Properties of agglomerate-reduced propellant under solid rocket motor conditions

To improve understanding of the combustion properties of agglomerate-reduced propellants under solid rocket motor conditions and to compare their combustion properties between combustor conditions and rocket motor conditions, agglomerate-reduced propellants have been subjected to a series of contrastive experiments. The burning agglomerate particle size, ablation, composition of combustion residue, and combustion efficiency have been studied under solid rocket motor conditions and compared with data obtained under high-pressure combustor conditions. The results indicate that, both in the high-pressure combustor and in the solid rocket chamber, the agglomerate-reduced propellant efficiently reduced the burning agglomerate particle size and the ablation of the insulation material, and it promoted a higher combustion efficiency of aluminum as compared to common propellants.