Anti-Torque and yaw-control system for a rotary-wing aircraft

• US 6,755,374 B1
• Filed: 01/27/2003
• Issued: 06/29/2004
• Est. Priority Date: 01/27/2003
• Status: Expired due to Fees

• Current Assignee: Franklin D. Carson
• Original Assignee: Franklin D. Carson
• Inventors: Carson, Franklin D.
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Sukman, Gabriel S.
• Application Number:
  US10/353,162
• Time in Patent Office: 519 Days
• Field of Search: 244/17.11, 244/17.19, 244/17.21, 244/765, 244/91
• US Class Current: 244/17.19
• CPC Class Codes: B64C 2027/8245 using air jets
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft

Abstract

A preferred embodiment of a rotary-wing aircraft comprises a main rotor, a tail boom extending through an area of downwash from the main rotor, and a linear nozzle fixedly coupled to 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. A preferred embodiment also comprises a yaw-control device movably coupled to the tail boom and having an opening formed therein for discharging fluid in a direction away from the yaw-control device and into the area of downwash from the main rotor.

Claims

1. 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.

2. The rotary-wing aircraft of claim 1, wherein the first opening is positioned within the plenum chamber.

3. The rotary-wing aircraft of claim 1, wherein the yaw-control device comprises a first and second nozzle mounted in the respective first and second openings.

4. The rotary-wing aircraft of claim 3, wherein the first and second nozzles are linear nozzles.

5. The rotary-wing aircraft of claim 1, wherein the yaw-control device comprises an outer skin and the first and second openings are formed in the outer skin.

6. The rotary-wing aircraft of claim 5, wherein the yaw-control device further comprises a plurality of frame members and a plurality of stringers, the outer skin being fixedly coupled to the frame members and the frame members being interconnected by the stringers.

7. The rotary-wing aircraft of claim 1, further comprising an actuator mechanically coupled to the yaw-control device and the tail boom for rotating the yaw-control device in relation to the tail boom.

8. The rotary-wing aircraft of claim 1, further comprising a first and a second collar fixedly coupled to the tail boom, a first flange fixedly coupled to the yaw-control device and rotatably coupled to the first collar, and a second flange fixedly coupled to the yaw-control device and rotatably coupled to the second collar.

9. The rotary-wing aircraft of claim 1, wherein the yaw-control device is substantially tubular.

10. The rotary-wing aircraft of claim 1, wherein the yaw-control device has a substantially circular cross-section.

11. The rotary-wing aircraft of claim 1, wherein the yaw-control device has a substantially oval cross-section.

12. The rotary-wing aircraft of claim 1, wherein the yaw-control device has a substantially teardrop-shaped cross-section.

13. The rotary-wing aircraft of claim 1, further comprising a seal located between the tail boom and the yaw-control device.

14. The rotary-wing aircraft of claim 1, wherein the pressurized fluid is discharged from the second opening in a direction away from the yaw-control device.

15. The rotary-wing aircraft of claim 1, further comprising a second linear nozzle fixedly coupled to the tail boom and having an opening extending along the tail boom, the second linear nozzle being adapted to discharge a sheet of fluid in a direction substantially tangential to the outer surface of the tail boom.

16. The rotary-wing aircraft of claim 1, wherein the yaw-control device is selectively positionable in relation to the tail boom in response to input from a pilot of the rotary-wing aircraft.

17. The rotary-wing aircraft of claim 1, further comprising a fan in fluid communication with the plenum chamber.

18. The rotary-wing aircraft of claim 17, further comprising an air intake positioned on a top portion of the fuselage and being in fluid communication with the fan.

19. A rotary-wing aircraft, comprising:

a main rotor;

a tail boom extending through an area of downwash from the main rotor;

a linear nozzle fixedly coupled to 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 rotatably coupled to the tail boom and having an opening formed therein for discharging fluid in a direction away from the yaw-control device and into the area of downwash from the main rotor when the rotary-wing aircraft is hovering.

20. The rotary-wing aircraft of claim 19, wherein the yaw-control device is rotatably coupled to the tail boom so that an orientation of the opening in relation to the tail boom can be altered thereby altering a circulation pattern of the downwash from the main rotor around the tail boom.

