Rotor blade control horn arrangements

Patent metadata

Field	Value
Publication number	US-10486805-B2
Application number	US-201715721519-A
Country	US
Kind code	B2
Filing date	Sep 29, 2017
Priority date	Oct 19, 2016
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A control horn arrangement includes a control horn body with an inboard end and an opposed outboard end. The control horn body defines a torque tube axis which extends between the inboard and outboard end of the control horn body. An inner flange and an outer flange are disposed on the outboard end of the control horn body. The inner flange and the outer flange extend about the torque tube axis and define between one another a receptacle to fix a torque tube to the outboard end of the control horn body.

First claim

What is claimed is:

1. A control horn arrangement connection to a torque tube, comprising:
a control horn body with an inboard end and an opposed outboard end, the control horn body defining a torque tube axis extending between the inboard and outboard end of the control horn body;
an inner annular flange extending from the control horn body outboard end; and
an outer annular flange extending from the control horn body outboard end,
wherein the inner annular and outer annular flanges extend about and are co-axial with the torque tube axis and define a receptacle to fix the torque tube to the outboard end of the control horn body.

2. The control horn arrangement as recited in claim 1 , wherein the inner annular flange extends continuously about the torque tube axis.

3. The control horn arrangement as recited in claim 1 , wherein the outer annular flange extends only partially about the torque tube axis.

4. The control horn arrangement as recited in claim 1 , wherein the outer annular flange has a pressure-side segment and an opposed suction-side segment, the suction side being separated from the pressure side by a gap.

5. The control horn arrangement as recited in claim 4 , wherein the gap is disposed on a leading edge of the control horn body.

6. The control horn arrangement as recited in claim 4 , wherein the gap is disposed on a trailing edge of the control horn body.

7. The control horn arrangement as recited in claim 4 , further comprising a closure connecting the suction-side segment to the pressure-side segment.

8. The control horn arrangement as recited in claim 1 , wherein the outer annular flange radially overlaps the inner annular flange.

9. The control horn arrangement as recited in claim 1 , wherein the inner annular flange extends axially along the torque tube axis to a location axially beyond the outer annular flange.

10. The control horn arrangement as recited in claim 1 , wherein the outer annular flange is angled away from the inner annular flange.

11. The control horn arrangement as recited in claim 1 , wherein an axially outer portion of the outer annular flange is spaced apart further from the inner annular flange than an axially inner portion of the outer annular flange.

12. The control horn arrangement as recited in claim 1 , wherein the inner annular flange has torque tube-facing surface with an adhesive layer on the inner annular flange torque tube-facing surface.

13. The control horn arrangement as recited in claim 1 , wherein the outer annular flange has torque tube-facing surface with an adhesive layer on the outer annular flange torque tube-facing surface.

14. The control horn arrangement as recited in claim 1 , further comprising a torque tube seated in the receptacle and bonded to the inner and outer annular flanges of the control horn body.

15. A rotorcraft having a rotor assembly with the control horn arrangement as recited in claim 1 .

16. A rotor assembly, comprising:
a control horn body with an inboard end and an opposed outboard end, the control horn body defining a torque tube axis extending between the inboard and outboard end of the control horn body,
wherein the control horn body has an inner annular flange and an outer annular flange disposed on the outboard end of the control horn body, the inner annular flange and the outer annular flange being co-axial with and extending about the torque tube axis, and defining a receptacle;
a torque tube with an inboard end seated in the receptacle and opposed suction-side and pressure-side surfaces extending longitudinally from the inboard end, the torque tube inboard end defining an inner gap between the torque tube inboard end and the inner annular flange, the torque tube inboard end defining an outer gap between the torque tube inboard end and the outer annular flange;
an inner adhesive layer disposed within the inner gap between the inboard end of the torque tube and the inner annular flange, the inner adhesive layer bonding the torque tube to the control horn body; and
an outer adhesive layer disposed within the outer gap between the inboard end of the torque tube and the outer annular flange, the outer adhesive layer bonding the torque tube to the control horn body.

17. The rotor assembly as recited in claim 16 , wherein the outer annular flange radially overlaps the inner annular flange, wherein the inner annular flange extends axially beyond the outer annular flange, wherein the outer annular flange is angled away from the inner annular flange, and wherein an axially outer portion of the outer annular flange is spaced apart further from the inner annular flange than an axially inner portion of the outer annular flange.

18. The rotor assembly as recited in claim 16 , further comprising an ice protection circuit fixed to a leading edge of the torque tube, the ice protection circuit radially overlapping the inner annular flange.

19. The rotor assembly as recited in claim 16 , wherein the outer annular flange has a pressure side and an opposed suction side, the suction side being separated from the pressure side by a gap disposed on a leading edge of the control horn body, wherein the suction side is separated from the pressure side by a gap disposed on a trailing edge of the control horn body.

20. A rotorcraft anti-torque system having a rotor assembly as recited in claim 16 .

Assignees

• Sikorsky Aircraft Corp

Inventors

• Rothermich Brian
• Meyer Leon M

Classifications

• B64D15/12

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• B64C27/78

  in association with pitch adjustment of blades of anti-torque rotor · CPC title

• B64C27/473 Primary

  Constructional features · CPC title

• B64C11/32

  mechanical · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title