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. Multi-chamber liquid-propellant rocket engine with afterburning with controlled thrust vector comprises gas generator, turbo-pump unit, several chambers located in stabilization planes connected by gas ducts with turbine pump turbine pump turbine cavity, and control nozzles connected to turbine-pump unit turbine cavity by mains inputs with start-shutoff valves installed on them, wherein outputs of lines through channels made in their walls with installed in them hydraulic diodes are connected by pipelines with cavities of generator gas of mixing heads of chambers. Hydraulic diodes are made in the form of centrifugal nozzles directed by nozzles towards cavities of main lines.
EFFECT: invention provides higher accuracy of control force with the help of control nozzles.
1 cl, 9 dwg
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