Accession Number : AD0815882
Title : THE PREDICTION OF THE BURNING RATE EXPONENT OF SOLID PROPELLANTS,
Corporate Author : ARMY RESEARCH AND DEVELOPMENT GROUP (EUROPE) FPO NEW YORK 09510
Personal Author(s) : Heaston, Robert J.
Report Date : DEC 1966
Pagination or Media Count : 33
Abstract : It has been postulated by the author that the burning rate exponent for solid propellant combustion can be represented by n = log (1/Lewis number). The Lewis number, Le, is a dimensionless ratio of mass diffusivity to thermal diffusivity. The Lewis number correlation is used in the paper to explain burning rate versus pressure behavior for various progressive, plateau, and regressive propellants. Qualitative prediction by the correlation of observed relationships of heat and mass transport, density, specific heat, and thermal conductivity is described. Discussion is also presented on use of the model to predict a critical density effect in deflagration-to-detonation phenomena. Using a selected PBAA-ammonium perchlorate propellant as a base, the burning rate exponents of two other similar propellants were calculated. Calculated exponent values, using the Lewis number correlation, were within 10 to 25 percent of measured exponents. (Author)
Descriptors : (*BURNING RATE, MATHEMATICAL MODELS), (*PROPELLANT GRAINS, BURNING RATE), SOLID ROCKET PROPELLANTS, FUNCTIONS(MATHEMATICS), DETONATIONS, DEFLAGRATION, AMMONIUM PERCHLORATE, MASS TRANSFER, THERMAL CONDUCTIVITY.
Subject Categories : Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE