FUEL SUPPLY UNIT TO DECOMPOSITION CHAMBER OF SINGLE-COMPONENT LIQUID ROCKET ENGINE OF LOW THRUST Russian patent published in 2019 - IPC F02K9/68 

FIELD: astronautics.

SUBSTANCE: invention relates to space engineering and can be used in development of single-component liquid-propellant rocket engines, which are part of low-traction power plants of satellites. Unit of fuel supply into decomposition chamber of single-component liquid rocket low-thrust engine includes control valve 1, support tube 2 tightly connecting valve 1 with decomposition chamber 3 with catalyst 4 arranged inside it, capillary tube 5 and radial displacement limiter 6 of capillary tube 5. Capillary tube 5 is coaxially located inside support tube 2 and cantilevered at outlet of control valve 1 by means of bushing 7. Limiter of radial displacement 6 is installed with gap between capillary 5 and support 2 tubes, providing their sufficient coaxiality, and is made in the form of cylindrical spiral from metal wire, ends of which are fixed on capillary tube 5. Distance “l₁” from the outlet end surface of capillary tube 5 to decomposition chamber 3 is selected from the condition of ensuring the operability of the engine with relatively small thrusts in the operating conditions of its use and in all possible operating modes of the engine and is (0.7–0.8) of the length "L" of support tube 2 from the outlet portion of control valve 1 to the end surface of decomposition chamber 3.

EFFECT: invention provides elimination of the effect of "thermal locking" in the fuel supply unit during operation of the engine with relatively low fuel consumption and especially in pulse operating modes and, as a result, providing stability of thrust pulses, as well as exclusion of critical pressure drop amplitude when engine is switched on.

1 cl, 2 dwg