Abstract: | Comprehensive numerical modeling of the processes occurring in the combustion chamber of a solid propellant rocket engine
during the stabilization of the design operation mode is performed. The self-consistent problem considered includes nonstationary
operation of an ignition device, warmup and ignition of a solid propellant charge followed by its nonstationary burning, nonstationary
threephase homogeneous-heterogeneous flow of the combustion products in the combustion chamber, in the nozzle, and behind
the engine nozzle unit, engine depressurization, and nozzle unit plug blowing-out. The results of the calculations are presented. |