An Investigation of the Effect of Acceleration on the Burning Rate of Composite Propellants PDF Download
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Languages : en
Pages : 0
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Book Description
The average burning rates of composite solid rocket propellant were measured in acceleration fields up to 2000 times the standard acceleration of gravity. The acceleration vector was perpendicular to and into the burning surface. Propellant strands were burned in a combustion bomb mounted on a centrifuge, and surge tanks were employed to ensure essentially constant pressure burning at 500, 1000, and 1500 psia. The burning rates of both aluminized and non-aluminized composite propellants were found to depend on acceleration. The effect of acceleration on burning rate was found to depend on the burning rate of the propellant without acceleration, aluminum mass loading, and aluminum mass median particle size. The relative burning rate increase was found to be greater for slow burning propellant than for faster burning propellants. The experimental results are compared to the analytical models proposed by Crowe for aluminized propellants and by Glick for non-aluminized propellants. The results indicate that these models do not adequately predict the observed relative burning rate increase with acceleration, and hence, that more complex modeling will be required to explain the observed acceleration effect. (Author).
Author:
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Category :
Languages : en
Pages : 0
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Book Description
The average burning rates of composite solid rocket propellant were measured in acceleration fields up to 2000 times the standard acceleration of gravity. The acceleration vector was perpendicular to and into the burning surface. Propellant strands were burned in a combustion bomb mounted on a centrifuge, and surge tanks were employed to ensure essentially constant pressure burning at 500, 1000, and 1500 psia. The burning rates of both aluminized and non-aluminized composite propellants were found to depend on acceleration. The effect of acceleration on burning rate was found to depend on the burning rate of the propellant without acceleration, aluminum mass loading, and aluminum mass median particle size. The relative burning rate increase was found to be greater for slow burning propellant than for faster burning propellants. The experimental results are compared to the analytical models proposed by Crowe for aluminized propellants and by Glick for non-aluminized propellants. The results indicate that these models do not adequately predict the observed relative burning rate increase with acceleration, and hence, that more complex modeling will be required to explain the observed acceleration effect. (Author).
Author: G. Burton Northam
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 36
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Author: James Bruce Anderson
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Category : Aeronautics
Languages : en
Pages : 208
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Book Description
The average burning rates of composite solid rocket propellant were measured in acceleration fields up to 2000 times the standard acceleration of gravity. The acceleration vector was perpendicular to and into the burning surface. Propellant strands were burned in a combustion bomb mounted on a centrifuge, and surge tanks were employed to ensure essentially constant pressure burning at 500, 1000, and 1500 psia. The burning rates of both aluminized and non-aluminized composite propellants were found to depend on acceleration. The effect of acceleration on burning rate was found to depend on the burning rate of the propellant without acceleration, aluminum mass loading, and aluminum mass median particle size. The relative burning rate increase was found to be greater for slow burning propellant than for faster burning propellants. The experimental results are compared to the analytical models proposed by Crowe for aluminized propellants and by Glick for non-aluminized propellants. The results indicate that these models do not adequately predict the observed relative burning rate increase with acceleration, and hence, that more complex modeling will be required to explain the observed acceleration effect. (Author).
Author: David W. Netzer
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Category :
Languages : en
Pages : 14
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Book Description
This report discusses four experimental investigations: (1) The effect of propellant strand size on the experimentally measured burning rate at various acceleration levels; (2) an investigation of the effect of initial propellant temperature on acceleration induced burning rate augmentation; (3) an investigation of the effect of nominal burning rate on acceleration induced burning rate augmentation; and (4) a photographic investigation of augmented burning rate. Significance of the investigation and a brief review of the literature are presented.
Author: Kennerly Wendell Funk
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 102
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Author: David W. Netzer
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Category :
Languages : en
Pages : 109
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Book Description
The acceleration sensitivity of aluminized and nonmetallized composite and double-base propellants were investigated. A review of previous experimental findings and current analytical models was also conducted. An investigation was conducted to determine the cause(s) for the differences in burning rate augmentation data reported by various investigators. Strand length (burn time) was found to be the dominant factor. Lead and copper additives commonly found in double-base propellants were found to decrease the burning rate with increasing acceleration. Burning rate instability was also obtained at high accelerations. The addition of aluminum increased the burning rate at any given acceleration. (Author).
Author: G. Burton Northam
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 50
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Author: G. Burton Northam
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Category :
Languages : en
Pages : 44
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Author: Edward John Sturm
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Category :
Languages : en
Pages : 225
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The average burning rates of a series of composite solid propellants were measured in acceleration fields up to 1000 G using a combustion bomb mounted on a centrifuge. The propellants were burned at constant pressures of 500, 1000, and 1500 psia. Specially prepared motors allowed the study of the effect of simultaneous erosive and acceleration induced burning rate increases. The burning rates of both the non-metallized and the majority of the metallized propellants were found to depend on acceleration. The effect of acceleration was found to depend on the basic burning rates of the propellants and the aluminum and oxidizer particle sizes and weight percentages. The burning rates of two very fast burning rate propellants were found to be essentially independent of acceleration. The erosion sensitivity of a propellant was found to decrease with increasing acceleration. A model was developed which successfully correlates the experimental results obtained for the non-metallized propellants. The experimental results for the metallized propellants could not be correlated by either of two models proposed by other investigators. This result indicates that a more complex model is required to explain the observed acceleration effects for metallized propellants. (Author).
Author: G. Burton Northam
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 68
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Book Description
Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight percent aluminum, were calculated from the pressure histories of a test motor with 96.77 sq cm of burning area and a 5.08-cm-thick propellant web. Additional acceleration tests were conducted with reduced propellant web thicknesses of 3.81, 2.54, and 1.27 cm. The metallic residue collected from the various web thickness tests was characterized by weight and shape and correlated with the instantaneous burning rate measurements. Rapid depressurization extinction tests were conducted in order that surface pitting characteristics due to localized increased burning rate could be correlated with the residue analysis and the instantaneous burning rate data. The acceleration-induced burning rate augmentation was strongly dependent on propellant distance burned, or burning time, and thus was transient in nature. The results from the extinction tests and the residue analyses indicate that the transient rate augmentation was highly dependent on local enhancement of the combustion zone heat feedback to the surface by the growth of molten residue particles on or just above the burning surface. The size, shape, and number density of molten residue particles, rather than the total residue weight, determined the acceleration-induced burning rate augmentation.
