A Study of Flame Spreading and Combustion Processes in Solid Propellant Cracks PDF Download
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Author: Mridul Kumar
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 196
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Book Description
Author: Mridul Kumar
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 196
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 100
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Book Description
This report presents results of a study of combustion processes in solid propellant cracks. As might be expected, under moderate chamber pressurization rates (10,000 atm/s), the theoretical predictions, as well as the experimental observations, indicate that the ignition front propagates from the entrance of the crack to the tip. However, under rapid chamber pressurization rates (100,000 atm/s or higher), the tip region of the crack was observed to ignite before the arrival of the convective ignition front. (Ignition is defined here as the onset of emission of luminous light from the propellant surface with some material loss. A theoretical model has been developed to explain the tip ignition phenomena. The model considers: a one-dimensional transient heat conduction equation for the solid phase; and one-dimensional, unsteady mass and energy conservation equations for the gas phase near the crack tip. Both experimental and theoretical results indicate that the ignition delay time decreases as the pressurization rate is increased.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
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Book Description
A one-dimensional theoretical model, incorporating the Noble-Abel dense gas law, has been developed to describe the transient model combustion phenomena inside a propellant crack. The theoretical model can be used to predict wave phenomena, heat transfer from the gas to the propellant surface and associated thermal penetration, flame propagation, and resultant pressurization at various locations along the propellant cavity. Calculations made with the current theoretical model revealed that the internal pressurization rate, pressure gradient, and flame velocity in propellant cracks (for which gases can penetrate) decrease as: the gap width increases, the rocket chamber pressurization rate decreases, and the propellant gasification temperature increases. Additionally, the predicted flame spreading was found to decelerate in a region near the crack tip; this phenomena has been experimentally observed by others.
Author: K. K. Kuo
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Martin Summerfield
Publisher: AIAA
ISBN: 9781600863967
Category : Solid propellants
Languages : en
Pages : 922
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Author: Yeu-Cherng Lu
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 37
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Book Description
Selective calculations have been made for burning in cracks as it pertains to solid rocket motor propellants. The possibility of obtaining pressures high enough to cause a shock-to-detonation transition (sdt) in propellant grains is examined. variables affecting the crack combustion process which were selected for study are: crack shape; location; surface roughness; propellant deformation; ignition criterion; and burning rate. The variables are evaluated and ordered in groups of relative importance. results suggest that SDT should not occur in propellants unless the granulation of the grain is severe enough to provide large burning surface area.
Author: J. Mantzaras
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Book Description
Crack propagation in burning solid propellants and explosives can affect the performance of a rocket motor by increasing both the burning surface area and local pressurization rates. This may sometimes lead to deflagration-to-detonation transition (DDT) or detonation due to some unresolved mechanisms (XDT). In order to obtain direct evidence of structural damage of the propellant sample during crack propagation and branching, an interrupted burning experiment has been designed, constructed, and tested. Sample recovered from a preliminary test firing showed rough surface structure and several macrocracks in directions from the initial crack orientation. The propellant sample is believed to undergo significant cracking and branching before the extinction. This is supported by the experimental evidence of rough and cracked surfaces of the recovered sample, source-flow pattern observed from high-speed movie films, and extremely rapid pressurization of the source-flow region beyond the initial crack tip due to the fast burning of damaged propellant sample. (Author).
Author: Jeffrey A. Nimis
Publisher:
ISBN:
Category :
Languages : en
Pages : 70
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Book Description
The importance of crack propagation in solid rocket motors is widely recognized. However, the processes of crack propagation and branching in burning solid propellants are not as yet well understood. These processes could be instrumental in creating large specific surface areas for burning causing rocket motor failure. Key factors influencing the crack combustion, propagation and branching process considered in the dimensional analysis include chamber pressurization rate, initial crack length, initial temperature, sample geometry, and mechanical and thermal properties of the solid propellant. (jes).
Author: Yeu-Cherng Lu
Publisher:
ISBN:
Category :
Languages : en
Pages :
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