SOLID FUEL ROCKET ENGINE Russian patent published in 2020 - IPC F02K9/34 

FIELD: rocket equipment.

SUBSTANCE: invention relates to the field of rocket equipment and can be used in rocket engines of solid fuel and autonomous on-board power sources. Solution of the set task is achieved by the fact that in solid-propellant rocket engine consisting of combustion chamber, partially armoured powder charge and nozzle bottom, in the centre of which there is a cavity communicating with the charge end, in the wall separating the cavity and the volume between the charge and the bottom with the nozzles, there are evenly distributed gas ducts on its surface connecting the cavity with the volume between the charge and the nozzle bottom. Some gas ducts are made in plane of nozzles. Total flow area of the channels is determined by the ratio

, where F_chan - total flow area gas-water channels m²; S₁ is the powder charge combustion surface area limited by the cavity dimensions, m²; F_cr is area of critical section of nozzles of solid propellant rocket engine, m²; S_r is area of initial surface of powder charge burning, m².

EFFECT: higher reliability of functioning of rocket engine of solid fuel with propellant charge, having developed initial burning surface.

1 cl, 2 dwg