Study of solid propellant ignition by a hot gas stream

The process of fast ignition of double-base solid propellants (ignition time 0.6–40 msec) is studied in a model rocket chamber by means of fine thermocouples that are located on the surface being ignited and in the igniting gas stream under rapidly varying external conditions. The basic parameters of the process (propellant surface temperature, gas-propellant heat transfer coefficient, heat flux from the gas to the propellant, and the heat content and the heat release in the propellant) are obtained as functions of time. Three ignition regimes are found: fast, normal, and delayed. We discuss briefly the nature of the transition to steady-state combustion for the obtained regimes. The directions of future studies are noted.