The Use of an Arc Image Furnace for Solid Propellant Ignition Studies PDF Download
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Author: J. B. Dawes
Publisher:
ISBN:
Category : Internal combustion engines
Languages : en
Pages :
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Author: J. B. Dawes
Publisher:
ISBN:
Category : Internal combustion engines
Languages : en
Pages :
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Author: Jacqueline Bernadette Dawes
Publisher:
ISBN:
Category : Electric furnaces
Languages : en
Pages : 24
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The arc image furnace is a laboratory device which may be used to ignite rocket propellant, simulating the conditions of overall heat flux and pressure levels obtained in the rocket motor. Ignition in a motor is usually initiated by a pyrotechnic device which produces a heating effect mainly by conduction of heat by hot particles impinging on the propellant surface and convective heating from the hot gases flowing over the surface. There is only a small proportion of the heat transferred by radiation from the igniter products. In the arc image furnace, however, radiant heat is the means used for igniting the propellant. Thus it is not an absolute test of ignition delay, but it gives an indication of the delays which may be expected from a solid propellant. (Author).
Author: M. Summerfield
Publisher:
ISBN:
Category :
Languages : en
Pages : 45
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The arc image furnace is used widely for evaluating solid propellant ignition characteristics, but the applicability of such data to rocket motors is questionable. In arc image testing, radiation replaces the normal conductive and convective heating modes that exist in rocket motor ignition; radiation interacts with the propellant in a basically different way. Thus, for example, because radiation is absorbed in depth, the ignition delay is sensitive to propellant opacity. In addition, radiation can cause subsurface disruption of the propellant. A physical model is proposed in which incident radiation penetrates the propellant and is absorbed, causing thermal and photochemical decomposition and a temperature increase. Oxidative reactions start either in the gaseous boundary layer or on the surface and, by thermochemical action, lead to a flame. The system of differential equations for this complete model is complicated and has not been solved. However, an equivalent model of simpler character is solved, and an equation is produced for the ignition time delay as a function of radiation intensity, pressure, and physico-chemical properties. The qualitative behavior of experimental radiative ignition data reported by Beyer and Fishman and by Bastress is explained by this theory. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 960
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: R. W. Fleming
Publisher:
ISBN:
Category :
Languages : en
Pages : 45
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The objective of this research program was to evaluate the feasibility of coating the propellant surface with an opaque, nonreacting material to eliminate this difficulty in interpretation of test results. The effect of the coating would be to reduce absorption of radiant energy beneath the propellant surface and provide a uniform surface absorptivity for different propellants. Radiant flux levels considered for this study were selected to indicate the effectiveness of coatings over a range of 30 to 130 cal/sq cm -sec. Both rubber-base and double-base propellants were tested. Results of this program indicate that zirconium carbide and tungsten carbide can be used as nonreactive coatings in arc-image furnace testing. However, certain anomalies were observed that might indicate that propellant ingredients and coating materials can interact and influence the ignition energy requirements in specific heating ranges. (Author).
Author: Peter E. Glaser
Publisher: Springer
ISBN: 148995645X
Category : Science
Languages : en
Pages : 273
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Author: Martin Summerfield
Publisher: Elsevier
ISBN: 0323163351
Category : Science
Languages : en
Pages : 713
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Book Description
Solid Propellant Rocket Research
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 780
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Author: L. Dauerman
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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The objective is to investigate the mechanism of action of burning rate catalysts in the ignition and combustion of double-base propellants. Experimentally, the surface temperatures of burning propellant strands are measured and chemical-kinetic investigations of the products of degradation of the regressing surface are carried out. Heat is supplied by an arc image furnace for the ignition studies. (Author).
Author:
Publisher:
ISBN: 9788170226611
Category :
Languages : en
Pages : 6
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