Patent ID: 7628356

Claim:
A yaw control device for an aircraft fitted with a supersonic nozzle of rectangular cross section, said nozzle having a stationary supersonic throat extended by a diverging portion, the supersonic throat having an outlet downstream of which supersonic flow occurs, said device comprising at least one jet control surface in the form of an airfoil disposed fully within the diverging portion of the nozzle to be completely in said supersonic flow, said at least one jet control surface being disposed vertically so as to be movable about a vertical axis of rotation, to generate a lateral force when in a deflected position, thereby enabling the aircraft to turn about its yaw axis, the device further comprising a stationary element disposed upstream from at least one jet control surface in the nozzle, said stationary element presenting an aerodynamic leading edge in order to protect the control surface from the supersonic flow in the nozzle.