| The combustion response of heterogeneous solid propellants, a quantity needed in combustion instability calculations of solid propellant rocket motors, is studied through development of a response model for analogous oxidizer-binder laminate propellants. Two key features of this analysis are incorporation of current experimental knowledge concerning the structure of the laminate combustion zone, resulting in a more detailed and physically realistic description of the phenomena, and development of a modular approach to the analysis, allowing a significant reduction in the complexity of the solution by isolating and then analyzing in a quasi-one-dimensional manner closely coupled flame-surface regions. Results show that there can be significant differences between the responses calculated via the current model and those obtained from classical one-dimensional treatments. |
