Combustion Response Calculations for Composite Solid Propellants. Volume I.
Final rept. Feb 78-Feb 80,
PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS
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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-basedhydrocarbon 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 ZeldovichNovozhilov model are also briefly described. Finally, a second velocity coupled response model based on the ZeldovichNovozhilov methodology coupled to the erosive burning PEM is presented. Author
- Combustion and Ignition
- Solid Rocket Propellants