Helicopter blade retention composite yoke

Patent metadata

Field	Value
Publication number	US-9308992-B2
Application number	US-201213407113-A
Country	US
Kind code	B2
Filing date	Feb 28, 2012
Priority date	Feb 28, 2012
Publication date	Apr 12, 2016
Grant date	Apr 12, 2016

Abstract

A rotary wing aircraft yoke is provided including an arcuate medial portion. A pair of arms extends from the medial portion and each terminates in a distal end. The yoke is made from multiple plies of glass and graphite fibers of varying orientations. The number of graphite plies increases along each arm from adjacent the medial portion to the distal end.

First claim

The invention claimed is:

1. A rotary wing aircraft yoke comprising:
an arcuate medial portion; and
a pair of arms, each extending from the medial portion and terminating in a distal end, the distal ends being substantially aligned such that an adjacent component is received within an opening formed between the distal ends of the pair of arms, each arm being made from plies of glass fibers and graphite fibers having varying configurations such that no two consecutive plies are identical in material and orientation, wherein at least a portion of the glass plies in the yoke have a ±4° fiber orientation;
wherein a number of graphite plies increases along each arm from adjacent the medial portion to the distal end and wherein the distal end of each arm is formed from a plurality of graphite plies and a plurality of glass plies arranged in an alternating configuration.

2. The rotary wing aircraft yoke according to claim 1 , wherein the pair of arms has a variable thickness.

3. The rotary wing aircraft yoke according to claim 1 , wherein the graphite plies have a ±45° or a 90° fiber orientation.

4. The rotary wing aircraft yoke according to claim 1 , wherein glass plies having a fiber orientation of ±4° make up approximately 49% of the distal end, graphite plies having a fiber orientation of ±45° make up approximately 41% of the distal end, and graphite plies having a fiber orientation of 90° make up approximately 10% of the distal end.

5. The rotary wing aircraft yoke according to claim 1 , wherein each arm connects to the medial portion by a bend, such that the medial portion has a first radius, and the bend connecting the arm to the medial portion has a second radius that is smaller than the first radius.

6. A rotary wing aircraft rotor mount assembly comprising:
a hub plate having a plurality of spokes and arcuate segments;
at least one rotor blade;
at least one yoke for connecting the blade to the hub plate including:
an arcuate medial portion;
a pair of arms, each extending from the medial portion and terminating in a distal end, the distal ends being substantially horizontally aligned such that an adjacent component is received within an opening formed between the distal ends of the pair of arms, each arm being made from plies of glass fibers and graphite fibers having varying configurations such that no two consecutive plies are identical in material and orientation, wherein at least a portion of the glass plies in the yoke have a ±4° fiber orientation;
wherein a number of graphite plies increases along each arm from adjacent the medial portion to the distal end and wherein the distal end of each arm is formed from a plurality of graphite plies and a plurality of glass plies arranged in an alternating configuration; and

an elastomeric bearing disposed between the medial portion of the yoke and an arcuate segment of the hub plate to accommodate the loading and displacement of the rotor blade, wherein a cap fastened to the elastomeric bearing adjacent the edges of the medial portion of the yoke holds the elastomeric bearing to the yoke.

7. The rotary wing aircraft rotor mount assembly according to claim 6 , wherein the elastomeric bearing includes an inner member in contact with the medial portion of the yoke and an outer member in contact with the arcuate segment of the hub plate.

8. The rotary wing aircraft rotor mount assembly according to claim 6 , further comprising:
a blade attachment connected to an end of the rotor blade; and
a mounting sleeve connected at a first end to the blade attachment and at a second end to the distal end of the yoke.

9. The rotary wing aircraft rotor mount assembly according to claim 8 , wherein a nylon pad is disposed adjacent a top surface and a bottom surface of the distal end of the yoke between the yoke and the mounting sleeve.

10. A method of manufacturing a rotary wing aircraft yoke comprising:
placing a plurality of plies of glass fibers of varying orientations around a tool head contoured to form at least two yokes facing each other, each yoke including a pair of arms, a distal end of each arm being substantially aligned such that an adjacent component is receivable within an opening formed between the distal ends, wherein at least a portion of the plurality of glass plies having a ±4° fiber orientation;
placing a plurality of plies of graphite fibers of varying orientations around at least a portion of the tool head to form a preform, the plurality of glass plies and the plurality of graphite plies having varying configurations such that no two consecutive plies are identical in material and orientation; and
curing the preform; and
machining a plurality of yokes from the preform.

11. The method of manufacturing a rotary wing aircraft yoke according to claim 10 , wherein the length of the tool head determines how many yokes will be manufactured.

12. The method of manufacturing a rotary wing aircraft yoke according to claim 10 , wherein consecutive graphite plies become increasingly shorter to create a tapered arm of the yoke.

13. The method of manufacturing a rotary wing aircraft yoke according to claim 10 , wherein the orientation or material of adjacent plies is not identical.

14. The method of manufacturing a rotary wing aircraft yoke according to claim 10 , wherein the graphite plies have a ±45° or a 90° fiber orientation.

15. The method of manufacturing a rotary wing aircraft yoke according to claim 10 , wherein glass plies having a fiber orientation of ±4° make up approximately 49% of the distal end, graphite plies having a fiber orientation of ±45° make up approximately 41% of the distal end, and graphite plies having a fiber orientation of 90° make up approximately 10% of the distal end.

Assignees

• Cabrera Pedro L
• Deyo Kenneth F
• Templeton David
• Laitenberger Kevin
• Sikorsky Aircraft Corp

Inventors

• Cabrera Pedro L
• Deyo Kenneth F
• Templeton David
• Laitenberger Kevin

Classifications

• B64C27/48 Primary

  Root attachment to rotor head · CPC title

• Y10T156/1052

  with cutting, punching, tearing or severing · CPC title