Study of working process instability in the two-chamber solid-propellant rocket engine

The mechanism of low-frequency acoustic instability generation in the two-chamber tandem solid-propellant rocket engine is studied numerically using the Davydov method (the method of large particles). The calculation results are in a good agreement with the experimental data. The gasodynamic nature (that is essentially nonlinear) of low-frequency acoustic fluctuations of pressure and thrust connected with the structure and pattern of the flow in the rocket engine combustion chamber is corroborated.