Accession Number : ADA139182
Title : Non-Steady Combustion of Composite Solid Propellants.
Descriptive Note : Final research progress rept. 1 Mar-30 Sep 82,
Corporate Author : JET PROPULSION LAB PASADENA CA
Personal Author(s) : Cohen,N. S. ; Strand,L. D.
Report Date : MAY 1983
Pagination or Media Count : 32
Abstract : An analytical model for the linearized velocity-coupled combustion response function was developed. The model combines elements of response to velocity perturbations, pressure perturbations, and compositional perturbations due to the heterogeneity of composite propellants. The important effects of AP size distribution are accounted for in terms of effects on ballistics properties and in terms of periodic fluctuations in propellant composition. Properties of the response function have been calculated theoretically over a range of the governing variables. There are two facets of the crossflow problem: the response to velocity perturbations, and the effect of crossflow velocity on the various response elements. The crossflow mechanism is heuristically based upon the so-called 'Soderholm erosive burning law,' but which has been given physical significance in the theoretical work of Kuo. Significant results are described. In addition, the triggered non-linear instability experiments performed at CARDE were reviewed and shown to depend upon the achievement of a formulation-dependent critical velocity in the rocket motor. Progress was made in the measurement of the pressure-coupled response functions of propellants formulated to seek out the effects of AP particle size. Progress was made toward formulating a high frequency combustion response model applicable to nitramine/minimum-smoke propellants.
Descriptors : *Composite propellants, *Combustion stability, *Mathematical models, Combustion, Solid rocket propellants, Ammonium perchlorate, Oxidizers, Particle size, Distribution, Heterogeneity, Concentration(Composition), Burning rate, Formulations, Variations, Pressure, Coupling(Interaction)
Subject Categories : Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE