Aerodynamic blade attachment for a bearingless rotor of a helicopter

Patent metadata

Field	Value
Publication number	US-9359071-B2
Application number	US-201313785696-A
Country	US
Kind code	B2
Filing date	Mar 5, 2013
Priority date	Apr 18, 2012
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

An aerodynamic blade attachment ( 1 ) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade ( 2 ) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam ( 3 ); a control cuff ( 4, 22 ) enclosing and extending along said flexbeam ( 3 ) and a separable junction arrangement between said flexbeam ( 3 ), said control cuff ( 4 ) and said root end of said airfoil blade ( 2 ). Said junction arrangement is mechanical between said flexbeam ( 3 ), said control cuff ( 4 ) and said root end of said airfoil blade ( 2 ). Removable fasteners ( 5, 6 ) connect said root end of said airfoil blade ( 2 ) and said control cuff ( 4 ) with said flexbeam ( 3 ). Said junction arrangement comprises fairing means ( 10, 27, 28, 31, 32 and 39 ) encompass the removable fasteners ( 5, 6 ) and said flexbeam ( 3 ).

First claim

What is claimed is:

1. An aerodynamic blade attachment for a bearingless rotor of a helicopter, comprising:
an airfoil blade having a tip end and a root end forming opposite ends thereof and having a pitch axis from the tip end to the root end;
a flexbeam;
a control cuff enclosing and extending along at least a predominant portion of the flexbeam; and
a separable junction arrangement between the flexbeam, the control cuff and the root end of the airfoil blade, the junction arrangement being mechanical between the flexbeam, the control cuff and the root end of the airfoil blade with a removable main bolt and a removable supporting bolt respectively removable connecting the root end of the airfoil blade and the control cuff with the flexbeam, the junction arrangement comprising fairing means encompassing the main bolt and the supporting bolt and the flexbeam, wherein the fairing means are formed with a first circular segment and a second circular segment at a free end of the control cuff, the root end of the blade having corresponding first and second circular segments, a first center of the first circular segment being aligned with a central axis of the main bolt, a second center of the second circular segment being offset from the first center and between the central axis of the main bolt and a central axis of the supporting bolt, a radius of the second circular segment being greater than a radius of the first circular segment.

2. The aerodynamic blade attachment according to claim 1 , wherein the fairing means are provided by the control cuff.

3. The aerodynamic blade attachment according to claim 1 , wherein the fairing means are provided by the root end of the airfoil blade.

4. The aerodynamic blade attachment according to claim 1 , wherein the fairing means are provided by at least one supplemental profile.

5. The aerodynamic blade attachment according to claim 4 , wherein the at least one supplemental profile, is mounted either to the root end of the airfoil blade and/or to the control cuff.

6. The aerodynamic blade attachment according to claim 1 , wherein the offset is 10-15 mm.

7. The aerodynamic blade attachment according to claim 1 , wherein the radius of the first circular segment or the radius of the second circular segment is greater than the distance from the main bolt or the supporting bolt to the free end.

8. The aerodynamic blade attachment according to claim 1 , wherein the main bolt and the supporting bolt are asymmetric with regard to a middle axis of the flexbeam.

9. The blade attachment according to claim 8 , wherein the main bolt is arranged in the area of a 10-30% chord of a profile section of the airfoil blade, respectively slightly in front of the chord towards a leading edge of the profile section.

10. The blade attachment according to claim 8 , wherein the main bolt is hollow.

11. The blade attachment according to claim 8 , wherein the main bolt and the supporting bolt together with any screw nuts are integrated aerodynamically into respectively associated corrugations of the fairing means.

12. The blade attachment according to claim 8 , wherein the flexbeam head is fork shaped to accommodate the main bolt and the supporting bolt.

13. The blade attachment according to claim 8 , wherein the root end of the airfoil blade is fork shaped, the flexbeam has a flat stepped cross section and the root end of the airfoil blade is arranged inbetween the control cuff and the flexbeam.

14. The blade attachment according to claim 1 , wherein the control cuff is provided with a frontal slit and a rear slit adjacent to the flexbeam.

15. The blade attachment according to claim 1 , wherein the first circular segment is contiguous with the second circular segment.

16. A blade assembly for a bearingless helicopter rotor, comprising:
a flexbeam having a first end and a second end, the first end being configured to couple to a rotor head;
a control cuff extending about a portion of the flexbeam, the control cuff having a free end with an arcuate profile having a first circular segment and a second circular segment;
a blade extending from a root to a tip, the blade having a pitch axis extending from the root to the tip, the root having a corresponding arcuate profile to the control cuff with a corresponding first circular segment and a corresponding second circular segment;
a first bolt coupling the control cuff free end to the blade root; and
a second bolt coupling the control cuff free end to the blade root, wherein the first circular segment is concentric with the first bolt, the second circular segment has a center offset from the first bolt and second bolt and positioned between a central axis of the first bolt and a central axis of the second bolt, the second circular segment has a different radius from the first circular segment, and wherein the first bolt or the second bolt couples the flexbeam second end to the blade root and control cuff free end.

17. The blade assembly of claim 16 , wherein the arcuate profile of the control cuff free end is a convex arcuate profile.

18. The blade assembly of claim 16 , wherein the cuff has a generally planar upper surface and the arcuate profile lies within the general plane of the upper surface.

19. A rotorcraft comprising: a rotor head;
a flexbeam having a first end and a second end, the first end being coupled to the rotor head;
a control cuff extending about a portion of the flexbeam, the control cuff having a free end with an arcuate profile having a first circular segment and a second circular segment;
a blade extending from a root to a tip, the blade having a pitch axis extending from the root to the tip, the root having a corresponding arcuate profile to the control cuff with a corresponding first circular segment and a corresponding second circular segment; a first bolt coupling the control cuff free end to the blade root; and a second bolt coupling the control cuff free end to the blade root, wherein the first circular segment is concentric with the first bolt, the second circular segment has a center offset from the first bolt and second bolt and positioned between a central axis of the first bolt and a central axis of the second bolt, the second circular segment has a different radius from the first circular segment, and wherein the first bolt or the second bolt couples the flexbeam second end to the blade root and control cuff free end.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Kuntze-Fechner Gerald
• Bauer Markus
• Ortner Martin

Classifications

• B64C27/50

  Blades foldable to facilitate stowage of aircraft · CPC title

• B64C27/33 Primary

  having flexing arms · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title

• B64C27/473 Primary

  Constructional features · CPC title