Abstract
A burning rate model for ammonium perchlorate (AP) and hydroxy-terminatedpolybutadiene (HTPB) composite propellants has been developed based on highfidelity calculations. The high-fidelity model, which includes detailed kinetics and species transport, was used to identify combustion trends in AP/HTPB propellants. A low-fidelity burning rate model has been developed based on the identified trends and calculated burning rates of the high-fidelity model. The AP/HTPB burning rate model requires negligible runtime and predicts burning rates based on AP particle size, formulation, and pressure. The model has been applied to 27 different AP/HTPB formations including mono, bi, and tri-modal propellants with 90% of the predictions within 20% of the experimental data. Limitations and possible improvements to the predicative capability of the model are discussed.
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