Accession Number : ADB000707
Title : Analytical Investigation of the Combustion Processes Occurring in Advanced Nitramine-Based Propellants.
Descriptive Note : Final rept. Jun 73-Jul 74,
Corporate Author : JET PROPULSION LAB PASADENA CALIF
Personal Author(s) : Kumar,R. N. ; Strand,L. D.
Report Date : SEP 1974
Pagination or Media Count : 64
Abstract : This report summarizes a theoretical investigation of the current problems of nitramine (composite) propellant combustion. This study has a detailed examination of the condensed-phase processes in the combustion of nitramine propellants. As a consequence of a recently developed model for the combustion of ammonium perchlorate (AP)/composite propellants, it is hypothesized that the condensed-phase degradation of the nitramine oxidizer particles to a vaporizable state is the overall rate-limiting step. It is also assumed that the gas-phase details are secondary in importance and need be studied only to the extent of supplying the correct boundary conditions on the condensed-phase/vapor-phase heat transfer. Because of an imprecise understanding of the gas-phase processed in the presence of combustion, several plausible models are considered for the gas phase. All of the gas-phase models considered lead to predictions sufficiently close to experimental trends to conclude that precise details of gas-phase processes are not of critical importance in determining propellant combustion behavior. It is believed that a thorough examination of the condensed-phase details may be sufficient in itself not only to interpret most of the available data on experimental regression rate vs. pressure of nitramine propellants, but also to aid in the formulation of propellants needed.
Descriptors : (*NITRAMINES, *COMBUSTION), (*COMPOSITE PROPELLANTS, NITRAMINES), SOLID ROCKET PROPELLANTS, SOLID ROCKET OXIDIZERS, INTERIOR BALLISTICS, BURNING RATE, CONDENSATION, DEGRADATION, VAPORS, PHASE STUDIES, AMMONIUM PERCHLORATE, PARTICLE SIZE, HEAT TRANSFER, COMPUTER PROGRAMS, MATHEMATICAL MODELS
Subject Categories : Computer Programming and Software
Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE