An Experimental Study of Composite Propellant-burning Thermal Wave in the Presence of Crossflow PDF Download
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Author: Miroljub Adzic
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Category :
Languages : en
Pages :
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Author: Miroljub Adzic
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Category :
Languages : en
Pages :
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Author: Merrill K. King
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Category :
Languages : en
Pages : 30
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Augmentation of solid propellant burning rate often occurs in the presence of strong product gas flow across the burning surface: This phenomenon is referred to as erosive burning. Increasing use of motors with low port-to-throat area ratios (including nozzleless motors) is leading to increased occurrence and severity of erosive burning. A first generation model based upon bending of columnar diffusion flames by a crossflow, permitting prediction of the effect of high-velocity crossflow on the burning rate of a composite propellant given only the zero-crossflow burning rate characteristics, is briefly summarized and compared with data. A second generation model (currently under development) which does not require even zero-crossflow burning rate data, using only composition and particle size as input, is outlined. In addition, a test device permitting extensive characterization of burning rate-pressure-crossflow velocity relationships for various propellants with direct continuous measurement of instantaneous burning rate by high-speed cinematography is described, and results of a series of tests with four propellants are presented. These tests indicate that the first generation composite propellant erosive burning model has reasonable good predictive capability, particularly in the higher pressure region where the propellant combustion is dominated by the propellant heterogeneity.
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Category : Aeronautics
Languages : en
Pages : 974
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Author:
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Category :
Languages : en
Pages : 14
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An experimental apparatus designed for measurement of erosive burning rates at crossflow velocities up to Mach 1 has been used to determine the erosive burning characteristics of seven propellant formulations with systematically varied properties. A composite propellant erosive burning model based on the bending of columnar diffusion flames gives reasonably good agreement with the measured erosive burning data over a wide range of conditions, breaking down only in regions where the fuel-oxidizer gas stream mixing does not control burning rate. Propellant base (no-crossflow) burning rate is found to have a predominant effect on sensitivity to crossflow (higher- burning-rate formulations being considerably less sensitive) whether the base burning rate differences are produced by oxidizer particle size variation, oxidizer/fuel ratio variation, or use of catalysts. Comparison of erosive burning predictions using the erosive burning model described herein with flow profiles expected to prevail in the test apparatus to predictions using profiles believed to exist in cylindrically-perforated motor grains indicate that erosive burning may be considerably less for a given mainstream crossflow velocity in such a motor than in the typical erosive burning test apparatus, a result quite important to extrapolation of test apparatus erosive burning data to actual motor conditions.
Author: Mohan Kishen Razdan
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ISBN:
Category :
Languages : en
Pages : 174
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The overall objective of the current research is to achieve a basic understanding of the erosive burning mechanism in solid-propellant rocket motors. Both theoretical and experimental studies are undertaken. In the theoretical modeling, a reactive turbulent boundary-layer approach is used to analyze the erosive burning phenomenon. A second-order turbulent closure has been selected in the theoretical formulation. The theoretical model can be used to study the effect of gas velocity, pressure, streamwise pressure gradient, oxidizer particle size, and oxidizer-to-fuel ratio. For model validation, a test rig has been designed to establish a two-dimensional, turbulent boundary layer flow over a flat plate. The test rig can operate under various gas-dynamic conditions. A laser-photodiode servomechanism has been developed to measure the burning rate, and preliminary tests have demonstrated successful operation of the apparatus. (Author).
Author: Richard B. Cole
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Category :
Languages : en
Pages :
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Author: E. J. Sturm
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Category : Combustion
Languages : en
Pages : 10
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Author:
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Category : Aeronautics
Languages : en
Pages : 1124
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Author: Masafumi Tanaka
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Category :
Languages : en
Pages :
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Author:
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Category :
Languages : en
Pages : 27
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A theoretical model for prediction of burning rates of composite (ammonium perchlorate oxidizer) solid propellants as a function of pressure and crossflow velocity has been developed. Included in this model is the capability for treatment of multimodal oxidizer particle sizes and metalized formulations. In addition, an experimental device for measuring the effects of crossflow velocity on propellant burning rate has been developed and used to characterize a series of AP/HTPB propellants with systematically varied formulation parameters. Model predictions of zero-crossflow burning rate versus pressure characteristics have been found to be in excellent agreement with data, while the agreement between erosive burning predictions and data is in general good.
