Design features of a granular-propellant supply system and an experimental setup for analyzing bulk materials outflow

An analysis of the design features of a system for supplying granular propellant to the rocket engine combustion chamber was carried out and requirements for this system were formulated. The closest analogue is considered – the aluminum powder supply system of a jet engine. This supply system provides a critical flow mode for the powder-gas medium, at which the processes occurring in the combustion chamber do not affect the granular propellant supply. The disadvantages of this supply system are listed, provided that it is used in a granular-propellant engine. An engine schematic diagram was developed, as well as a control unit for the propellant supply system as part of the propulsion system that fully satisfies the stated requirements. An experimental setup for the powder-gas medium (granules and gas) outflow studying was designed, the operation of the setup was described in detail and a design diagram was given, in particular, a propellant tank and a flow control unit. Some design solutions used in the experimental setup can be subsequently used in the real rocket engine design. Based on the theoretical and experimental data available in the literature, the problems solved using the developed installation are formulated: obtaining flow and velocity characteristics of the critical outflow of a powder-gas medium as a function of the pressure in front of the outlet.