FIELD: rocket science.
SUBSTANCE: invention relates to rocket science and can be applied to rockets and other aircraft for space and air applications. A rocket engine (RE) is described, containing a nozzle and a combustion chamber connected by means of a pump to a tank in which the fuel is located, according to the invention, the fuel is in a solid dispersed bulk state, the tank is a hopper, and the pump is an airlock feeding mechanism containing a housing with inlet and outlet pipes and a movable element mounted in the housing connected to the motion drive with a cavity capable of being combined with these pipes alternately. The shell of the hopper is made up of annular sections interconnected by snap ties, and the bottom of the hopper is made in the form of a piston, on which the combustion chamber is fixed with a nozzle and the specified airlock feeding mechanism.
EFFECT: invention provides a simplification of the design, increasing the reliability and safety of the engine in case of damage to its structure.
2 cl, 2 dwg
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