MULTI-CHAMBER LIQUID-PROPELLANT ROCKET ENGINE WITH AFTERBURNING WITH CONTROLLED THRUST VECTOR Russian patent published in 2019 - IPC F02K9/80 

FIELD: engine building.

SUBSTANCE: invention relates to multichamber liquid-propellant rocket engines with afterburning and controlled thrust vector. Multichamber liquid-propellant rocket engine with afterburning and controlled thrust vector comprises frame, gas generator, turbo pump unit with pumps, input manifolds of oxidizer and fuel with inlet pipes and installed on them starting valves, several fixed main chambers connected by gas ducts with turbine cavity and lines with cavities of pumps, and control nozzles connected by main lines with start-shutoff valves with turbine pump turbine pump turbine cavity, wherein an additional pump unit is installed with fuel and oxidizer pumps and an electric drive in the form of an electric motor, connected by an electrical system to the installed battery, Inputs of similar components of the latter are connected by mains with start-shutoff valves installed thereon with cavities of inlet branch pipes before start-shutoff valves. Besides, in it the second additional unit is installed with a current generator with a hydraulic turbine, which inlet is connected to a pumping cavity of one of the turbo-pump unit components, and outlet – main line with installed on it starting-shut-off valve with cavity of control element with same name component, and current generator is connected to accumulator by means of feeder with possibility of disconnection at main cameras switching-off.

EFFECT: invention provides expansion of functional capabilities due to operation of control chambers at switched off turbo-pump unit and fixed main chambers and due to conversion of rocket stage to new orbit.

1 cl, 4 dwg