METHOD OF CONTROL OF VECTORED-THRUST NOZZLE OF AIRCRAFT GAS-TURBINE ENGINE Russian patent published in 2007 - IPC F02K1/18 

FIELD: aircraft industry; vectored-thrust nozzles of gas-turbine engines.

SUBSTANCE: proposed vectored-thrust nozzles are furnished, as a rule, with drive ring to control supersonic flaps of nozzle, and control hydraulic drives with rods connected to drive ring, and hydraulic drives to control nozzle throat section. According to proposed method of control of vectored-thrust nozzle of aircraft gas-turbine engine including measurement of parameter characterizing area of nozzle throat section, determination of its value, changing of position of rods of supersonic flap control hydraulic drives at thrust vector control signal according to area of nozzle throat section and signals of setting of aircraft angles of pitch and yaw and at no thrust vector control signal, gas pressure after turbine, pressure characterizing pressure at section of supersonic flaps are measured additionally, and, basing of said additionally measured parameters and area of throat section of nozzle, required area of exit section of nozzle is determined, and position of rods of hydraulic drives is changed according to preliminarily determined relationship between area of exit section of nozzle and position of rod of hydraulic drive at fixed values of area of nozzle throat section. Result is obtained also owing to the fact that at determining area of nozzle throat section, angle of deflection of engine control level and air temperature at engine inlet are taken as parameters characterizing area of nozzle throat section. Thus additional increase of engine thrust characteristics is provided.

EFFECT: increased thrust characteristics of engine at supersonic regimes at axially symmetric position of supersonic flaps of nozzle owing to optimization of flap control process.

2 cl, 1 dwg