Fold wing tip having stub spar

Patent metadata

Field	Value
Publication number	US-9908612-B2
Application number	US-201113251216-A
Country	US
Kind code	B2
Filing date	Oct 1, 2011
Priority date	Oct 1, 2011
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A wing includes a wing tip hinged to a main wing section. The wing tip includes a stub spar extending past an end of the wing tip. When the wing tip is extended, the stub spar extends into the main wing section to react a moment load across a length of the stub spar.

First claim

The invention claimed is:

1. An aircraft wing defining a chordwise direction, the wing comprising:
a main wing section;
a wing tip rotatably coupled to the main wing section by a hinge defining a hinge line extending in the chordwise direction and about which the wing tip rotates relative to the main wing section, the wing tip being movable between an extended position, in which the wing tip is aligned with the main wing section, and a folded position, in which the wing tip is rotated about the hinge line, the wing tip further including a stub spar extending past an end of the wing tip and configured for insertion into the main wing section when the wing tip is in the extended position, a free end of the stub spar defining a locking location configured for coupling to the main wing section, wherein a distance along a length of the stub spar between the hinge line and the locking location defines a moment arm for reacting a moment load across a length of the stub spar when the wing tip is extended and locked to the main wing section; and
an actuator attached directly to the free end of the stub spar and configured to rotate the wing tip about the hinge line.

2. The wing of claim 1 , wherein the stub spar includes a beam, and the hinge comprises a stub spar hinge directly attached to the beam.

3. The wing of claim 2 , wherein the stub spar hinge is located beneath an upper surface of the main wing section.

4. The wing of claim 1 , wherein the stub spar is aligned with a main wing spar when the wing tip is in the extended position; and wherein the stub spar is roughly normal to the main wing section when the wing tip is in the folded position.

5. The wing of claim 4 , further comprising a locking device at the locking location of the stub spar for locking the stub spar to the main wing spar.

6. The wing of claim 1 , wherein the distance between the hinge line and the locking location is greater than a distance between an upper surface and a lower surface of the wing tip.

7. The wing of claim 1 , wherein the stub spar is an extension of a spar in the wing tip.

8. The wing of claim 1 , wherein the stub spar is fastened to a spar in the wing tip.

9. The wing of claim 1 , wherein the stub spar is subject to a stub spar lock load and a stub spar hinge load at different locations along a length of the stub spar.

10. An aircraft wing, the wing comprising:
a main wing section defining a chordwise direction and including a main spar;
a hinge coupled to the main spar and defining a hinge line extending in the chordwise direction;
a wing tip including a stub spar extending past an end of the wing tip and attached to the hinge at a first location of the stub spar, so that the wing tip rotates relative to the main wing section about the hinge line between an extended position, in which the wing tip is aligned with the main wing section and the stub spar is aligned with the main spar, and a folded position, in which the wing tip is rotated about the hinge line, the stub spar configured for insertion into the main wing section when the wing tip is in the extended position, a free end of the stub spar defining a locking device positioned at a second location of the stub spar and configured to releasably engage the main spar of the main wing section, wherein a distance along a length of the stub spar between the first location and the second location defines a moment arm for reacting a moment load across a length of the stub spar when the wing tip is extended and locked to the main wing section, and wherein the distance along the length of the stub spar between the first location and the second location is greater than a distance between an upper surface and a lower surface of the wing tip; and
an actuator operably coupled to the wing tip to fold the wing tip about the hinge line.

11. The wing of claim 10 , wherein the hinge is located beneath an upper surface of the main wing section.

12. The wing of claim 10 , wherein the stub spar is an extension of a spar in the wing tip.

13. The wing of claim 10 , wherein the stub spar is fastened to a spar in the wing tip.

Assignees

• Fox Bruce Robert
• Boeing Co

Inventors

• Fox Bruce Robert

Classifications

• B64C3/56 Primary

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

• B64C3/42

  Adjusting about chordwise axes · CPC title

• Y02T50/145

  Cross-Sectional Technologies · mapped topic

• Y02T50/10

  Drag reduction · CPC title