Thrust vectorable exhaust nozzle

A flight maneuverable exhaust device for use with a gas turbine engine including:

• first variable position flap means partially defining an exhaust stream flow path having a throat and an exit, said first flap means being pivotably connected to an upstream fixed duct portion for varying exhaust stream flow path area convergence;
• second variable position flap means further defining the flow path, said second flap means being downstream of and pivotably connected to the first flap means for providing variable exhaust stream expansion control in a first operating mode and exhaust stream deflection in a second operating mode;
• third variable position flap means pivotably connected to the second flap means proximate their respective downstream extremities, said third flap means partially defining a variable contour flight control surface;
• and
• an actuation system operatively connected to at least one of said flap means for synchronously moving said first, second and third flap means to control, in a predetermined relationship the exhaust stream flow path throat area and the exhaust stream flow path exit area, and
• wherein said actuation system comprises first actuation means operatively connected to said first flap means for controlling, through the pivotable connections between the first and second flap means and the second and third flap means, the throat area and the exit area in said first operating mode;
• and
• second actuation means carried by and capable of overriding the first actuation means in said second operating mode by positioning said second flap means for deflecting the exhaust stream and, by positioning said third flap means, for changing the camber of the flight control surface.

An aircraft having a gas turbine engine flight maneuverable exhaust device comprising:

• first variable position flap means partially defining an exhaust stream flow path having a throat and an exit, said first flap means being pivotably connected to an upstream fixed duct portion for varying exhaust stream flow path area convergence;
• second variable position flap means further defining the flow path, said second flap means being downstream of and pivotably connected to the first flap means for providing variable exhaust stream expansion control in a first operating mode and exhaust stream deflection in a second operating mode;
• third variable position flap means pivotably connected to the second flap means proximate their respective downstream extremities, said third flap means partially defining a variable contour aircraft flight control surface;
• and
• an actuation system operatively connected to at least one of said flap means for synchronously moving said first, second and third flap means to control, in a predetermined relationship the exhaust stream flow path throat area and the exhaust stream flow path exit area.