Analysis of multidimensional and two-phase flows in solid rocket motors

Abstract

A physicomathema tical model describing the processes in the combustion chamber of solid rocket motors (SRMs) is suggested. The model can be used in practical calculations of the parameters of real motors with solid-propellant charges of complex geometry. The model allows the description of two-phase flows (from averaged zero dimensional to three dimensional) for the complete operation cycle of SRMs, including transition to steady-state operating conditions and pressure drop accompanying the propellant burnout. Equations obtained can readily be employed in designing computer codes. Methods for the solution of these equations are discussed. Results of studying the gasdynamics parameters of internal flows are reported. Calculated values are compared with experimental data obtained for a modeled gas flow turning from the head-end to the charge channel. A three-dimensional calculation of flow parameters in a slotted-tube charge of a large-size motor is illustrated by distribution patterns for pressure and velocity. The influence of the redistribution of aluminum in a solidpropellant charge on the combustion efficiency coefficient of the metal, specific impulse, and in-chamber losses is analyzed.