Analysis of Segmented Combustion Instability Phenomenon in Solid Rocket Motor

WANG Zhixin; SUN Xiaojiao; LE Hao; LI Shasha; LIU Xiaochen

doi:10.15892/j.cnki.djzdxb.2025.01.014

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 1: 101 - 107

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.01.014

Analysis of Segmented Combustion Instability Phenomenon in Solid Rocket Motor

WANG Zhixin ,
SUN Xiaojiao ,
LE Hao ,
LI Shasha ,
LIU Xiaochen

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Shanghai Space propulsion Technology Research Institute,Shanghai 201109,China

Received date: 2024-05-25

Online published: 2025-03-12

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Abstract

For the segmented combustion instability phenomenon of slender solid rocket motors in the ground test, it can obtained the distribution range of pressure oscillation frequency in the combustion chamber by mean of acoustic cavity frequency analysis, analyzing the main factors of two-stage combustion instability from a perspective of acoustic-vortex coupling and propellant combustion response. Then through comparison experiment, comparing the combustion instability of the motor with the same grain configuration and different propellant formulations and combiningewith the acoustic cavity mode of the combustion chamber at the initial, middle and end time and the flow field vortex structure computation of the combustion chamber and the pressure coupled response function test results of the T-burner, the conclusion is that the combustion instability phenomenon at the initial stage of the motor operation is due to the fact that the vortex shedding frequency caused by the grain configuration is close to the frequency of the acoustic field of the chamber to generate coupling gain and induce the pressure oscillation. At the end of the operation of the motor, the combustion instability frequency is different from the initial frequency range, and there are frequency multiplication characteristics, the instability is caused by the combustion response of the propellant. The analysis unfolds from the two-stage combustion instability in the ground test andprovids a reference to optimize solid rocket design and effective avoidance of such problems in engineering design.

Key words： solid rocket motor; segmented combustion instability; acoustic cavity frequency analysis; pressure-coupled response function

Cite this article

WANG Zhixin , SUN Xiaojiao , LE Hao , LI Shasha , LIU Xiaochen . Analysis of Segmented Combustion Instability Phenomenon in Solid Rocket Motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(1) : 101 -107 . DOI: 10.15892/j.cnki.djzdxb.2025.01.014

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