21. The rotary-wing aircraft of claim 19, wherein the yaw-control device comprises a linear nozzle mounted in the opening.

22. The rotary-wing aircraft of claim 19, wherein the yaw-control device has a second opening formed therein and positioned within a plenum chamber formed by the tail boom, and the yaw-control device receives the fluid from the plenum chamber by way of the second opening.

23. The rotary-wing aircraft of claim 19, wherein the yaw-control device comprises an outer skin and the opening is formed in the outer skin.

24. The rotary-wing aircraft of claim 23, wherein the yaw-control device further comprises a plurality of frame members and a plurality of stringers, the outer skin being fixedly coupled to the frame members and the frame members being interconnected by the stringers.

25. The rotary-wing aircraft of claim 19, further comprising an actuator mechanically coupled to the yaw-control device and the tail boom for rotating the yaw-control device in relation to the tail boom.

26. The rotary-wing aircraft of claim 19, further comprising a first and a second collar fixedly coupled to the tail boom, a first flange fixedly coupled to the yaw-control device and rotatably coupled to the first collar, and a second flange fixedly coupled to the yaw-control device and rotatably coupled to the second collar.

27. The rotary-wing aircraft of claim 19, wherein the yaw-control device is substantially tubular.

28. The rotary-wing aircraft of claim 19, wherein the yaw-control device has a substantially circular cross-section.

29. The rotary-wing aircraft of claim 19, wherein the yaw-control device has a substantially oval cross-section.

30. The rotary-wing aircraft of claim 19, wherein the yaw-control device has a substantially teardrop-shaped cross-section.

31. The rotary-wing aircraft of claim 19, wherein the yaw-control device is selectively positionable in relation to the tail boom in response to input from a pilot of the rotary-wing aircraft.

32. 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;

a linear nozzle mounted on the tail boom and having an opening extending along the tail boom for discharging a sheet of the pressurized fluid in a direction substantially tangential to an outer surface of the tail boom and toward a yaw-control device; and

the yaw-control device, comprising an outer skin defining an internal volume within the yaw-control device for receiving the pressurized fluid, the outer skin having an opening formed therein for discharging the pressurized fluid from the internal volume in a direction away from the yaw-control device and into the area of downwash from the main rotor when the rotary-wing aircraft is hovering, wherein the yaw-control device is rotatably coupled to the tail boom so that an orientation of the opening can be altered in relation to the tail boom thereby altering a circulation pattern of the rotor downwash around the tail boom.

33. A method of counteracting main-rotor torque and controlling yaw in a helicopter having a main rotor and a tail boom located within an area of downwash from the main rotor, comprising:

altering a direction of travel of the downwash from the main rotor by directing a first flow of fluid along an outer surface of the tail boom to produce a layer of fluid flow along at least a portion of the outer surface; and

further altering the direction of travel of the downwash from the main rotor by using a rotatable yaw-control member to introduce a second flow of fluid into the area of downwash from the main rotor in a direction away from the yaw-control device when the rotary-wing aircraft is hovering.

34. 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 having a squared edge, wherein the yaw-control device is coupled to a lower portion of the tail boom so that an opening is formed between the yaw-control device and the tail boom, the pressurized air from the plenum chamber is discharged through the opening, and the yaw-control device is rotatable in relation to the tail boom so that a direction in which the pressurized air flows away from the yaw-control device is variable.

35. 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 first opening is positioned within the plenum chamber, 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.

36. 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, 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, and the yaw-control device comprises a first and second nozzle mounted in the respective first and second openings.

37. A rotary-wing aircraft, comprising:

a main rotor;

a tail boom extending through an area of downwash from the main rotor;

a linear nozzle fixedly coupled to 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 movably coupled to the tail boom, wherein the yaw control device has a first opening formed therein for discharging fluid in a direction away from the yaw-control device and into the area of downwash from the main rotor, the yaw control device has a second opening formed therein and positioned within a plenum chamber formed by the tail boom, and the yaw-control device receives the fluid from the plenum chamber by way of the second opening.