This paper reports results obtained from an experimental study of the combustion mechanism of aluminized propellants based on an energetic binder. The techniques used in this investigation include: Quench-collection of condensed combustion products in the gas phase zone above the burning surface and study of the products including mass, chemical, and structural analyses and particle size measurements Measurement of propellant burning rate Study of combustion residues collected using special plates On the basis of the experimental data obtained, a general physical picture of combustion of aluminized propellants based on energetic binders was developed. The results of this study allowed us to refine the general understanding of metallized propellant combustion, to identify problems related to the use of such propellants, and to suggest methods for the optimization of high-energy solid rocket propellants.