INCREASING MEAN-TRAJECTORY SPECIFIC THRUST PULSE OF LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE TO THIS END Russian patent published in 2014 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: at engine operation in first-stage mode, fuel components combustion products expansion is confined by diameter of inner moving cylindrical shell with end surface, preferably, shaped. Said shell makes an integral part of nozzle profile to be accommodated in the nozzle fixed shell, preferably, at shell centre so that moving shell end surface makes the part of fixed shell profile part. Moving shell extends towards nozzle edge at engine operation at first-stage mode and displaces towards mixing head, primarily, to initial position at engine operation in second- and third-stage modes. Engine nozzle consists of fixed shell with at least two shaped consecutive parts connected with the chamber and/or engine structural elements and arranged with circular clearance relative to each other. It comprises the moving shell composed by hollow cylinder displacing axially along chamber axis and arranged in said circular clearance between fixed shell parts Cross-section of the joint between fixed and moving shells features the diameter making 4.0-5.0 of the nozzle throat diameters. Moving shell is connected with chamber and/or engine structural elements.

EFFECT: decreased thrust specific pulse, weight and overall dimensions.

4 cl, 4 dwg