AXISYMMETRIC NOZZLE OF ROCKET ENGINE Russian patent published in 2014 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: in a supersonic part of an axisymmetric nozzle of a rocket engine there is an insert installed, which has length, output diameter and expansion degree less than the appropriate geometric parameters of the wall in the supersonic part of the nozzle. The insert takes two mounting positions - adjoins the wall of the supersonic part of the nozzle in process of flight in dense layers of atmosphere and is placed outside the area of aerodynamic interference with the rear edge of the wall in process of flight in low-density atmosphere. In the position designed for flight in low-density atmosphere the front edge adjoins the surface, which limits disturbances that reach the wall and the tangent to the generatrix of which passing via the edge of the output cross section of the nozzle, is directed at the angle $$\mu =arctg\frac{1}{\sqrt{M^2-1}}$$ to the tangent to the generatrix of the wall in the output section, where M - local Mach number near the wall in the output section of the nozzle.

EFFECT: increased nozzle traction at specified dimensions.

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