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RESEARCH PAPERS

Numerical Solution of Solid Propellant Transient Combustion

[+] Author and Article Information
D. E. Kooker, C. W. Nelson

U. S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD 21005

J. Heat Transfer 101(2), 359-364 (May 01, 1979) (6 pages) doi:10.1115/1.3450974 History: Received February 06, 1978; Online August 11, 2010

Abstract

Three thermal theories of solid propellant combustion, [1, 2, 3], all based on the quasi-steady flame assumption, were subjected to a rapidly rising external pressure field simulating a gun combustion chamber. Transient burning rates were computed by four different numerical solution methods; the best results were obtained with an invariant imbedding scheme. The numerical predictions show that (1) burning rate “runaway” is a numerical difficulty and is not a solution to the models, (2) the final state of an intrinsically unstable model at constant pressure is composed of repeating finite-amplitude spikes, and (3) the dynamic burning rate from a linearly-stable model can be many times greater than r = apn .

Copyright © 1979 by ASME
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