The Unsteady Burning of Radiatively Active Solid Propellants PDF Download
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Author: Seung W. Baek
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Seung W. Baek
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 268
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Book Description
Experimental and analytical investigations were conducted to understand the ignition and nonsteady burning processes that occur at and near the propellant surface, to determine the connection between the ignitability of a propellant and its other nonsteady combustion characteristics, to quantify the peculiarities of radiative ignition, and to develop a means of ranking propellant ignitability. As a result of these investigations, radiative ignition processes have been explained for a wide variety of propellant and test conditions. The stability properties of heterogeneous combustion waves were considered for linear and nonlinear situations. Nonlinear (large disturbances) solid propellant stability boundaries can be immediately defined from the knowledge of the associated restoring function. The restoring function is a property strictly dependent on the nature of the solid propellant.
Author: Martin Summerfield
Publisher: AIAA
ISBN: 9781600863967
Category : Solid propellants
Languages : en
Pages : 922
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Book Description
Author: Vasily B. Novozhilov
Publisher: John Wiley & Sons
ISBN: 1119525640
Category : Technology & Engineering
Languages : en
Pages : 352
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Book Description
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:
Publisher:
ISBN:
Category :
Languages : en
Pages : 77
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Book Description
The model of uniformly distributed combustion in the gas phase is used as the basis for examining several features of unsteady burning. As a zeroth approximation the flame zone begins at the solid-gas interface and responds linearly and quasi-statistically to changes of pressure only. Three deviations from this behavior are then examined: the combustion zone is displaced from the surface, the energy release responds to fluctuations of temperature and the response is not quasi-static. It appears that the assumption that the burning begins immediately at the surface can lead to significant changes, more important than the assumption that the energy release responds to changes of pressure only, especially in the interpretation of experimental data. The problem of nonquasi-static behavior, i.e., processes in the gas phase do not follow precisely impressed changes of pressure, is formulated as an expansion in frequency. Approximate results seem to be consistent with existing information.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
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Book Description
A theoretical analysis is presented of unsteady solid propellant combustion, particularly combustion stability and extinction by rapid depressurization. It is assumed that the solid decomposes by a pyrolosis law and the gaseous products react exothermically following an Arrhenius law. For large values of this non-dimensional activation energy the gas-phase combustion, turns out to be quasisteady. The characteristic response time of the solid to gas-phase perturbations turns out to be large compared to the characteristic residence time in the heat-up zone of the solid, their ratio being of the order of the non-dimensional activation energy in the gas-phase. A linear stability criterion has been obtained that gives stable burning for steady burning rates above and below two limiting values; the width of the unstable region increases with the activation energy of the pyrolisis law, and becomes zero for a finite value of that activation energy.
Author: Ben T. Zinn
Publisher:
ISBN:
Category : Solid propellant rockets
Languages : en
Pages :
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Author: Martin Summerfield
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
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:
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Category :
Languages : en
Pages :
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Author: Bantwal Rabindranath Baliga
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
A one-dimensional analysis of the small-amplitude oscillatory burning of a solid propellant has been developed. The analysis is based on a simplified flame model using quasi-steady gas-phase approximation. The difference between this analysis and previous analyses is that radiant heat loss from the burning surface has been included in the present theory. This heat loss produces significant qualitative and quantitative differences in the unsteady behaviour of solid propellants at low pressures. The effect of initial temperature on the stability of the combustion process has also been examined. (Modified author abstract).
