MULTI-CHAMBER LIQUID-PROPELLANT ROCKET ENGINE WITH AFTERBURNING WITH CONTROLLED THRUST VECTOR Russian patent published in 2020 - IPC F02K9/88 

FIELD: rocket equipment.

SUBSTANCE: invention relates to rocket engineering, and more specifically to multi-chamber liquid-fuel rocket engine with afterburning with controlled thrust vector. Multichamber liquid-propellant rocket engine with afterburning of generator gas with controlled thrust vector, comprising gas generator, turbo-pump unit, several fixed relative to frame of chambers located in stabilization planes connected by gas ducts with turbine-pump unit turbine cavity, inert gas source in the form of a cylinder and a control nozzle, connected to the turbine-pump unit turbine cavity by the mains inputs with the start-shut-off valves installed on them, according to the invention the control nozzle units are made in the form of pairs of coaxially installed nozzles, note here that those connected with turbine pump turbomachine cavity are located in central parts while peripheral nozzles are communicated with inert gas source by means of lines with start-shutoff valves.

EFFECT: invention provides higher accuracy of control force with the help of control nozzles due to provision of control before start-up and on start-up, increase of control efficiency, and also after shutdown of multi-chamber liquid rocket engine with afterburning with control vector of thrust.

3 cl, 10 dwg