Abstract
The composition of a pasty propellant for small-sized space engines has been proposed. For this propellant, a research of the burning process was carried out. This research included the determination of the burning rate law, the characteristics of the agglomeration process, and the properties of the surface layer. The presence of an intermediate structure, a skeleton layer, during the burning of such propellants, and the nature of the influence of pressure, additives, and the size of oxidizer particles on this structure, have been established. The determining influence of this structure on the burning process is shown. Composition solutions that provide control over the burning rate law of such propellants are determined. These solutions make it possible to change the absolute value of the burning rate, as well as its dependence on pressure. Regularities of the agglomeration process have been established. These regularities are associated with the features of the formation of the skeleton layer, which depend on the structure of the propellant, pressure, and the presence of additives.
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