Large-Eddy Simulation of Vortex Shedding and Pressure Oscillations in Solid Rocket Motors

Bernardini, Matteo; Cimini, Matteo; Stella, F.; Cavallini, Enrico; Mascio, Andrea Di; Neri, Agostino; Martelli, Emanuele

doi:10.2514/1.j058866

Cited by 14 publications

(3 citation statements)

References 42 publications

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“…Furthermore, this level of detail is not relevant to fulfill the purpose of obtaining a suitable skirt substitution with CFRP materials. In addition, the igniter at the SRM head end is not considered [ 30 ]. The computational domain is a structured grid

for a total number of 280,000 cells.…”

Section: Test Case—model Definitionmentioning

confidence: 99%

A Numerical Study on Carbon-Fiber-Reinforced Composite Cylindrical Skirts for Solid Propeller Rockets

2023

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A solid rocket motor (SRM) is a rocket engine that uses a fuel/oxidizer mixture in a solid state; the most commonly employed propellants are Hydroxyl-Terminated Polybutadiene (HTPB) as the fuel and ammonium/potassium perchlorate as the oxidizer. To increase the flight range of this kind of vehicle, the weight has to be reduced as much as possible. A possible element that can be worked on is the coating of the combustion chamber: the skirt. The aim of this paper is to investigate the behavior of a cylindrical skirt subjected to internal pressure load and axial thrust and to compare the performance of a skirt made of a standard steel for aeronautics purposes with a carbon-fiber-reinforced composite skirt. The motor test case is taken from the ONERA C1xb and the flowfield is simulated with an axisymmetric k-ω turbulence model. The carbon-fiber-reinforced composite skirt is a cylindrical shell with a symmetric and balanced layup [90/0/45/−45]s. To check composite layer integrity, Hashin’s failure criteria were adopted while linearized buckling methods were used to assess the buckling behavior of the skirt. The composite layup was modeled by adopting the classical laminate theory.

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for a total number of 280,000 cells.…”

Section: Test Case—model Definitionmentioning

confidence: 99%

A Numerical Study on Carbon-Fiber-Reinforced Composite Cylindrical Skirts for Solid Propeller Rockets

2023

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“…According to these studies, there are many driving and damping factors that together determine the stability of a motor. The primary driving factors leading to an increase in fluid flow disturbance energy and thereby causing instability in the motor are pressure-coupled response [11] on the propellant surface, the velocity-coupled response [12], the vortexacoustic coupling [13,14], etc., whereas the main damping factors include the nozzle [15] and particles [16], etc., which tend to dissipate the energy causing perturbations to the flow, thereby exerting a stabilizing influence on a motor.…”

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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“…Experimental research serves as a foundation to test and guide the establishment of theoretical models [2][3][4]. Theoretical research comprises physical model simulations and numerical analysis, which is based on experimental data and basic theory [5][6][7][8]. However, low fault tolerance rate, high cost, drastic changes and unstable of work process have become the biggest obstacles for experiment research.…”

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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Large-Eddy Simulation of Vortex Shedding and Pressure Oscillations in Solid Rocket Motors

Cited by 14 publications

References 42 publications

A Numerical Study on Carbon-Fiber-Reinforced Composite Cylindrical Skirts for Solid Propeller Rockets

A Numerical Study on Carbon-Fiber-Reinforced Composite Cylindrical Skirts for Solid Propeller Rockets

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

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