Theoretical Modeling and Numerical Study for Thrust- Oscillation Characteristics in Solid Rocket Motors

Zhang, Qiao; Wei, Zhijun; Su, Wanxing; Li, Junwei; Wang, Ningfei

doi:10.2514/1.b34152

Cited by 21 publications

(3 citation statements)

References 22 publications

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“…Despite all of the merits possessed by SRMs, the pressure oscillations that frequently occur in the SRM combustion chamber have always been a major barrier for the research and development of high-performance propulsion rocket systems. These oscillations, commonly observed as the average pressure amplification of the combustion chamber, may cause thrust variations and vibrations of the propellant, disturb the stability of the heat penetration zone on the propellant surface, and even result in the fatal failure of a launching mission [1][2][3][4].…”

Section: Introductionmentioning

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: Introductionmentioning

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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“…Industrial applications cannot entirely rely on experimental research. There are many factors contribute to the oscillations of physical parameters during the working process [9][10][11]. Establishing an accurate physical model of solid rocket motors demands considerable effort and expertise, which makes theoretical research inconvenient for industry purposes.…”

Section: Introductionmentioning

confidence: 99%

Deep learning-based total impulse prediction method in ignition process of solid rocket motor

Yang,

Wang,

Zheng

et al. 2023

International Workshop on Signal Processing and Machine Learning (WSPML 2023)

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“…In the last seventy years, active control of aero acoustic pressure oscillations has been a serious challenge of designers in segmented large solid rocket motors (Zhang et al, 2012), (Ferretti et al, 2011). Literatures have referred to two methods for active control of pressure oscillations include of acoustic excitation using a loudspeaker and secondary injection of a pulsating fluid (Poinsot et al, 1989).…”

Section: Introductionmentioning

confidence: 99%

Theoretical, Numerical and Experimental Investigation of Secondary Injection with a Novel Pyrogenic Pulser

Taherinezhad¹,

Zarepour²

2019

JAFM

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In this paper, a novel pyrogenic pulser was designed both analytically and numerically and evaluated with empirical tests. The motivation of this study was the need for active control of the aero acoustic pressure oscillations by injecting the secondary flow into the solid rocket motor. First, in brief, pyrotechnic and pyrogenic pulsers have been introduced, and then analytical governing equations have been presented in three transient, sinusoidal and Hercules methods. In order to understand the internal pressure of the pulsar and its plume length, the injection flow field has been evaluated using the ANSYS-Fluent software with both − SST and − Realizable models both at ambient and motor pressure. After that, the design and manufacturing of the pulser hardware and the test process have been described. Finally, analytical, numerical and experimental results have been discussed. The results show that there is a good correlation between the transient analysis in theory and the numerical solution by the k-ω SST model and the empirical test data. In addition, pyrogenic pulsers design depends on various parameters of motor and pulser charge performance prediction. The quality of pulser charge bonding to its insulator and erosion of its throat path due to injection have an important role to obtain a desirable pulser mass flow rate and plume length.

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Theoretical Modeling and Numerical Study for Thrust- Oscillation Characteristics in Solid Rocket Motors

Cited by 21 publications

References 22 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

Deep learning-based total impulse prediction method in ignition process of solid rocket motor

Theoretical, Numerical and Experimental Investigation of Secondary Injection with a Novel Pyrogenic Pulser

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