A model of composite solid-propellant combustion based on multiple flames
01 Dec 1970-AIAA Journal (American Institute of Aeronautics and Astronautics (AIAA))-Vol. 8, Iss: 12, pp 2200-2207
TL;DR: In this paper, a model describing the combustion of ammonium perchlorate (AP) composite propellants has been developed based on a flame structure surrounding individual oxidizer crystals; the relationship between crystals and the binder matrix was evaluated statistically.
Abstract: A model describing the combustion of AP composite propellants has been developed. The model is based on a flame structure surrounding individual oxidizer crystals; the relationship between crystals and the binder matrix being evaluated statistically. Three separate flame zones are considered: 1) a primary flame between the decomposition products of the binder and the oxidizer, 2) a premixed oxidizer flame, and 3) a final diffusion flame between the products of the other two flames. Simple global kinetics are assumed for gas-phase reactions, and the surface decomposition of the propellant ingredients is assumed to be adequately described by simple Arrhenius expressions. The oxidizer decomposition is taken as being the over-all controlling factor in the combustion process. The results obtained show that the calculated surface temperature and the effect of oxidizer concentration predicted by the model are in agreement with observed experimental trends. The predicted effect of particle size is somewhat greater than observed experimentally while the temperature sensitivity is in excellent agreement with experimental data. The results of the calculations indicate a relatively strong exothermic reaction taking place at the propellant surface. Apparently the ammonium perchlorate (AP) partially decomposes exothermically in the thin surface melt previously reported in AP deflagration studies.
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Cites background or methods from "A model of composite solid-propella..."
...21) captures the flame structure proposed by the original BDP combustion model [27]....
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...The flamesheet approach used in the BDP model [27,33] in essence follows the assumption of high activation energy in the gas phase....
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...One of the earliest models for mono- and composite-propellant combustion was the Beckstead–Derr–Price (BDP) model [27,33]....
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...(36) represented by an Arrhenius-like pyrolysis law is often employed [27] as follows:...
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TL;DR: In this paper, a substructure coupling method is proposed which employs free-interface substructure modes supplemented by reduced flexibility, and a numerical comparison with Hou's freeinterface method is given.
Abstract: Benfield, et al. (1972) showed that among fixed-interface, free-interface, and hybrid substructure coupling methods, the fixed-interface methods as the most accurate and the free-interface methods are the least accurate. In the present note, a substructure coupling method is proposed which employs free-interface substructure modes supplemented by 'reduced flexibility.' Substructure coupling based on the improved substructure model is discussed, and a numerical comparison with Hou's free-interface method is given. To simplify representation of the method proposed, the substructure equations are developed first for constrained substructures, and then the equations representing substructures with rigid-body modes are given. Finally, the equations for coupling of substructures are derived. Example calculations are included.
166 citations
TL;DR: In this paper, the authors used digital in-line holography (DIH) to experimentally quantify the three-dimensional position, size, and velocity of aluminum particles during combustion of ammonium perchlorate (AP) based solid-rocket propellants.
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References
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TL;DR: In this paper, the surface heterogeneity of a composite propellant is incorporated in a model of the propellant combustion process, explicitly including the oxidizer particle size distribution, and expressions for the mean, one-dimensional, propellant surface and flame temperatures are derived assuming planar regions of heat generation.
Abstract: The surface heterogeneity of a composite propellant is incorporated in a model of the propellant combustion process. This process is pictured as the sum of fuel pyrolysis, oxidizer decomposition, heterogeneous chemical reaction between the fuel and decomposed oxidizer in small fissures surrounding individual oxidizer particles, and gas phase combustion of all final decomposition products. Expressions for the burning rate and the rate of heat generation at the propellant surface and in the gas phase flame are formulated, explicitly including the oxidizer particle size distribution. Expressions for the mean, one-dimensional, propellant surface and flame temperatures are derived assuming planar regions of heat generation. A collected set of implicit, algebraic equations is solved numerically for the propellant burning rate, surface (and flame) temperatures for a variety of physical parameters. The burning rate is found to depend strongly on the oxidizer particle ignition delay at low pressures, and upon the position of the external flame at high pressures. The effect of the heterogeneous reaction on the burning rate is strongest at intermediate pressures. The results agree quite well with experimental data on the effect of pressure and oxidizer particle size on composite propellant burning rates, surface temperatures, and surface structure.
134 citations
01 Jan 1967
TL;DR: In this paper, the authors used cleaved sections of large single crystals grown from water solution, discussing burning rate and combustion zone, and discussed burning area and burning rate of ammonium perchlorate.
Abstract: Deflagration of ammonium perchlorate studied using cleaved sections of large single crystals grown from water solution, discussing burning rate and combustion zone
93 citations
TL;DR: In this article, a two-temperature model for the burning of ammonium nitrate composite propellants is presented, which predicts a lower limit of about 0·04 cm/sec to the burning rate of AN propellants.
65 citations