FIELD: rocketry.
SUBSTANCE: invention relates to rocketry, in particular to methods of operation of detonation rocket engines. The method of operation of a reusable detonation liquid-propellant rocket engine is that gas energy is used to start the liquid-propellant rocket engine (LPRE) with the possibility of a short-term supply of gases to set the parts in the ready position. The energy of the oxidizer to increase the pressure in the fuel delivery mechanism. Acceleration of parts with the formation of a low-pressure area in the low-pressure chamber. With the possibility of increasing the speed of the outflow of fuel, in the area of reduced pressure, in violation of the continuity of the liquid flow in the area of reduced pressure. Displacement of gases from the high-pressure chamber with subsequent equalization of the pressure in the high-pressure chamber and automatic shutdown of the oxidant supply by the oxidizer gas distribution mechanism. Opening the reduced pressure chamber, followed by detonation of the vapor-gas mixture.
EFFECT: creation of a method of operation of a reusable detonation rocket engine, the characteristics of which provide an increase in the rate of mass rejection.
1 cl, 16 dwg
