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Burning Rates Of Solid Composite Propellants At Pressures Up To 20000 Psig
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Book Synopsis BURNING RATES OF SOLID COMPOSITE PROPELLANTS AT PRESSURES UP TO 20,000 PSIG. by :
Download or read book BURNING RATES OF SOLID COMPOSITE PROPELLANTS AT PRESSURES UP TO 20,000 PSIG. written by and published by . This book was released on 1966 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: Strand burning rates of ammonium perchlorate-containing composite propellants having plastisol-nitrocellulose, carboxyl-terminated-polybutadiene, and NF binders have been measured to 20,000 psig. For the first two types and probably the NF type the major influences on burning-rate transition are those resulting from variations in binder type and in oxidizer concentration and particle size; the presence of aluminum or burning-rate promoters has little effect on the pressure-dependence of the burning rate at high pressure. The pressure exponents of plastisol-nitrocellulose formulations reach constant values of 1.0 to 1.3 at about 6000 psi, with little dependence on AP particle size. Carboxyl-terminated-polybutadiene formulations examined give indexes from 0.3 at 2000 psi to 2 up to 10,000 psi, with appreciable AP-particle-size dependence; above 10,000 psi the index decreases to 0.9 and appears to be insensitive to oxidizer size. A proposed model suggests an alteration in the volatilization processes which ensue from differences in pressure-dependence of the respective binder and oxidizer release rates.
Book Synopsis INVESTIGATION OF THE MECHANISM OF SOLID PROPELLANT BURN RATE. by :
Download or read book INVESTIGATION OF THE MECHANISM OF SOLID PROPELLANT BURN RATE. written by and published by . This book was released on 1967 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: The mechanism by which iron compounds catalyze the burning rate of solid composite propellants is reported. A series of experiments were conducted to define the efficacy of iron compounds on burning rate. Experiments performed under Phases I and II studies, which were designed to study the interaction, if any, between catalysts and oxidizer and binder indicate the following conclusions. Thermal decomposition of ammonium perchlorate under pressure occurs in a single-phase step instead of the three phases observed at atmospheric pressure. The singe-phase decomposition step of ammonium perchlorate is shifted to lower temperature in the presence of iron oxide. The degree of this shift is dependent upon Fe2O3 concentration. The autoignition temperature of composite propellant decreases with increasing pressure. The rate of decomposition of anhydrous perchloric acid on varied surfaces seems to be a strong function of exposed specific surface of the catalyst and not overly dependent upon the chemical nature of the material. Iron compounds such as Fe2O3, ferrocene and butyl ferrocene do not facilitate the pyrolysis of polybutadiene polymers or gumstocks. A mechanism for catalysis by iron compounds is presented and mathematical expressions relating the variables involved have been formulated.
Book Synopsis Nonsteady Burning and Combustion Stability of Solid Propellants by : Martin Summerfield
Download or read book Nonsteady Burning and Combustion Stability of Solid Propellants written by Martin Summerfield and published by AIAA. This book was released on 1992 with total page 922 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Effect of Aluminum Size and Loading on the Burning Rate of Solid Propellants Under Acceleration by : G. Burton Northam
Download or read book Experimental Investigation of the Effect of Aluminum Size and Loading on the Burning Rate of Solid Propellants Under Acceleration written by G. Burton Northam and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Effect of Acceleration on the Burning Rate of Composite Propellants by :
Download or read book An Investigation of the Effect of Acceleration on the Burning Rate of Composite Propellants written by and published by . This book was released on 1966 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis An Investigation of the Effect of Acceleration on the Burning Rate of Composite Propellants by : James Bruce Anderson
Download or read book An Investigation of the Effect of Acceleration on the Burning Rate of Composite Propellants written by James Bruce Anderson and published by . This book was released on 1966 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis An Investigation of Solid Propellant Combustion in Standard and High Acceleration Environments by :
Download or read book An Investigation of Solid Propellant Combustion in Standard and High Acceleration Environments written by and published by . This book was released on 1974 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Nonmetallized double-base and composite propellant, metallized composite propellant, and ammonium perchlorate (AP)/binder sandwich combustion were studied in standard and high acceleration environments. Experimental techniques used were high speed motion pictures, tow-color schlieren, laser schlieren, and centrifuge mounted combustion bombs. It was found for double-base propellant that the temperature increased continuously from the surface into the visible flame. Acceleration induced burning rate augmentation occurred and resulted in elimination of the visible flame. Acceleration apparently modified the surface or subsurface zones. AP/binder sandwich combustion was also found to be acceleration sensitive with binder flow-AP interactions proposed as the mechanism. Composite propellants burned with local diffusion flames to pressures as slow as 100 psi. A comparison is made between AP/binder sandwich combustion and propellant combustion. (Author).
