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T. L. Boggs

Bio: T. L. Boggs is an academic researcher. The author has contributed to research in topics: Ammonium perchlorate & Deflagration. The author has an hindex of 1, co-authored 1 publications receiving 109 citations.

Papers
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Journal ArticleDOI
TL;DR: In this article, a single crystal self-deflagration of pure ammonium perchlorate single crystal was studied, determining energy transfer mechanisms from pressure effects, combustion characteristics and subsurface profile.
Abstract: Pure ammonium perchlorate single crystal self deflagration, determining energy transfer mechanisms from pressure effects, combustion characteristics and subsurface profile

123 citations


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Book
01 Jan 2000
TL;DR: In this article, the authors present in-depth coverage on a wide range of topics including advanced materials and non-traditional formulations; the chemical aspects of organic and inorganic components in relation to decomposition mechanisms, kinetics, combustion and modelling; safety issues, hazards and explosive characteristics; and experimental and computational interior ballistics research, including chemical information and the physics of the complex flow field.
Abstract: This volume brings together international scientists in the field of solid rocket propulsion. Thirty-nine papers present in-depth coverage on a wide range of topics including: advanced materials and non-traditional formulations; the chemical aspects of organic and inorganic components in relation to decomposition mechanisms, kinetics, combustion and modelling; safety issues, hazards and explosive characteristics; and experimental and computational interior ballistics research, including chemical information and the physics of the complex flow field.

190 citations

Journal ArticleDOI
TL;DR: Burning rate data for three compounds that are currently used in propellant and explosive formulations are presented in this article with respect to initial temperature and pressure, and the dependence of burning rate on initial temperature is investigated for ammonium perchlorate, HMX, and RDX.
Abstract: Burning rate data are presented with respect to initial temperature and pressure for three compounds that are currently used in propellant and explosive formulations. The dependence of burning rate on initial temperature and pressureispresented forammonium perchlorate(AP), HMX, and RDX.Data foringredients being considered for advanced propellants, such as CL-20, ammonium dinitramide (ADN), and hydrazinium nitroformate (HNF) are also presented and compared to the more traditional compounds. These ingredients are all capable of selfdee agration,andtheirbehavioroftencontrolsthebehaviorofthepropellantsinwhichtheyarethemainingredients.

147 citations

Journal ArticleDOI
TL;DR: In this paper, a series of experimental studies of combustion of sandwiches is reported, and the results are used to develop a relatively detailed qualitative model for the combustion zone microstructure.

117 citations

Journal ArticleDOI
01 Jan 1971
TL;DR: In this article, a model describing the combustion of composite propellants has been applied to three different types of composite powders, and to two oxidizers which burn as monopropellants.
Abstract: A model describing the combustion of composite propellants has been applied to three different types of composite propellants, and to two oxidizers which burn as monopropellants. The oxidizers studied are AP, HMX, and KP (ammonium perchlorate, cyclotetramethylenetetranitramine, and potassium perchlorate), each of which has unique combustion characteristics. The monopropellant combustion of AP and HMX has been considered in detail, particularly that of AP. Calculations have been compared with experimental data for the burning rate, the sensitivity of the burning rate to both pressure and initial temperature, and the surface temperature. The agreement between the calculations and experimental data is very adequate. The results indicate that AP and HMX apparently burn with a considerable exothermic reaction at the burning surface as well as in the gas phase above the surface. Both reactions must be accounted for to give consistent results. The combustion of the three oxidizers burning with a fuel in composite propellants has also been simulated. Experimental data are presented for propellants in which the oxidizer has been systematically varied. A direct comparison has been made between the data and the calculations of the model. The calculations agree quite well with the combustion characteristics of the three different types of composite propellants.

81 citations