Calculation for the Burning Rate of Composite Solid Propellants

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Abstract
A calculation of the burning rate for a composite solid propellant is based on a model in which the distribution of combustion in the gas phase is specified. The formulation of the problem can accommodate an arbitrary distribution, but only the simplest case of uniform combustion is treated here. An inverse numerical computation is carried out, as the magnitude of the reaction rate, and its dependence on pressure, are calculated for several specified burning rates. Simultaneously, flame stand-off distances and thicknesses are determined as part of the solution. The numerical results for those characteristics of the flame appear to be comparable to observed values. However, the principal value of this treatment of the problem is due to the ease with which one can study and understand the influence of the various physical properties and combustion characteristics.