FIELD: engine building.
SUBSTANCE: invention relates to rocket thrusters. In the low-thrust liquid-propellant engine operating method arrangement, consisting in feeding self-inflammable fuel components into chamber by means of jet nozzles, obtaining fuel and oxidizer veils, followed by mixture formation and ignition in antechamber, according to the invention combustion of fuel jets is converted into veils under action of centrifugal forces and directed along the axle area of the prechamber and combustion chamber. In a preferable version, fuel component jets are converted into veils in vortex chambers of rectangular cross-section. Besides, the fuel and oxidizer veils at the outlet of the mixing screens have the same thickness and width.
EFFECT: invention provides higher efficiency of low-thrust liquid-propellant engine working process on self-igniting fuel components and higher specific thrust pulse coefficient.
3 cl, 3 dwg
