Pivoting spanwise-flow redirector for tiltrotor aircraft

• US 6,161,800 A
• Filed: 05/04/1999
• Issued: 12/19/2000
• Est. Priority Date: 05/04/1999
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Liu, John, McVeigh, Michael A., Mayer, Robert J.
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Bergin, James S.
• Application Number:
  US09/304,938
• Time in Patent Office: 595 Days
• Field of Search: 244/6, 244/7 R, 244/7 A, 244/7 C, 244/56, 244/66, 244/17.19
• US Class Current: 244/7.00R
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 9/32 Air braking surfaces
• CPC Class Codes: B64C 9/326 associated with fuselages
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A tiltrotor aircraft includes a spanwise-flow redirector having a pair of flow-redirection panels respectively mounted on the aircraft'"'"'s mid-fuselage area for rotation about a panel pivot axis between a stowed position and a deployed position. In the stowed position, each panel is substantially flush with an adjacent surface of the mid-fuselage area. In the deployed position, each panel is raised into the path of one of the inbound spanwise flows generated by the aircraft'"'"'s rotors during hover operation, whereupon each panel redirects the respective one of the inbound spanwise flows either forward or aft of the other inbound spanwise flow. In this manner, the deployed panels prevent stagnation of the inbound spanwise flow atop the mid-fuselage area while further serving to minimize re-ingestion of merged spanwise flow into the rotors, resulting in decreased airframe download forces, increased rotor thrust, and reduced noise levels during hover operation.

Claims

1. In a tiltrotor aircraft including a fuselage having a centerline axis, a pair of generally-oppositely-extending wings on the fuselage separated by a mid-fulselage area, and a driven rotor mounted on each wing for rotation between a forward-flight position and a hover position, and wherein the driven rotors in the hover position generate a first spanwise flow toward the mid-fuselage area over one of the wings and a second spanwise flow toward the mid-fuselage area over another of the wings, the improvement comprising a spanwise-flow redirector including:

at least one panel mounted on the aircraft for pivotal movement about a respective panel pivot axis between a first position and a second position, each panel pivot axis forming a respective first acute angle with a vertical reference plane containing the centerline axis of the fuselage;

wherein the first position is characterized in that the at least one panel is substantially flush with an adjacent surface of at least one of the group consisting of a wing and the mid-fuselage area; and

wherein the second position is characterized in that the at least one panel projects above the adjacent surface of the at least one of the group consisting of the wing and the mid-fuselage area to substantially redirect the first spanwise flow generally forward of the second spanwise flow while substantially redirecting the second spanwise flow generally aft of the first spanwise flow.

2. The tiltrotor aircraft of claim 1, wherein the flow redirector includes a first panel and a second panel, and wherein the respective second positions for the first and second panels are characterized in that the first panel redirects the first spanwise flow and the second panel redirects the second spanwise flow.

3. The tiltrotor aircraft of claim 2, wherein each panel has a flow-redirecting surface, and wherein the second position is further characterized in that the flow-redirecting surface of each panel forms a respective second acute angle with a horizontal reference plane.

4. The tiltrotor aircraft of claim 3, wherein second acute angle is no greater than about 60 degrees.

5. The tiltrotor aircraft of claim 3, wherein the second acute angle is no less than about 30 degrees.

6. The tiltrotor aircraft of claim 2, wherein the first panel and the second panel are positioned side-by-side atop the mid-fuselage area.

7. The tiltrotor aircraft of claim 6, wherein the first and second panel pivot axes are collinear.

8. The tiltrotor aircraft of claim 1, wherein each of the at least one panels extends forward on the aircraft to a first point which is aft of an aft-most portion of a leading edge of one wing.

9. The tiltrotor aircraft of claim 8, wherein the first point is aft of the forward-most leading edge by no greater than about ten percent of the maximum root chord length of the one wing.

