Abstract: A gas turbine engine flight maneuverable nozzle for installation within an aircraft wing or the like is provided with pivotably connected convergent and divergent flaps partially defining an exhaust stream flow path. A third flap, pivotably connected to the divergent flap, partially defines the wing control surface contour. In the cruise and flight maneuver modes, an actuation system provides synchronous movement of the convergent and divergent flaps to control, in a predetermined relationship, the areas of the exhaust stream flow path throat and exit. A vectoring actuator, carried by the main actuator, overrides the main actuator in the flight maneuvering mode and causes the divergent flap to pivot downward, thus deflecting the exhaust stream. Simultaneously, the control surface contour defining flap is repositioned to increase the control surface camber thereby increasing lift. Flow separation from the wing control surface is prevented by the effect of super-circulation due to the exhaust stream.

Abstract: An extendable exhaust nozzle for rocket motors that can be deployed from a stored compact position to an extended position. The interior surface of the nozzle is provided with a thin layer of a nickel-titanium alloy that is characterized by its ability to revert back to its original shape, subsequent to being deformed. The alloy is applied to the nozzle surfaces while in extended form, and then the nozzle is folded and stored. It can then be deployed to its extended shape at any time by heating the nozzle.

Abstract: A system for controlling the annular nozzle throat area (and hence the tht) of a solid-propellant rocket by means of a pintle or plug the position of which is caused to vary in response to pressure variations within the combustion chamber of the rocket.

Abstract: A pintle screwed into an explosive bolt and released when the bolt is exped is used to alter the area of a rocket nozzle while the rocket is in flight.