Foldable aircraft wings

Patent metadata

Field	Value
Publication number	US-11485474-B2
Application number	US-201916580762-A
Country	US
Kind code	B2
Filing date	Sep 24, 2019
Priority date	Feb 1, 2019
Publication date	Nov 1, 2022
Grant date	Nov 1, 2022

Abstract

Foldable aircraft wings are disclosed. An example aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs. The hinge also includes a tip transition portion including tip hinge ribs, where respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs.

First claim

What is claimed is:

1. An aircraft comprising:
a foldable wing including a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion, the hinge including:
a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs; and
a tip transition portion including tip hinge ribs, respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs, wherein the respective ones of the wing hinge ribs are to couple to corresponding respective ones of the tip hinge ribs to define a hinge interface, and wherein the wing hinge ribs and the tip hinge ribs provide single-shear reaction at the hinge interface when the hinge interface is subjected to single-shear loading.

2. The aircraft of claim 1 , wherein at least a portion of the hinge provides a double-shear reaction.

3. The aircraft of claim 2 , wherein the portion of the hinge that is to provide the double-shear reaction includes a latch interface.

4. The aircraft of claim 1 , wherein the hinge is to provide a primary load path to transfer a load from the foldable wing portion to the fixed wing portion.

5. The aircraft of claim 4 , wherein the hinge provides a primary wing bending/spanwise load path and a stream/chord wise stiffening load path.

6. The aircraft of claim 1 , further including a hinge pin assembly having a first hinge pin, a second hinge pin and a third hinge pin, the first hinge pin supported by a first wing hinge rib and a first tip hinge rib, the second hinge pin supported by a second wing hinge rib and a second tip hinge rib, and the third hinge pin having a first end supported by a third wing hinge rib and a third tip hinge rib and a second end opposite the first end supported by a fourth wing hinge rib and a fourth tip hinge rib.

7. An aircraft comprising:
a foldable wing including a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion, the hinge including:
a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs; and
a tip transition portion including tip hinge ribs, respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs, wherein the respective ones of the wing hinge ribs and wing stub ribs couple to corresponding respective ones of the tip hinge ribs along a latch interface, and wherein the wing hinge ribs and the wing stub ribs provide double-shear reaction at the latch interface when the hinge is subjected to single-shear loading.

8. The aircraft of claim 7 , wherein at least one of the wing hinge ribs, the wing stub ribs and the tip hinge ribs includes a latch pin aperture.

9. The aircraft of claim 8 , wherein at least one of the wing hinge ribs and the tip hinge ribs includes a latch pin aperture to receive a latch pin.

10. A foldable aircraft wing, comprising:
a foldable wing tip;
a fixed wing portion; and
a hinge to rotatably couple the foldable wing tip to the fixed wing portion, the hinge including:
a wing transition portion including a first wing hinge rib, a second wing hinge rib, a third wing hinge rib, and a fourth wing hinge rib, the wing transition portion further including a first wing stub rib coupled to the first wing hinge rib, a second wing stub rib coupled to the second wing hinge rib, a third wing stub rib coupled to the third wing hinge rib, and a fourth stub hinge rib coupled to the fourth wing hinge rib; and
a tip transition portion including a first tip hinge rib, a second tip hinge rib, a third tip hinge rib and a fourth tip hinge rib, the first tip hinge rib coupled to the first wing hinge rib and the first hinge stub rib, the second tip hinge rib coupled to the second wing hinge rib and the second hinge stub rib, the third tip hinge rib being coupled to the third wing hinge rib and the third hinge stub rib, and the fourth tip hinge rib being coupled to the fourth wing hinge rib and the fourth hinge stub rib, wherein at least one of the first wing hinge rib, the second wing hinge rib, the third wing hinge rib, the fourth wing hinge rib, the first tip hinge rib, the second tip hinge rib, the third tip hinge rib, and the fourth tip hinge rib includes a hinge pin aperture that aligns to receive a hinge pin assembly at a hinge interface, and wherein the hinge interface provides a single-shear reaction when the hinge interface is subjected to single-shear loading.

11. The foldable aircraft wing of claim 10 , wherein the wing transition portion supports a first stop pad and the tip transition portion supports a second stop pad.

12. The foldable aircraft wing of claim 11 , wherein the first stop pad is to engage the second stop pad when the foldable aircraft wing is in an unfolded position, engagement between the first and second stop pads to provide a load path between the foldable wing tip and the fixed wing portion.

13. A foldable aircraft wing, comprising:
a foldable wing tip;
a fixed wing portion; and
a hinge to rotatably couple the foldable wing tip to the fixed wing portion, the hinge including:
a wing transition portion including a first wing hinge rib, a second wing hinge rib, a third wing hinge rib, and a fourth wing hinge rib, the wing transition portion further including a first wing stub rib coupled to the first wing hinge rib, a second wing stub rib coupled to the second wing hinge rib, a third wing stub rib coupled to the third wing hinge rib, and a fourth stub hinge rib coupled to the fourth wing hinge rib; and
a tip transition portion including a first tip hinge rib, a second tip hinge rib, a third tip hinge rib and a fourth tip hinge rib, the first tip hinge rib coupled to the first wing hinge rib and the first hinge stub rib, the second tip hinge rib coupled to the second wing hinge rib and the second hinge stub rib, the third tip hinge rib being coupled to the third wing hinge rib and the third hinge stub rib, and the fourth tip hinge rib being coupled to the fourth wing hinge rib and the fourth Response to the official action dated Feb. 23, 2022 hinge stub rib, wherein at least one of the first wing stub rib, the second wing stub rib, the third wing stub rib, the fourth wing stub rib, the first tip hinge rib, the second tip hinge rib, the third tip hinge rib, and the fourth tip hinge rib includes a latch pin aperture that aligns to receive a latching pin at a latch interface wherein the latch interface provides a double-shear reaction when the hinge is subjected to single-shear loading.

14. A method of enhancing a structural integrity of a fixed wing portion and a foldable wing tip at wing joint, the method comprising:
coupling a portion of an end of a tip hinge rib of a foldable wing tip between a wing hinge rib and a stub hinge rib of a fixed wing portion, the wing hinge rib and the stub hinge rib to provide a double-shear reaction when the portion of the end is subjected to single-shear loading to reduce or restrict transfer of prying forces into latch pin actuators positioned adjacent the at least the portion of the end of the tip hinge rib.

15. The method of claim 14 , further including pivotally coupling the foldable wing tip and the fixed wing portion via a hinge pin assembly passing through an aperture of the wing hinge rib and the tip hinge rib.

Assignees

• Boeing Co

Inventors

• Dees Paul W
• Gruner Eric
• Addington Michael
• Boes David Douglas
• Blohm Eric Dwight
• Elenbaas Matthew Scott
• Hansken Rickie
• Herzberg Mark John
• Kamila Eric Sean
• Olds Jeffrey Michael
• Soman Charuhas
• Townsend Keith
• Walker Steven Paul

Classifications

• B64C3/546

  by foldable elements · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C3/187

  Ribs · CPC title

• B64C3/54 Primary

  Varying in area · CPC title

• B64C23/069

  using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title