Rotorcraft rotor assemblies

Patent metadata

Field	Value
Publication number	US-10604246-B2
Application number	US-201715406316-A
Country	US
Kind code	B2
Filing date	Jan 13, 2017
Priority date	Jan 21, 2016
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

An attachment assembly for coupling a rotary blade to a hub includes a hollow shear pin, a nut cap, and a tensioning fastener. The hollow shear pin defines an attachment axis. The nut cap abuts the shear pin along the attachment axis. The tensioning fastener is seated within the shear pin, is threadably engaged to the nut cap, and has an axial length that is smaller than an axial length of the shear pin to fix a rotary blade to a rotor assembly within a profile of the rotary blade.

First claim

What is claimed is:

1. An attachment assembly for coupling elements of an aircraft rotor assembly, comprising:
a hollow shear pin defining an attachment axis and having a first end and a second end, the hollow shear pin comprising a seat and a shear pin flange disposed at the second end along the attachment axis;
a nut cap abutting the first end of the shear pin along the attachment axis, the nut cap having a nut cap flange; and
a tensioning fastener seated within the shear pin abutting the seat of the second end and threadably engaged to the nut cap, wherein the tensioning fastener has an axial length that is smaller than an axial length of the shear pin, whereby the nut cap flange and shear pin flange fix the coupled elements.

2. The attachment assembly as recited in claim 1 , wherein the seat is an internal annular seat disposed within an interior of the hollow shear pin.

3. The attachment assembly as recited in claim 2 , wherein the internal annular seat is axially offset from both the first end and the second end of the shear pin.

4. The attachment assembly as recited in claim 1 , wherein the shear pin flange is a compression flange extending radially outward from the second end of the shear pin.

5. The attachment assembly as recited in claim 1 , wherein the shear pin has a rim disposed around the attachment axis and is oblique relative to the attachment axis defined by the shear pin.

6. The attachment assembly as recited in claim 1 , wherein the nut cap has an annular portion, the annular portion defining therein a female threaded segment.

7. The attachment assembly as recited in claim 6 , wherein the annular portion of the nut cap defines therein an anti-rotation feature, the anti-rotation feature being axially stacked relative to the female threaded segment.

8. The attachment assembly as recited in claim 6 , wherein the nut cap has a compression flange disposed on an end of the nut cap opposite the female threaded segment.

9. The attachment assembly as recited in claim 6 , wherein the nut cap has a rim portion disposed on an end of the nut cap opposite the female threaded segment and oblique relative to the attachment axis defined by the shear pin.

10. The attachment assembly as recited in claim 1 , wherein the tensioning fastener is asymmetrically arranged between opposed first and second ends of the shear pin.

11. The attachment assembly as recited in claim 1 , further including a prong spacer extending about the shear pin.

12. The attachment assembly as recited in claim 11 , wherein the shear pin defines a necked segment axially adjacent to the prong spacer.

13. The attachment assembly as recited in claim 1 , further including a bushing seated about the shear pin.

14. A rotary blade of an aircraft, comprising:
a blade body defining an attachment aperture with a recessed seat extending about the attachment aperture; and
an attachment assembly as recited in claim 1 seated in attachment aperture, wherein the nut cap or the shear pin flange abuts the recessed seat within an aerodynamic profile of the blade body to fix the rotary blade to a rotor assembly.

15. The rotary blade as recited in claim 14 , further including a plug seated in the attachment aperture, wherein a surface of the plug opposite the attachment assembly is conformal with the aerodynamic profile of the blade body.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Baskin Bryan K
• Higbie Robert
• D'Anna Frank P
• Smith Ryan

Classifications

• F16B2/065

  using screw-thread elements (F16B2/08 - F16B2/12 take precedence) · CPC title

• B64C27/48 Primary

  Root attachment to rotor head · CPC title

• B64C27/10

  arranged coaxially · CPC title