MECHANICS

Experimental investigation and modeling of metallized composite solid propellant combustion with allowance for the size distribution of agglomerates. II. Numerical modeling results

V. A. Poryazov^a, O. G. Glotov^b, A. Yu. Krainov^a, D. A. Krainov<sup>c

a</sup> Tomsk State University, Tomsk, Russian Federation
^b Voevodsky Institute of Chemical Kinetics and Combustion Siberian Branch
^c Tomsk Polytechnic University, Tomsk, Russian Federation

Abstract: A physical and mathematical model with the results of numerical modeling of metallized solid propellant combustion is presented. The physical and chemical processes occurring in the solid phase are determined by the thermal conductivity equation and the oxidant decomposition equation. In the gas phase, the processes are described based on the approaches of multiphase reacting media dynamics proposed by R. I. Nigmatulin. The conditions for the conservation of components' mass and energy are specified on the solid propellant surface. Experimental data obtained by the sampling procedure are used to determine the size distributions of the dispersed phase particles leaving the solid propellant surface during combustion. The calculated burning rate satisfies the experimentally obtained values in the pressure range of 2–9 MPa. The numerical study results confirm the assumption that the dispersion of aluminum particles leaving the propellant surface significantly affects the burning rate of the metallized composite solid propellant. Using experimental data on the dispersion of combustion products, the developed physical and mathematical model enables the prediction of the burning rate of metallized composite solid propellants with satisfactory accuracy.

Keywords: condensed combustion products, aluminum, burning rate.

UDC: 536.46

Received: 05.06.2024
Accepted: April 10, 2025

DOI: 10.17223/19988621/94/14