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Investigation of Acoustic Instability in Solid-Propellant Rocket Motors with the Use of a Pulsed T-Burner

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Combustion, Explosion, and Shock Waves Aims and scope

Abstract

Provision of stability of the operation process in solid-propellant rocket motors is an integral aspect of motor 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 admittance 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 motors. Results of stability computations for the operation process in a motor with a large aspect ratio operating on a metallized propellant are reported.

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  1. Keldysh Research Center, 125438, Moscow, Russia

    A. A. Kuroedov & P. A. Semenov

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  1. A. A. Kuroedov
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  2. P. A. Semenov
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Correspondence to A. A. Kuroedov or P. A. Semenov.

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Translated from Fizika Goreniya i Vzryva, 2021, Vol. 57, No. 4, pp. 57-68.https://doi.org/10.15372/FGV20210406.

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Kuroedov, A.A., Semenov, P.A. Investigation of Acoustic Instability in Solid-Propellant Rocket Motors with the Use of a Pulsed T-Burner. Combust Explos Shock Waves 57, 433–443 (2021). https://doi.org/10.1134/S0010508221040067

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