LOW-THRUST SINGLE-COMPONENT LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2020 - IPC F02K9/68 

FIELD: machine building.

SUBSTANCE: invention relates to single-component low-thrust liquid-propellant thrusters. Engine comprises fuel decomposition chamber 1 with gas-dynamic nozzle 2, fuel supply tube 3 from control valve 4 fixed on circuit board 5 with flange for connection to spacecraft (not shown), to inlet part of decomposition chamber 1. Decomposition chamber 1 with nozzle 2 and the fuel supply pipe 3 are coaxially located inside power casing 6. Inlet end part of decomposition chamber 1 is made in the form of bushing 7, at the end of which there are three lobes 8 perpendicular to the engine axis, which form the minimum required radial gap with the inner surface of power casing 6 considering their mutual thermal expansion. On the output surface of power casing 6 perpendicular to the engine axis there are three projections 9 forming minimum required radial clearance with the external surface of decomposition chamber 1 in the area of nozzle 2 considering their mutual thermal expansion. In power housing 6 to simplify the design and reduce the heat flow to bushing 7 with lobes 8, as well as towards mounting board 5, openings 10 are made.

EFFECT: invention provides mechanical strength of fuel supply pipe and decomposition chamber as a whole with simultaneous increase of specific characteristics due to maximum reduction of heat flow from decomposition chamber to fuel supply tube and power housing.

1 cl, 3 dwg