Calculation of the ignition stages and steady-state combustion of a metallized solid propellant under laser radiation

The paper presents a physical and mathematical model as well as the results of the calculation of ignition and steady-state combustion of a metallized solid propellant under the action of heat flux. The approach is based on the coupled mathematical model which takes into account the physical and chemical processes in the solid propellant and in the gas phase over the propellant surface. The mass and energy flow conservation equations specify the boundary conditions on the surface of the solid propellant. The equations of heat transfer and decomposition of condensed phase are used below the surface of the propellant. The gas phase over the propellant surface is described by two-velocity and two-temperature model of the reacting flow of propellant decomposition products and their gasification.
The effect of the heat flux capacity, mass fraction and dispersion of the aluminum particles in the composition of solid propellant on the ignition characteristics and development of the steadystate combustion is studied.