MULTI-CHAMBER LIQUID ROCKET ENGINE WITH CONTROLLED THRUST VECTOR Russian patent published in 2022 - IPC F02K9/80 

FIELD: rocket and space technology.

SUBSTANCE: invention relates to the field of rocket and space technology. A multi-chamber liquid-propellant rocket engine with a controlled thrust vector contains a gas generator, a turbopump unit with pumps, the inputs of which are connected to the fuel tanks of the propulsion system, a frame protruding with a conical central part relative to the peripheral, bottom protection, several fixed chambers mounted to the frame in the central part, located symmetrically relative to longitudinal axis of symmetry of the engine, connected by brackets with trunnions installed with the possibility of rotation in the traverses by means of steering gears, rocking units of the control chambers located along the periphery in the sectors between the fixed chambers in the stabilization planes, connected by lines with cavities after the pumps of the turbopump unit. The traverse and the trunnion of each swing unit are located inside the tapered central part of the bottom protection. The junction of the bracket with the journal is made in the form of a control chamber attachment beam through a cylindrical hinge perpendicular to its axis of symmetry relative to the journal and the longitudinal axis of symmetry of the control chamber. The beam is equipped with a drive for turning the control chamber around a cylindrical hinge.

EFFECT: when implementing the invention, an increase in the service life of the main liquid-propellant rocket engine is provided, a simplification of the means of protection against thermal effects on the engine units during a vertical landing of the reentrant stage of the launch vehicle, a decrease in the mass of the means for thermal insulation of the fuel tanks and units of the central main liquid-propellant rocket engine.

2 cl, 9 dwg