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Abstract
The classical wave-model for the laminar, adiabatic combustion of a homogeneous, pre-mixed, gaseous flame is expanded and applied to the heterogeneous combustion of a pure solid propellant. The conservation equations for the gas, solid and Gibbsian surface states are solved to obtain an explicit expression for the steady-slate burning rate. The major problem of predicting the magnitude of the gas-phase heating rate, is resolved by relating the heating rate to the burning velocity of a simulated flame above the solid surface. The theory is readily modified to include energy loss corrections for the non-adiabatic processes of conduction, convection and radiation to the surroundings. The theory predicts a magnitude for the burning rate of pure ammonium perchlorate that is in good agreement with experiment
New data are presented for the non-adiabatic, laser-induced combustion of ammonium perchlorate. The theory is in good agreement with these measurements and those of previous investigators
The difficulties of extending such laminar theories to composite propellants are considered. Quantitative criteria are presented which justify the steady-state theory only for a limiting case of composite propellants.