Compact folding yoke in a folding rotor blade assembly

Patent metadata

Field	Value
Publication number	US-10569869-B2
Application number	US-201715845810-A
Country	US
Kind code	B2
Filing date	Dec 18, 2017
Priority date	Dec 18, 2017
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

First claim

What is claimed is:

1. A rotor blade assembly, comprising:
a hub spring operatively connected to a central mast;
a bilateral yoke connected to the hub spring;
a yoke arm pivotally connected to the bilateral yoke at a pivot point providing a first pivot axis;
bearings connecting the yoke arm to a rotor blade, the bearings positioned on the yoke arm outboard of the pivot point; and
a pitch horn connected to the rotor blade with a releasable pin and with a pivot pin providing a second pivot axis.

2. The rotor blade assembly of claim 1 , wherein the yoke arm is generally parallel with an adjacent yoke arm when the yoke arm is rotated about the pivot point to a folded position.

3. The rotor blade assembly of claim 2 , wherein the bilateral yoke further comprises:
an upper plate vertically aligned with a lower plate; and
the yoke arm is connected to the bilateral yoke between the upper plate and the lower plate.

4. The rotor blade assembly of claim 2 , wherein the bearings comprise an inboard beam, housing an inboard bearing, connected to the yoke arm and to the rotor blade outboard of the pivot point.

5. The rotor blade assembly of claim 4 , wherein the bilateral yoke further comprises:
an upper plate vertically aligned with a lower plate; and
the yoke arm is connected to the bilateral yoke between the upper plate and the lower plate.

6. The rotor blade assembly of claim 2 , wherein the bearings comprise an outboard beam, housing an outboard bearing, connected to a tip of the yoke arm and to the rotor blade outboard of the pivot point.

7. The rotor blade assembly of claim 1 , wherein the bilateral yoke further comprises:
an upper plate vertically aligned with a lower plate; and
the yoke arm is connected to the bilateral yoke between the upper plate and the lower plate.

8. The rotor blade assembly of claim 1 , wherein upon removal of the releasable pin and coaxial alignment of the first pivot axis with the second pivot axis, the yoke arm can rotate about the pivot point.

9. The rotor blade assembly of claim 1 , wherein the bearings further comprise:
an inboard beam, housing an inboard bearing, connected to the yoke arm and to the rotor blade outboard of the pivot point.

10. The rotor blade assembly of claim 1 , wherein the bearings further comprise:
an outboard beam, housing an outboard bearing, connected to a tip of the yoke arm and to the rotor blade outboard of the pivot point.

11. A method for folding a rotor blade assembly comprising a yoke arm connected to a rotor blade and connected to a bilateral yoke at a first pivotable connection including a first pivot axis, a pitch horn connected to the rotor blade at a releasable connection and at a second pivotable connection including a second pivot axis, and a set of bearings connected to the yoke arm outboard of the first pivot axis, comprising:
pitching the rotor blade;
releasing the releasable connection; and
rotating the yoke arm about the first pivotable connection and the second pivotable connection.

12. The method of claim 11 , wherein pitching the rotor blade includes axially aligning the first pivot axis with the second pivot axis.

13. The method of claim 12 , wherein the rotor blade assembly is connected to a nacelle pivotally mounted to a wing; and
pivoting the nacelle to a 90° nacelle angle.

14. The method of claim 13 , further comprising subsequent to rotating the yoke arm, pivoting the nacelle to a 0° nacelle angle.

15. The method of claim 12 , wherein the rotor blade assembly is connected to a nacelle pivotally mounted to a wing, further comprising, pivoting a wing tip of the wing.

16. The method of claim 12 , wherein the rotor blade assembly is mounted to a wing and the wing is mounted to a fuselage, further comprising, subsequent to rotating the yoke arm, swivelling the wing about its vertical axis to align with the fuselage.

17. The method of claim 11 , wherein:
the rotor blade assembly is connected to a nacelle pivotally mounted to a wing; and
pivoting the nacelle to a 90° nacelle angle.

18. The method of claim 17 , further comprising subsequent to rotating the yoke arm, pivoting the nacelle to a 0° nacelle angle.

19. The method of claim 11 , wherein the rotor blade assembly is connected to a nacelle pivotally mounted to a wing, further comprising, pivoting a wing tip of the wing.

20. The method of claim 11 , wherein the rotor blade assembly is mounted to a wing and the wing is mounted to a fuselage, further comprising, subsequent to rotating the yoke arm, swivelling the wing about its vertical axis to align with the fuselage.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Paulson Jared Mark
• Baldwin Tyler Wayne
• Cravener Kyle Thomas

Classifications

• B64C27/50 Primary

  Blades foldable to facilitate stowage of aircraft · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title

• B64C3/56

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title