The paper is devoted to the development of a rocket engine on granular solid fuel (REGSF). The paper shows the main advantages and disadvantages of widely used propulsion systems (such as a solid-propellant rocket engine, liquid-propellant rocket engine, gas turbine engine). The proposed hybrid power plant borrows the strengths of well-known engines, such as the ability to control thrust in a wide range, multiple on and off, the ability to work in high temperatures and low oxygen content. The fuel in a REGSF is granules, the constituent components of which are both oxidizing agent and combustible. Possible propulsion systems based on REGSF, applicable for different types of tasks (can be used both for spacecraft and for ground unmanned aerial vehicles used at different altitudes with different flight speeds), are proposed and considered. As a prototype of the granular solid fuel supply system (GSFSS) the powder metal fuels supply system (PMFSS) is chosen. The flow rate and speed characteristics of the GSFSS are similar to the same characteristics of the PMFSS, they are also presented in this paper. Based on the available data on the supply system for powdered metal fuels and powdered aluminum (which is used as a fuel in a similar propulsion power plant), the requirements that granular fuel must satisfy in order to efficiently feed and ignite it are formulated and given. Requirements: dry, hydrophobic material, which must have high flowability, have a dispersion in the specified range, the type of particles must be spherical.
NUMERICAL INVESTIGATION OF THE EFFECT OF AERODYNAMIC FRAGMENTATION OF CONDENSATE PARTICLES ON THE TWO-PHASE IMPULSE LOSSES IN A SOLID-FUEL ROCKET ENGINE NOZZLE