Book Synopsis The Dependence of Linear Burning Rate Upon Pressure for Ammonium Perchlorate Polyester Resin Composite Solid Propellant by : Maurice John Webb
Download or read book The Dependence of Linear Burning Rate Upon Pressure for Ammonium Perchlorate Polyester Resin Composite Solid Propellant written by Maurice John Webb and published by . This book was released on 1958 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1967 with total page 866 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Propellant Composition Variables on Accleration-induced Burning-rate Augmentation of Solid Propellants by : G. Burton Northam
Download or read book Effects of Propellant Composition Variables on Accleration-induced Burning-rate Augmentation of Solid Propellants written by G. Burton Northam and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Study of the Burning Rates of Composite Solid Propellants in Acceleration Fields by : Edward John Sturm
Download or read book A Study of the Burning Rates of Composite Solid Propellants in Acceleration Fields written by Edward John Sturm and published by . This book was released on 1968 with total page 225 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Propellants and Explosives by : Naminosuke Kubota
Download or read book Propellants and Explosives written by Naminosuke Kubota and published by John Wiley & Sons. This book was released on 2015-04-23 with total page 560 pages. Available in PDF, EPUB and Kindle. Book excerpt: This third edition of the classic on the thermochemical aspects of the combustion of propellants and explosives is completely revised and updated and now includes a section on green propellants and offers an up-to-date view of the thermochemical aspects of combustion and corresponding applications. Clearly structured, the first half of the book presents an introduction to pyrodynamics, describing fundamental aspects of the combustion of energetic materials, while the second part highlights applications of energetic materials, such as propellants, explosives and pyrolants, with a focus on the phenomena occurring in rocket motors. Finally, an appendix gives a brief overview of the fundamentals of aerodynamics and heat transfer, which is a prerequisite for the study of pyrodynamics. A detailed reference for readers interested in rocketry or explosives technology.
Book Synopsis An Investigation of the Steady-State Burning of Ammonium Perchlorate Composite Solid Propellants by : Job S. Ebenezer
Download or read book An Investigation of the Steady-State Burning of Ammonium Perchlorate Composite Solid Propellants written by Job S. Ebenezer and published by . This book was released on 1973 with total page 143 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new, comprehensive steady-state model describing the burning of non-metalized, unimodal ammonium perchlorate (AP)-polymeric composite solid propellant has been developed and shown to yield better results than previous models. This new model incorporates a near-surface AP decomposition flame perturbed by fuel vapor diffusion (after Chaiken) followed by a granular diffusion flame (after Summerfield), and is termed the 'modified granular diffusion flame' (MGDF) model. The MGDF model permits numerical prediction of the influence of pressure, AP particle size, mixture ratio and propellant initial temperature on propellant burning rate. While the new model has proven notably successful, evaluation of the capabilities of it and other models is constrained by the limited existing data base. (Modified author abstract).
