Method and apparatus for controlling the throat area, expansion ratio and thrust vector angle of an aircraft turbine engine exhaust nozzle using regions of locally separated flow

摘要

A method and apparatus for controlling the throat area, expansion ratio and thrust vector of an aircraft turbine engine exhaust nozzle, includes means, such as deflectors and/or injected air, for producing and controlling regions of locally separated flow. The exhaust nozzle also allows control of the thrust vector angle defined by the gas exiting the nozzle to provide increased directional control of the aircraft.