Numerical investigation of thermoacoustic instability caused by small disturbance in a solid rocket motor

Xu, Guanyu; Liu, Peijin; Ao, Wen; Wang, Zhuopu; Jin, Bingning

doi:10.1016/j.ast.2021.106678

Cited by 13 publications

(2 citation statements)

References 47 publications

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“…The gas flow in the combustion chamber is described using the conservation laws of mass, momentum, and energy. By neglecting gravity, radiation, and chemical reactions, the internal gas flow can be described by the finite volume Reynolds-averaged Navier-Stokes (RANS) governing equations [14,34] as follows.…”

Section: Governing Equations For Flow Fieldmentioning

confidence: 99%

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Wang,

Li,

et al. 2024

Aerospace

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A solid rocket motor (SRM) with a high aspect ratio that performs normally during ground tests may experience instability during flight. To address this issue, this study employs the pulse triggering method and the numerical approach of two-way fluid–structure interaction to investigate the mechanisms behind the SRM instability resulting from distinctions between on-ground and in-flight conditions. The results indicate that the main distinctions between the on-ground and in-flight conditions for SRMs are the strong constraints during the ground test, as well as aerodynamic forces and aerodynamic heating during flight. The strong constraints in the ground test effectively suppress structural vibrations by limiting displacements. In flight conditions, the aerodynamic heating reduces the strength of the SRM casing and aerodynamic forces provide sustained energy input for structural vibrations during flight. The mechanism for the ground/flight differences that induce SRM instability is that the structural natural frequencies are reduced by aerodynamic heating and the first-order acoustic frequency increased by the propellant regression approach reaches the resonance condition. Therefore, an instability factor Φ is proposed to represent the resonance relationship between the structural natural modes and the acoustic mode of SRMs. Furthermore, the closer the frequency of the aerodynamic forces is to the resonance frequency of the acoustic-structure coupling, the more pronounced the SRM instability.

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Section: Governing Equations For Flow Fieldmentioning

confidence: 99%

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Wang,

Li,

et al. 2024

Aerospace

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show abstract

“…It is worth noting that pressure-induced waves of air molecules have a sinusoidal form, which fluctuates back and forth at the average sound pressure and can be measured using the pressure transmitter. Then the fast Fourier transform [21,22] algorithm is applied to analyze the collected data in the frequency domain and obtain the wave frequency and pressure amplitude at the measurement point.…”

Section: Experiments and Simulation Model 21 Cold-flow Experimentsmentioning

confidence: 99%

Investigating the Acoustic Response Characteristics of a Solid Rocket Motor Combustor in High‐Temperature and High‐Pressure Environments

Chen

Zhang

et al. 2022

Propellants Explo Pyrotec

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With the rapid development of aerospace technologies, coupling of pressure oscillations and unstable combustion in solid rocket motors has become a research hotspot in the past few years. In the present study, an experimental system is designed to investigate high-pressure flows subjected to acoustic excitation. Then cold flow experiments and numerical simulations are carried out with different acoustic excitation frequencies, different background pressures, and different ambient temperatures. The pressure oscillation characteristics and the acoustic response characteristics of the combustion chamber in a high-temperature and high-pressure combustion chamber are analyzed. It is found that the frequency of the pressure oscillation inside the combustion chamber and the output excitation frequency of the signal generator are the same. When the excitation frequency is in the range of 50-200 Hz, the sound pressure amplitude corresponding to each test temperature increases with the increase of the frequency. Moreover, when the background pressure is in the range of 0-0.6 MPa, the sound pressure amplitude increases with the increase of the pressure. Meanwhile, there is no clear correlation between the sound pressure amplitude of the combustion chamber and temperature when the chamber temperature is in the range of 293-363 K. The obtained results from the numerical simulation are consistent with the experimental data and the relative error is less than 5.9 %, which verifies the accuracy of the model. The simulated sound pressure amplitude in the combustion chamber at high temperatures and high pressures is a cubic function of pressure and temperature. The present study is expected to provide an innovative way to investigate pressure oscillations and combustion instability of the propellant in the combustion chamber of solid rocket motors at high temperatures and high pressures.

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A novel procedure to determine the effects of debonding on case exposure of solid rocket motors

et al. 2022

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Numerical investigation of thermoacoustic instability caused by small disturbance in a solid rocket motor

Cited by 13 publications

References 47 publications

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Investigating the Acoustic Response Characteristics of a Solid Rocket Motor Combustor in High‐Temperature and High‐Pressure Environments

A novel procedure to determine the effects of debonding on case exposure of solid rocket motors

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