Torque tube door

Patent metadata

Field	Value
Publication number	US-9623957-B2
Application number	US-201414469543-A
Country	US
Kind code	B2
Filing date	Aug 26, 2014
Priority date	Aug 26, 2014
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

A torque tube door and related method steps may include a door coupled to an inboard wing flap, such that the door is movable with the flap to selectively cover and uncover a torque tube opening in an aircraft fuselage.

First claim

I claim:

1. An aircraft comprising:
a fuselage including an opening configured to receive a torque member;
a wing connected to the fuselage, the wing including a flap adjacent to the fuselage; and
a door mounted to and movable with the flap such that the door covers the opening when the flap is in a first position, and uncovers at least a portion of the opening when the flap is in a second position;
wherein the door is mounted to the flap by a mounting bracket directly attached to both the door and the flap.

2. The aircraft of claim 1 , further comprising a sealing member disposed along an edge portion of the opening.

3. The aircraft of claim 2 , wherein the door includes a central body portion and a perimetral flange portion, the flange portion being configured to form a seal with the sealing member when the flap is in the first position.

4. The aircraft of claim 1 , wherein the torque member is coupled to the wing flap.

5. The aircraft of claim 1 , wherein the door is mounted to an inboard end portion of the flap.

6. The aircraft of claim 1 , wherein the opening in the fuselage has an arcuate shape.

7. The aircraft of claim 1 , wherein the first position is a flaps up position, and the second position is a flaps down position.

8. A wing flap for an aircraft, the wing flap comprising:
a wing flap body having an inboard end portion;
a torque member coupled to the wing flap body; and
a door mounted to the inboard end portion of the wing flap body by one or more brackets each affixed directly to both the door and the inboard end portion of the wing flap body;
wherein a portion of the door extends transversely beyond the wing flap body.

9. The wing flap of claim 8 , wherein the door is movable with the wing flap body, such that the door is configured to selectively cover and uncover an opening in an adjacent fuselage as the door moves with the wing flap body.

10. The wing flap of claim 8 , wherein the door is bonded to the wing flap body.

11. The wing flap of claim 8 , wherein the portion of the door extends transversely beyond a lower surface of the wing flap body.

12. The wing flap of claim 8 , wherein an outer edge portion of the door is configured to mate with a sealing member of a fuselage opening.

13. A method for selectively covering a torque tube opening in an aircraft fuselage, the method comprising:
when a wing flap is in a first position, covering a torque tube opening in a fuselage adjacent to the wing flap using a covering member mounted by at least one bracket directly to the wing flap; and
moving the covering member to at least partially uncover the torque tube opening in the fuselage by repositioning the wing flap to a second position.

14. The method of claim 13 , wherein the covering member is mounted to an inboard end portion of the wing flap.

15. The method of claim 14 , wherein a portion of the covering member extends transversely from the wing flap.

16. The method of claim 13 , further including sealing the torque tube opening when the wing flap is in the first position by causing an edge portion of the covering member to contact a sealing member of the opening.

17. The method of claim 13 , wherein the first position is a flaps up position, and the second position is a flaps down position.

18. The method of claim 13 , further including moving a torque tube through an arcuate path when repositioning the wing flap to the second position, the torque tube being attached to the wing flap and passing through the torque tube opening.

19. The method of claim 13 , wherein the at least one rigid bracket includes an upper bracket and two lower brackets.

20. The method of claim 19 , wherein the upper bracket and two lower brackets fit within and attach directly to respective inner surfaces of an outer skin of the wing flap.

Assignees

• Boeing Co

Inventors

• Bleazard Mark

Classifications

• B64C9/36 Primary

  the members being fuselages or nacelles · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title

• B64C9/18

  by single flaps · CPC title