Effects of Grain Geometry on Pulse-Triggered Combustion Instability in Rocket Motors

Golafshani, Mehdi; Farshchi, Mohammad; Ghassemi, Hassan

doi:10.2514/2.5906

Cited by 12 publications

(9 citation statements)

References 10 publications

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“…A linear stable motor can be translated to the nonlinearly unstable when it is triggered by pulse [8,9]. In order to investigate nonlinear combustion instability of rocket motors, pulse excitation technology is employed in various experiments for decades [10][11][12][13]. Except for damping and gain of the combustion chamber, the most important factor is the intensity of pulsed excitation, which determines whether nonlinear combustion instability can be triggered [14].…”

Section: Introductionmentioning

confidence: 99%

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Experimental and theoretical study on characteristics of pulse excitation in T-burners

Yan

Wang

et al. 2017

Acta Astronautica

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Pulse excitation is the key to measure the pressure-coupling response function of composite propellant. It is also a key trigger factor for nonlinear combustion instability. This paper aims at understanding characteristics of pulse excitation in T-burners. Pulse excitation is provided by black powder (BP). D 2 law is used to calculate BP burning properties. Firstly, the experimental pressure history of a pulse excitation is analyzed. Pressure pulse and mean pressure increment are introduced to describe pulse excitation. Secondly, the modified zero-dimension model and one-dimension model of pressure pulse are established based on energy conservation and modification. The results of models indicate that the modified zero-dimensional model can accurately predict the pressure pulse. The modified zero-dimension model demonstrates that the pressure pulse is determined by pulse build-up time threshold, volume coefficient, effective weight fraction of BP, weight of BP et. al. When burning time of BP is larger than the threshold, volume coefficient is equal to 2, and effective weight fraction of BP is less than 1. The pressure pulse is approximately linear correlation with weight and effective weight fraction of BP. Otherwise, volume coefficient is larger than 2, and effective weight fraction of BP is equal to 1. The pressure pulse is approximately linear correlation with volume coefficient and BP weight. Thirdly, a zero-dimensional prediction model of mean pressure is established based on conservations of energy and mass. The prediction models of pressure pulse and mean pressure are validated by T-burner experiments. Finally, effects of BP burning properties on pressure pulse and mean pressure increment are studied. The results show that both pressure pulse and mean pressure increment increase with increasing BP weight, linearly. The pressure pulse is more sensitivity to the variations of burning time of BP. As burning time of BP decreases, the mean pressure increment gradually increases to the maximum, and the pressure pulse can become a very large value.

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Section: Introductionmentioning

confidence: 99%

“…Pressure pulse of pulse excitation determines whether the pressure oscillation in T-burner can be triggered successfully. It also determines the frequency distribution of the pressure oscillation [11]. Mean pressure increment of pulse excitation determines the accuracy of the experimental measurement of pressure-coupled response [18].…”

Section: Introductionmentioning

confidence: 99%

Experimental and theoretical study on characteristics of pulse excitation in T-burners

Yan

Wang

et al. 2017

Acta Astronautica

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“…Such an approach has been derived from the classical non linear mechanics text by Krylov and Bogoliubov [4]. All the above approaches have been supplemented by rigorous analytical modelling by Fletcher [5] and Levine [6], by external ballistic pulsing (Solanki [7]) and the effect of propellant geometry on the combustion stability [8]. Experimentally, the T-burner has been employed by researchers [7], to study the propellant response to incoming pressure oscillations.…”

Section: Introductionmentioning

confidence: 99%

“…external ballistic pulsing [12], rotating valve [13] and magnetic flow meter [14]. Geometric aspects like the effect of propellant geometry on the combustion stability [8] have also been addressed as a follow up for the above methodologies.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Intermittent Oscillations in Composite Propellant

Selvakumaran

Kadiresh

2017

Propellants Explo Pyrotec

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A pressurized window bomb arrangement for AP-HTPB combustion is studied using high speed images to analyze for unsteady combustion, resulting in combustion instability. The base combustion is unsteady and non-stationary. The base filtered heat release rate pattern displays intermittency, seldom observed in prior literature. The intermittency observed is of type 1, and subsequent analysis leads to questions on conventional amplitude spectra as a measure of instability. A novel indicator, the intermittency factor is defined to understand the role of intermittency. It is seen that intermittency is marked by fluctuating intermittency factor values, implying a large deviation in phase values.

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“…In order to study the effects of grain configurations on combustion instability, a series of small test motor firings with various grain configurations was used [10]. Their tests showed that combination of STAR-circular perforation configuration offers a great stability margin during entire motor firing.…”

Section: Introductionmentioning

confidence: 99%

Simulation and Study of the Effect of Pressure Oscillations on Linear Combustion Instability in a Double Base Solid Rocket Motor

Seifollahzadeh¹,

Aminian²

2014

J Chem Eng Process Technol

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The combustion instability remained as a problem during solid rocket motors progress. In this study, combustion instability of a double base solid rocket motor was estimated wherein acoustical and erosive burning was considered. The ballistic parameters of the solid rocket motor were presented and the results were compared with simulations, which show a good agreement. The result shows that specific impulse of the solid propellant rocket motor was obtained 211 s and the maximum pressure of the combustion chamber reaches 13.8 MPa. Combustion instability analysis indicates that the motor became unstable after 0.5 s.

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Effects of Grain Geometry on Pulse-Triggered Combustion Instability in Rocket Motors

Cited by 12 publications

References 10 publications

Experimental and theoretical study on characteristics of pulse excitation in T-burners

Experimental and theoretical study on characteristics of pulse excitation in T-burners

Investigation of Intermittent Oscillations in Composite Propellant

Simulation and Study of the Effect of Pressure Oscillations on Linear Combustion Instability in a Double Base Solid Rocket Motor

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