Agglomerate Size Evolution in Solid Propellant Combustion under High Pressure

Solid propellant combustion and flow are significantly affected by condensed products (CCPs) in solid rocket motors. A new aluminum agglomeration model is established using the discrete element method, considering burning rate formulation of propellant. Combining alumina deposition model, an analytical evolution CCPs proposed, capable predicting particle-size distribution completely burned CCPs. The near away from surface collected a special quench vessel under 6~10 MPa, to verify applicability CCP model. Experimental results show that predicted error proposed less than 8.5%. Results expected help develop better tools for propellants