Accession Number : ADB062847
Title : Combustion Response Calculations for Composite Solid Propellants. Volume I.
Descriptive Note : Final rept. Feb 78-Feb 80,
Corporate Author : PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS
Personal Author(s) : Renie, J. P. ; Osborn, J. R.
Report Date : DEC 1981
Pagination or Media Count : 203
Abstract : In this report, the theoretical, steady state combustion model, the Petite Ensemble Model (PEM), is described in detail. The PEM is based upon a combination of a unique statistical treatment of the burning propellant surface and a comprehensive multiple flame type, physio-chemical combustion model. Due to this statistical treatment, the PEM can account for both oxidizer particle size and oxidizer particle size distribution effects on burning rate behavior; an unique feature of this model. The effects on propellant burning rate behavior due to the inclusion of aluminum particles have been taken into account within this version of the PEM, as have any possible effects caused by the presence of a crossflow velocity above the propellant surface (erosive burning). The PEM is capable of modeling the burning behavior of AP-based/hydrocarbon binder, composite solid propellants. Propellant additives such as aluminum oxide, zirconium carbide and graphite, as well as aluminum, can also be incorporated in the propellant formulations modeled by the PEM. This report presents the results obtained by applying a small perturbation analysis to the equations representing the steady state PEM (including aluminum and erosive burning effects). Performing such an analysis yields nonsteady state models of both the pressure coupled response and the velocity pressure coupled response of composite solid propellants. Other historical pressure coupled response models such as the Dension and Baum mode, the Cohen model, and the Zeldovich/Novozhilov model are also briefly described. Finally, a second velocity coupled response model based on the Zeldovich/Novozhilov methodology coupled to the erosive burning PEM is presented. (Author)
Descriptors : *COMBUSTION, *COMPOSITE PROPELLANTS, *SOLID PROPELLANTS, *RESPONSE, COMPUTATIONS, STEADY STATE, MODELS, BURNING RATE, ALUMINUM, PARTICLE SIZE, SURFACES, VELOCITY, PERTURBATIONS, ZIRCONIUM, CARBIDES, ADDITIVES, EROSIVE BURNING, ALUMINUM OXIDES.
Subject Categories : Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE