Patent ID: 8020386

Claim:
A mechanism included in a convergent-divergent nozzle configured to be connected to an aftward portion of a gas turbine engine, the mechanism comprising: at least one actuator configured to be connected to the aftward portion of the engine and to move a first coupling point through one or more positions; an annular ring connected to the at least one actuator, providing to the at least one actuator a second coupling point to move through the one or more positions, the second coupling point being disposed radially outward from the first coupling point and a main axis of the engine; a first link pivotally connected directly to the first coupling point of the at least one actuator; a convergent flap pivotally connected to the first link; a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to the second coupling point; and at least one track configured to extend from the aftward portion of the engine and which movably and pivotally receives the connection between the convergent flap and the first link.