10. The tiltrotor aircraft of claim 8, wherein each of the at least one panels extends afterward on the aircraft to a second point which is aft of the aft-most portion of the leading edge by at least about seventy-five percent of the maximum root chord length of the one wing.

11. The tiltrotor aircraft of claim 10, wherein the one wing includes a flap pivoting about a flap hinge axis between an undeflected position and a deflected position;

and wherein the second point is aft of the flap hinge axis and forward of an aft-most portion of a trailing edge of the flap when the flap is in the undeflected position.

12. A flow redirector adapted for use in a tiltrotor aircraft, wherein the aircraft includes a fuselage having a centerline axis, a pair of generally-oppositely-extending wings on the fuselage separated by a mid-fuselage area, and a driven rotor mounted on each wing for rotation between a forward-flight position and a hover position, and wherein the driven rotors in the hover position generate a first spanwise flow toward the mid-fuselage area over one of the wings and a second spanwise flow toward the mid-fuselage area over another of the wings, the flow redirector comprising:

a first panel mounted on one of the fuselage and one wing for pivotal movement about a first panel pivot axis between a first position, wherein the first panel is substantially flush with at least one of the fuselage and an upper surface of the one wing, and a second position, wherein a surface of the first panel substantially redirects spanwise flow over the one wing generally forward of spanwise flow over the other wing;

a second panel mounted on one of the fuselage and the other wing for pivotal movement about a second panel pivot axis between a first position, wherein the second panel is substantially flush with at least one of the fuselage and an upper surface of the other wing, and a second position, wherein a surface of the second panel substantially redirects spanwise flow over the other wing generally aft of spanwise flow over the one wing; and

wherein the first panel pivot axis forms a first acute angle with a vertical reference plane containing the centerline axis of the fuselage, and the second panel pivot axis forms a second acute angle with a vertical reference plane containing the centerline axis of the fuselage.

13. The flow redirector of claim 12, wherein each panel has a flow-redirecting surface, and wherein the second position for each panel is further characterized in that the flow-redirecting surface of each panel forms a respective third acute angle with a horizontal reference plane.

14. The flow redirector of claim 13, wherein the third acute angle is no greater than about 60 degrees.

15. The tiltrotor aircraft of claim 13, wherein the third acute angle is no less than about 30 degrees.

16. The tiltrotor aircraft of claim 12, wherein the first panel and the second panel are positioned side-by-side atop the mid-fuselage area.

17. The tiltrotor aircraft of claim 16, wherein the first and second panel pivot axes are collinear.

18. A method for operating a tiltrotor aircraft, wherein the aircraft includes a fuselage having a centerline axis, a pair of generally-oppositely-extending wings on the fuselage separated by a mid-fuselage area, and a pair of driven rotors respectively mounted on each of a pair of wings for rotation between a forward-flight position and a hover position, and wherein the driven rotors in the hover position generate a first spanwise flow toward the mid-fuselage area over one of the wings and a second spanwise flow toward the mid-fuselage area over another of the wings, the method including:

controllably raising at least one panel, mounted on at least one of the group consisting of the fuselage, the one wing and the other wing, from a stowed position to a deployed position, wherein the stowed position is characterized in that the at least one panel is substantially flush with an adjacent surface of at least one of the group consisting of the fuselage, the one wing and the other wing, and wherein the deployed position is characterized in that the at least one panel substantially redirects the first spanwise flow generally forward of the second spanwise flow while substantially redirecting the second spanwise flow generally aft of the first spanwise flow.

19. The method of claim 18, wherein controllably raising the at least one panel includes pivoting the at least one panel about a respective panel pivot axis between the first position and the second position, and wherein each panel pivot axis forms a respective first acute angle with a vertical reference plane containing the centerline axis of the fuselage.

20. The method of claim 18, further including lowering the at least one raised panel when the aircraft achieves an airspeed in forward flight greater than a predetermined threshold airspeed.

21. The method of claim 20, wherein the predetermined threshold airspeed is about 40 knots.