Patent ID: 6755374
Filing Date: 2004-06-29
Classification: B64C

Abstract:
A rotary-wing aircraft, comprising:a fuselage; a main rotor rotatably coupled to the fuselage; a tail boom fixedly coupled to the fuselage so that a least a portion of the tail boom is located within an area of downwash from the main rotor, the tail boom defining a plenum chamber therein for holding pressurized fluid; a linear nozzle mounted on the tail boom and having an opening extending along the tail boom for discharging a sheet of fluid in a direction substantially tangential to an outer surface of the tail boom; and a yaw-control device defining an internal volume therein, wherein the yaw-control device is rotatably coupled to a lower portion of the tail boom and has a first and a second opening formed therein, the internal volume receives the pressurized fluid from the plenum chamber by way of the first opening, and the yaw-control device discharges the pressurized fluid from the internal volume and into the area of downwash from the main rotor by way of the second opening when the rotary-wing aircraft is hovering.