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| Author | : Martin Summerfield |
| Publisher | : AIAA |
| Total Pages | : 922 |
| Release | : 1992 |
| Genre | : Solid propellants |
| ISBN | : 9781600863967 |
| Author | : N. S. Cohen |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1984 |
| Genre | : |
| ISBN | : |
Analytical models were developed for the linearized pressure-coupled and velocity-coupled combustion response functions of composite propellants. The theory is that compositional fluctuations occur in the course of composite propellant burning, that these fluctuations originate from the inherent heterogeneity of the propellant microstructure, and that they will contribute to the nonsteady combustion under oscillating pressure (and velocity) conditions. Properties of the response to compositional fluctuations were determined and compared with responses to pressure and velocity fluctuations in series of parametric studies. The response to compositional fluctuations was found to be relatively strong response. Each response tended to increase with increasing AP particle size and pressure, and with decreasing mean crossflow velocity. A series of experiments was carried out with three propellants to determine whether or not certain features of the microstructure could be measured and correlated with response function behavior. Additional tasks pertaining to nonlinear combustion response and high frequency combustion response were performed and are described in the text. A list of publication generated by or in the course of this program is presented.
| Author | : Vasily B. Novozhilov |
| Publisher | : John Wiley & Sons |
| Total Pages | : 352 |
| Release | : 2020-08-21 |
| Genre | : Technology & Engineering |
| ISBN | : 1119525640 |
Despite significant developments and widespread theoretical and practical interest in the area of Solid-Propellant Nonsteady Combustion for the last fifty years, a comprehensive and authoritative text on the subject has not been available. Theory of Solid-Propellant Nonsteady Combustion fills this gap by summarizing theoretical approaches to the problem within the framework of the Zeldovich-Novozhilov (ZN-) theory. This book contains equations governing unsteady combustion and applies them systematically to a wide range of problems of practical interest. Theory conclusions are validated, as much as possible, against available experimental data. Theory of Solid-Propellant Nonsteady Combustion provides an accurate up-to-date account and perspectives on the subject and is also accompanied by a website hosting solutions to problems in the book.
| Author | : Martin Summerfield |
| Publisher | : Elsevier |
| Total Pages | : 713 |
| Release | : 2013-11-11 |
| Genre | : Science |
| ISBN | : 0323163351 |
Solid Propellant Rocket Research
| Author | : Martin Summerfield |
| Publisher | : |
| Total Pages | : 13 |
| Release | : 1968 |
| Genre | : |
| ISBN | : |
The overall objective of the research program has been to study the non-steady burning characteristics of solid rocket propellants, both experimentally and theoretically, to establish a basis for avoiding combustion instability in rocket motors and for predicting thrust transients during motor ignition and extinction. A new non-steady burning model for composite propellants was formulated in which the key element, the non-steady heat feedback law from the gaseous flame, was shown to be a function of the instantaneous pressure and burning rate. Solutions to this model showed that burning stability is largely determined by the exothermicity of reactions in the immediate neighborhood of the propellant surface and by the sensitivity of burning rate to surface temperature. The predictions of the model were generally confirmed by T-motor and rapid pressurization experiments. The non-steady burning model was also used to analyze L-star combustion instability in rocket motors and to demonstrate the feasibility of a novel mechanism for suppression of combustion instability by aluminum addition to a propellant. (Author).
| Author | : G. Burton Northam |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1968 |
| Genre | : Acceleration (Mechanics) |
| ISBN | : |
| Author | : R. A. Battista |
| Publisher | : |
| Total Pages | : 112 |
| Release | : 1972 |
| Genre | : |
| ISBN | : |
Solid rocket performance during rapid pressure excursions differs greatly from predictions based on steady-state burning rate data. Rapid pressurization (150 to 250 kpsi/sec) following a sudden throat area decrease in a low L star combustor produces pressure overshoots of 10% and indicated burning rate overshoots in excess of 50%. A transient internal ballistics model was developed incorporating nonsteady continuity and energy equations for the chamber, nonsteady energy equation for the propellant condensed phase, and a modified Zeldovich heat feedback function for the propellant (which for the conditions considered is known to burn a thin quasi-steady reaction zone). Sensitivity analyses using the model indicate that accurate surface temperature and temperature sensitivity data are needed. (Author).
| Author | : Alexander S. Shteinberg |
| Publisher | : Springer Science & Business Media |
| Total Pages | : 203 |
| Release | : 2008-09-26 |
| Genre | : Science |
| ISBN | : 3540788611 |
Modern energetic materials include explosives, blasting powders, pyrotechnic m- tures and rocket propellants [1, 2]. The study of high-temperature decomposition of condensed phases of propellants and their components (liquid, solid and hybrid) is currently of special importance for the development of space-system engineering [3, 4]. To better understand the burning mechanisms (stationary, nonstationary, - steady) of composite solid propellants and their components, information about the macrokinetics of their high-temperature decomposition is required [5]. To be able to evaluate the ignition parameters and conditions of safe handling of heat-affected explosives, one needs to know the kinetic constants of their high-temperature - composition. The development of new composite solid propellants characterized by high performance characteristics (high burning rates, high thermal stability, stability to intrachamber perturbations, and other aspects) is not possible without quanti- tive data on the high-temperature decomposition of composite solid propellants and their components [6]. The same reasons have resulted in signi?cant theoretical and practical interest in the high-temperature decomposition of components of hybrid propellants. It is known that hybrid propellants have not been used very widely due to the low bu- ing (pyrolysis) rates of the polymer blocks in the combustion chambers of hybrid rocket engines. To increase the burning rates it is necessary to obtain information about their relationships to the corresponding kinetic and thermophysical prop- ties of the fuels.
| Author | : Vigor Yang |
| Publisher | : AIAA |
| Total Pages | : 1038 |
| Release | : 2000 |
| Genre | : Ballistics, Interior |
| ISBN | : 9781600864377 |
| Author | : R. L. Glick |
| Publisher | : |
| Total Pages | : 79 |
| Release | : 1975 |
| Genre | : |
| ISBN | : |
Monodisperse BDP combustion model was extended to nonmetallized propellants with mixed, polydisperse oxidizers by embedding monodisperse model in statistical framework including mixture ratio effects. Basically, polydisperse propellant is 'disassembled and rearranged' to form sequence of monodisperse pseudo-propellants whose rates are computed via monodisperse model. Reassembly provides real propellant's burning rate. Approach provides information pertaining to distribution of regression rates and surface structure among different size oxidizer particles. Preliminary results suggest that significant factor in rate increases wrought by introduction of small oxidizer modes is mixture ratio alternations in larger modes. Hydraulic T-burner analog was constructed and employed to visualize vent flow phenomena. Studies showed that flow enters vent with axial momentum and that momentum is partially transformed to vent into Karman vortex sheet. Fact that flow enters vent with axial momentum invalidates boundary condition of Culick analysis for flow turning gain; 'correct' boundary condition leads to null vent gain. Experimental facts consistent with proof that in formal one-dimensional flow vent gain violates second law of thermodynamics. Logical and consistent way to reduce solid rocket data when pressure-time history is not neutral was derived. Since current techniques are not self-consistent in this situation, these results open door to reclamation of performance data heretofore rejected. (Author).
