LOW-THRUST SINGLE-COMPONENT LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2019 - IPC F02K9/42 F02K9/68 

FIELD: astronautics.

SUBSTANCE: invention relates to space engineering, particularly, to single-component liquid-propellant rocket engines included in low-thrust propulsion systems of satellites for orbital maneuvering. Single-component low-thrust liquid-propellant engine comprises fuel decomposition chamber 1 with gas-dynamic nozzle 2, fuel supply tube 3 from control valve 4 fixed on circuit board 5 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 rigidly fixed on circuit board 5. Inlet end face of decomposition chamber 1 is permanently connected to support bushing of three-petal shape 7, having tail cylindrical part 8, at that fuel supply pipe 3 is coaxially located inside support sleeve with clearance. Elements of the decomposition chamber fixation elements located at the level of the fuel supply pipe inlet 3 into decomposition chamber 1 and at the level of the outlet part of nozzle 2 are made in the form of two sets of locating screws 10 and 11, three in each group. Heads of adjusting screws 10, 11 enter into threaded joints with power casing 6 and radially directed to engine axis. Ends of adjusting screws 10 pass through guide holes in intermediate ring 12, touching outer surface of tail cylindrical part 8. Intermediate ring 12 with a gap is fixed with mounting screws 10 in a suspended state above cylindrical tail part 8. Ends of adjusting screws 11 thrust against groove 13, made on outer surface of support ring 14. Support ring 14 is arranged on outer cylindrical surface of nozzle 2 in its outlet part. On inner surface of support ring 14 there is collar 15 providing contact of minimum area of support ring 14 with outer surface of nozzle 2 at all stages of engine operation. In power housing 6 there are openings 16, at the places of arrangement of threaded holes for adjusting screws 10 lugs 17 are made.

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

6 cl, 4 dwg