Wing flap with torque member and method for forming thereof

Patent metadata

Field	Value
Publication number	US-10647407-B2
Application number	US-201815975903-A
Country	US
Kind code	B2
Filing date	May 10, 2018
Priority date	Mar 30, 2018
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

First claim

What is claimed is:

1. A wing flap, comprising:
a flap body comprising:
an upper skin;
a lower skin, opposite the upper skin; and
a plurality of spars that extend between the upper skin and the lower skin; and

a torque member, comprising an axis of rotation and a plurality of extension members, and wherein:
each one of the extension members is coupled to the flap body and is spaced from an adjacent one of the plurality of extension members in a direction, transverse to the axis of rotation; and
a portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

2. The wing flap of claim 1 , wherein the torque member has a non-circular cross-sectional shape.

3. The wing flap of claim 1 , wherein:
the flap body further comprises an inboard end and an outboard end opposite the inboard end;
and
each one of the plurality of extension members is coupled to the inboard end of the flap body.

4. The wing flap of claim 3 , wherein:
the flap body further comprises an inboard rib that is coupled to the plurality of spars at the inboard end of the flap body; and
each one of the plurality of extension members is coupled to the inboard rib.

5. The wing flap of claim 4 , wherein:
the plurality of spars comprises a front spar and a rear spar;
the inboard rib extends between the front spar and the rear spar; and
each one of the plurality of extension members extends outwardly from the inboard end of the flap body.

6. The wing flap of claim 5 , wherein:
the plurality of extension members comprises a first extension member that is laterally spaced from the front spar.

7. The wing flap of claim 6 , wherein:
the plurality of extension members further comprises a second extension member that is laterally spaced from the rear spar.

8. The wing flap of claim 7 , wherein:
the plurality of extension members further comprises a third extension member that is located between the first extension member and the second extension member.

9. The wing flap of claim 5 , wherein:
the plurality of spars further comprises a middle spar located between the front spar and the rear spar; and
the plurality of extension members comprises:
a first extension member that is located between the front spar and the middle spar; and
a second extension member that is located between the rear spar and the middle spar.

10. The wing flap of claim 1 , wherein each one of the plurality of extension members is parallel to an adjacent one of the plurality of extension members.

11. The wing flap of claim 1 , wherein:
at least one of the upper skin and the lower skin comprises a skin major portion and a skin extension portion that extends from the skin major portion;
the flap body is partially formed by the skin major portion; and
the torque member is partially formed by the skin extension portion.

12. The wing flap of claim 1 , wherein the torque member comprises at least one of an upper-skin extension member that is contiguous with the upper skin and a lower-skin extension member that is contiguous with the lower skin.

13. The wing flap of claim 1 , wherein the torque member further comprises an extension rib that is coupled to and extends between an adjacent pair of the plurality of extension members.

14. A wing of an aircraft, the wing comprising:
a wing body; and
a wing flap, comprising:
a flap body that is coupled to and is movable relative to the wing body, the flap body comprising:
an upper skin;
a lower skin, opposite the upper skin; and
a plurality of spars, each extending between the upper skin and the lower skin; and

a torque member that comprises an axis of rotation and a plurality of extension members, and wherein:
each one of the extension members is coupled to the flap body and is spaced from an adjacent one of the plurality of extension members in a direction transverse to the axis of rotation; and
a portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

15. The wing of claim 14 , wherein the torque member has a non-circular cross-sectional shape.

16. The wing of claim 14 , wherein the torque member is configured to be coupled to a flap actuator of the aircraft.

17. The wing of claim 14 , wherein:
at least one of the upper skin and the lower skin comprises a skin major portion and a skin extension portion that extends from the skin major portion;
the flap body is partially formed by the skin major portion; and
the torque member is partially formed by the skin extension portion.

18. The wing of claim 14 , wherein:
the flap body further comprises an inboard end and an outboard end opposite the inboard end;
and
each one of the plurality of extension members is coupled to the inboard end of the flap body.

19. The wing of claim 18 , wherein:
the flap body further comprises an inboard rib that is coupled to the plurality of spars at the inboard end of the flap body; and
each one of the plurality of extension members is coupled to the inboard rib.

20. A method for forming a wing flap, the method comprising:
joining an upper skin, a lower skin, and a plurality of spars to at least partially form a flap body; and
coupling a plurality of extension members to the flap body to partially form a torque member, comprising an axis of rotation, and wherein:
each one of the extension members is spaced from an adjacent one of the plurality of extension members in a direction transverse to the axis of rotation;
the flap body is configured to be coupled to and movable relative to a wing of an aircraft about the axis of rotation; and
the torque member is configured to be coupled to a flap actuator of the aircraft.

Assignees

• Boeing Co

Inventors

• Kordel Jan A
• Balzer Michael A
• Bleazard Mark M
• Virnig Jacob D
• Choy Wendell C K
• Santini Gregory M

Classifications

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C9/16 Primary

  at the rear of the wing · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C9/20

  by multiple flaps · CPC title

• B64C3/20

  Integral or sandwich constructions · CPC title