Patent ID: 8469308

Claim:
An aircraft, comprising: an engine exhaust duct; a nozzle assembly rigidly attached to and concentrically aligned with the engine exhaust duct, the nozzle assembly having a first nozzle and a second nozzle in gaseous communication with the engine exhaust duct, the first nozzle being configured to redirect engine exhaust gas in a different direction relative to redirected gas from the second nozzle; a rotatable valve disposed within the nozzle assembly, the valve being configured to rotate concentrically to the engine exhaust duct, the rotatable valve having: a scoop portion in gaseous communication the engine exhaust duct, the scoop portion being configured to redirect all engine exhaust gases leaving the engine exhaust duct to the first nozzle and/or the second nozzle; wherein the scoop is selectively contoured to reduce turbulent flow as the exhaust gas is channeled from the exhaust duct to the first nozzle and/or the second nozzle; a wing extension carried within a wing of the aircraft, the wing extension being configured to extend from the wing in an extended position and retract within the wing while in a retracted position; a vertical lift system carried by the wing of the aircraft, the lift system being configured to create vertical flight; the lift system comprising: a conduit extending through the thickness of the wing; a rotor positioned within the conduit; and a vane operably associated with the rotor, the vane being configured to redirect rotor downwash from the rotor.