FIELD: rocket science.
SUBSTANCE: invention relates to combustion chambers of low-thrust rocket engines operating on two-component self-igniting liquid rocket fuel. A method consists in feeding self-igniting fuel components through nozzle elements of a mixing head, their flow in the combustion chamber, liquid-phase mixing in the zone of nozzle elements, obtaining liquid-phase and gas-phase intermediate combustion products, ignition, combustion and expiration of combustion products through the nozzle of the chamber, according to the invention, the flow of fuel components in the combustion chamber and the process of liquid-phase mixing are performed at pressure less than or equal to pressure of saturated vapors of at least one of fuel components.
EFFECT: organization of the workflow in the chamber of the low-thrust liquid rocket engine.
1 cl, 5 dwg
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