FIELD: engines and pumps, rocket engineering.
SUBSTANCE: invention relates to rocket thrusters. Gaseous hydrogen and oxygen rocket thruster, consisting of electropneumatic valves of fuel and oxidizer, a mixing head unit including an ignition device with a spark plug, a subsonic gas curtain to ensure an acceptable thermal state of the engine design, a combustion chamber and a nozzle, according to the invention, two annular cylinders made of oxidation-resistant and heat-resistant steel with hydrogen and oxygen manifolds, respectively, are mounted one on top of the other on the combustion chamber, on the end surfaces of which rectangular channels are installed so that each hydrogen channel intersects with the oxygen channel. Number of nodes of intersecting rectangular hydrogen and oxygen channels is 3, 4, 5 or more; they are distributed uniformly along the circumference. Height and width of the rectangular channels are related as 1:2. Ratio of the velocities of hydrogen and oxygen jets is 2.5:1.
EFFECT: invention provides an increase of the rocket engine combustion efficiency.
4 cl, 2 dwg
