Investigation of acoustic instability of the operation process in solid-propellant rocket motors with the use of a pulsed T-burner

Provision of stability of the operation process in solid-propellant rocket motors is an integral aspect of engine design and operation. The present paper describes a numerical and experimental method of determining the linear stability of the operation process in a solid rocket motor with an axisymmetric combustor. The method is based on solving a linearized system of equations that describe the dynamics of solid propellant combustion products in the frequency domain. The values of acoustic conductivity of the solid-propellant combustion region obtained in a pulse T-burner are used as the boundary conditions. Verification of the method is performed on the basis of numerical and experimental data obtained for six model engines. Results of stability computations for the operation process in an engine with a large aspect ratio operating on a metallized propellant are reported.