Book Synopsis Some Research Problems in the Steady-State Burning of Composite Solid Propellants by : D. W. Blair
Download or read book Some Research Problems in the Steady-State Burning of Composite Solid Propellants written by D. W. Blair and published by . This book was released on 1960 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper outlines a number of basic problems in the theory of steady-state combustion of solid propellants, particularly of the ammonium perchlorate composite type. It represents an extension of the earlier research at Princeton that led to a theoretical burning rate law for composite propellants that was based on the concept of granular diffusion flame. This paper is in the nature of a progress report in which the new experimental approaches are described, and some puzzling difficulties are analyzed. Specifically, the experiments deal with three topics: refinement of methods for measuring burning rate; the role of radiative energy transfer in the burning process; and the connection between oxidizer particle size and the b parameter in the above-mentioned theoretical burning rate law.
Book Synopsis Study of Solid Propellant Combustion and Aluminum Particles at High Pressure by : Alexander Hillstrom
Download or read book Study of Solid Propellant Combustion and Aluminum Particles at High Pressure written by Alexander Hillstrom and published by . This book was released on 2023 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Ammonium perchlorate's burning rate as a function of pressure has an exponent break around 4000 psi where the pressure exponent becomes greater than 1. This causes AP to be highly sensitive to pressure fluctuations that can damage or destroy ammonium perchlorate composite propellant-based solid rocket motors. Studies conducted on AP at these high pressure are few and there is a lack of direct qualitative data due to the challenges posed by the high-pressure environment and optical window structural limitations. This has left the cause exponent break mechanism unknown and difficult to study. The High-Pressure Combustion Lab has built an Ultra-High Pressure Optical Chamber (UHPOC) that allows for optical measurements at these higher pressure regimes. Testing visual measurement techniques using the UHPOC and a telescope zoom lens to take detailed images of the propellant surface during the burn was conducted. Non-aluminized propellant and aluminized propellant samples were tested to observe the mechanisms of aluminum particle combustion in a propellant at high pressures and the behavior of the propellant past the exponent break region. \par At atmospheric, detailed high-speed images on the propellant surface were obtained using a high-powered lamp to light the surface brighter than the flame. At higher pressures, however, the luminosity of the flame was significantly greater than the lamp, creating shadow images of the propellant. Binder agglomerates were observed coming off the surface which increased in size and magnitude as the pressure increased. This is attributed to AP decomposition becoming the dominant burning rate mechanism which burned faster than the surrounding binder as has been observed from previous studies and numerical models. This leaves the binder only partially pyrolyzed, forming the agglomerates which detached from the surface. Aluminum particles were found to ignite at all pressures with the binder agglomerating the same amount in both aluminized and non-aluminized samples. Atmospheric tests show aluminum particles with detached flames and high-pressure tests show aluminum particles with surface flames.
Book Synopsis Effects of Normal Acceleration on Transient Burning-rate Augmentation of an Aluminized Solid Propellant by : G. Burton Northam
Download or read book Effects of Normal Acceleration on Transient Burning-rate Augmentation of an Aluminized Solid Propellant written by G. Burton Northam and published by . This book was released on 1972 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis An Analytical and Experimental Investigation of the Erosive Burning of Composite Propellants by : Merrill K. King
Download or read book An Analytical and Experimental Investigation of the Erosive Burning of Composite Propellants written by Merrill K. King and published by . This book was released on 1977 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Augmentation of solid propellant burning rate often occurs in the presence of strong product gas flow across the burning surface: This phenomenon is referred to as erosive burning. Increasing use of motors with low port-to-throat area ratios (including nozzleless motors) is leading to increased occurrence and severity of erosive burning. A first generation model based upon bending of columnar diffusion flames by a crossflow, permitting prediction of the effect of high-velocity crossflow on the burning rate of a composite propellant given only the zero-crossflow burning rate characteristics, is briefly summarized and compared with data. A second generation model (currently under development) which does not require even zero-crossflow burning rate data, using only composition and particle size as input, is outlined. In addition, a test device permitting extensive characterization of burning rate-pressure-crossflow velocity relationships for various propellants with direct continuous measurement of instantaneous burning rate by high-speed cinematography is described, and results of a series of tests with four propellants are presented. These tests indicate that the first generation composite propellant erosive burning model has reasonable good predictive capability, particularly in the higher pressure region where the propellant combustion is dominated by the propellant heterogeneity.
