Experimental studies on the burning of nanoaluminum-based solid rocket propellants are carried out. Data on the properties of condensed combustion products, mechanisms of their formation, and burning-rate law are obtained.\ud Based on these data, a physical picture is developed of the considered burning-propellant classes. Mathematical modeling of burning nanoaluminum in composite solid rocket propellants is carried out. The influence of nanoaluminum on ignition temperature of the metal fuel and burning-rate law is shown. The results of this study allow carrying out the analysis and selection of good-quality propellants using nanoaluminum

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.* Quench-collection of condensed combustion products in the gas phase zone above the burning surface and direct study of the products, including mass, chemical, and structural analyses and particle size measurements * Measurement of the propellant burning rate * Study of combustion residues obtained using special collecting platesThe techniques and equipment used are described in [1] and [2]. For a quantitative description of the process the following parameters are used: * f m (D) -mass-median probability density of size of agglomerates * f m (d) -mass-median probability density of size of smoke oxide particles * Z m -fraction of unburned metal in agglomerates relative to initial metal content in propellant * Z ox m -fraction of initial metal content in propellant used to form oxide in agglomerates * Z a m -fraction of initial metal content in propellant used to form agglomerates * h -mass fraction of oxide in agglomerate * D 43 -mass-median diameter of agglomerates, mm

The experimental results obtained within a joint international research e¨ort regarding the formation of condensed combustion products from nanoaluminum-based solid propellants (SPs) are reported. Data on the size, structure, chemical composition, and quantity of condensed combustion products (CCPs) as well as conditions of their formation are discussed. On the basis of the collected experimental data, a general physical picture of condensed combustion products formation is portrayed. The results of this study allow carrying out the analysis of good quality propellants using nanoaluminum.

The present work is devoted development of model of agglomerating process for propellants based on ammonium perchlorate (AP), ammonium dinitramide (ADN), HMX, inactive binder, and nanoaluminum. Generalization of experimental data, development of physical picture of agglomeration for listed propellants, development and analysis of mathematical models are carried out. Synthesis of models of various phenomena taking place at agglomeration implementation allows predicting of size and quantity, chemical composition, structure of forming agglomerates and its fraction in set of condensed combustion products. It became possible in many respects due to development of new model of agglomerating particle evolution on the surface of burning propellant. Obtained results correspond to available experimental data. It is supposed that analogical method based on analysis of mathematical models of particular phenomena and their synthesis will allow implementing of the agglomerating process modeling for other types of metalized solid propellants.

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