Temperature and Pressure Sensitivities of Burning Wave Parameters of Nitramine-Containing Propellants and HMX

Abstract

Burning rate and burning surface temperatures have been obtained experimentally for modern double-base propellants containing nitramine additives and for HMX. Temperature sensitivities of burning wave parameters were estimated from the experimental data measured at pressures of 20 and 100 atm and at sample temperatures of i 80, +20, +100 C. Evaluation of standard deviations of the estimations shows that smoothing procedures for dependencies of burning wave parameters on pressure and temperature are necessary to obtain correct values of thesensitivities. Calculations ofthecriteria forstable combustion show that Novozhilov’ s [Novozhilov, B. V., “ Nonstationary Combustion of Solid Rocket Fuels,” Nauka, Moscow, 1973 (Translation AFSC FTD-MD-24-317-74) (in Russian) and Novozhilov, B. V., “ Theory of Nonsteady Burning and Combustion Stability of Solid Propellants by Zel’ dovich‐ Novozhilov Method,” Nonsteady Burning and Combustion Stability of Solid Propellants , edited by L. DeLuca, E.W. Price,and M. Summere eld, Vol. 143,Progressin Astronauticsand Aeronautics,AIAA,Washington, DC, 1992, Chap. 15, pp. 601‐ 641] criterion correctly predicts regimes of stable combustion of the propellants and HMX. An analysis of burned surface irregularities of the propellants cone rms one-dimensional character of the combustion under the investigated conditions.