Influence of a flight overload on instability of working process in the combustion chamber of the solid-fuel rocket motor

For the first time direct numerical modeling (employing large particles method) is carried out for the low-frequency acoustic instability in SFRM with account of flight overload. As basic physicochemical model was used the complete non-stationary system of vortex differential gas dynamic equations for heterogeneous medium (gas + solid particles) written in the divergent form. The model accounts gravity field of the gravitation force at accelerated motion of a rocket. The flow processes in combustion chamber and SFRM nozzle were described using multiphase heterogeneous mechanics approach. The calculation results, which are in good agreement with the test data, confirm the previous conclusions about hydrodynamic strongly nonlinear nature of low-frequency acoustic pressure oscillations associated with the structure and character of flow in combustion chamber.