NOZZLE Russian patent published in 2023 - IPC F02K9/82 F02K9/97 

FIELD: aviation and rocket technology.

SUBSTANCE: invention relates in particular to systems for controlling the thrust vector of an aircraft engine by injecting a working fluid into the supersonic part of a nozzle containing a rocket nozzle and injection controls. The nozzle contains 4 injection controls, each of which is a valve, through the openings of which the working fluid is fed into the nozzle, which has an oval cross-sectional shape of its supersonic part. The valve openings are located with their axes perpendicular to the tangents to the oval formed by the intersection of the inner surface of the nozzle and the injection plane of the working fluid, and their axes form a certain angle with the major semi-axis of this oval in projection onto this plane at a set angle γ from 30 to 60°.

EFFECT: invention provides control of the thrust vector of a jet engine in pitch, yaw and roll, using a single control system, makes it possible to increase reliability by simplifying the design, reducing structural elements and increasing efficiency by reducing dynamic gas losses during injection of the working fluid.

4 cl, 3 dwg