LIQUID-PROPELLANT ROCKET ENGINE WITH EXTENDABLE NOZZLE Russian patent published in 2017 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: liquid propellant rocket engine with extendable nozzle containing a chamber with a nozzle of two parts, one of which, mounted fixedly with a combustion chamber, is provided with the extension mechanism in the form of the drive, the actuating mechanism and the assemblies of direction and fixation in the end position, and the second one is configured to move along the axis of the nozzle of two parts connected telescopically to each other with the possibility of mutual kinematic interaction with the asemblies of direction and fixation, profile multistart helical guides are made along the cylindrical contour on the periphery of the stationary nozzle shell, on the circularly equal helical paths equidistant from each other and the longitudinal axis of the engine, and an annular shell is mounted on the housing of the extendable nozzle part with maximal diameter, with the rotation possibility and axial fixing, equipped with two groups of trunnions with spherical bearings, directed to the longitudinal nozzle axis and in the other direction, one group of trunnions interacting by their bearings with inner profiles of screw guides, and the second group of trunnions being equipped with spherical bearings, interacting through the connecting rods with the group of trunnions placed at the outer nozzle part of the maximum diameter.

EFFECT: reducing dynamic loads on the nozzle at extending on the end extension portion and reducing the radial dimensions and weight.

4 cl, 7 dwg