Control device for an aircraft

Patent metadata

Field	Value
Publication number	US-2018099737-A1
Application number	US-201715689607-A
Country	US
Kind code	A1
Filing date	Aug 29, 2017
Priority date	Oct 11, 2016
Publication date	Apr 12, 2018
Grant date	—

Abstract

A control device ( 34 ) for an aircraft wing ( 3 ) including upper and lower spoilers ( 35, 37 ) mountable to a wing ( 3 ) behind a leading edge slat ( 26 ), wherein each of the upper and lower spoilers ( 35, 37 ) are movable in a direction towards each other into a wing ( 3 ) from a neutral position, to an enabled position to form an airflow slot ( 52 ) between the slat ( 26 ) and said upper and lower spoilers ( 35, 37 ). Each of the upper and lower spoilers ( 35, 37 ) may also be movable in a direction away from each other out of a wing ( 3 ) from said neutral position.

First claim

The invention is:

1 . A control device for an aircraft, the device comprising upper and lower spoilers mountable to a wing behind a leading edge slat, wherein each of said upper and lower spoilers are movable in a direction towards each other into a wing from a neutral position to an enabled position to form an airflow slot between the slat and said upper and lower spoilers.

2 . The control device according to claim 1 , wherein the upper and lower spoilers are configured to allow the wing to operate at a higher angle of attack when said upper and lower spoilers are in the enabled position.

3 . The control device according to claim 1 , wherein at least one of said upper and lower spoilers are rotatable in a direction towards the other of said upper and lower spoilers from said neutral position to said enabled position.

4 . The control device according to claim 1 , wherein each of said upper and lower spoilers are configured to contact each other in the enabled position.

5 . The control device according to claim 4 , wherein each of said upper and lower spoilers comprise a contact surface which are in contact while the upper and lower spoilers are in the enabled position.

6 . The control device according to claim 1 , wherein each of said upper and lower spoilers are movable in a direction away from each other out of a wing from said neutral position to a deployed position.

7 . The control device according to claim 6 , wherein the upper and lower spoilers are configured to reduce lift created by a wing when said upper and lower spoilers are in their deployed position.

8 . The control device according to claim 4 , wherein at least one of said upper and lower spoilers are rotatable in a direction away from the other of said upper and lower spoilers from said neutral position to said deployed position.

9 . The control device according to claim 1 , comprising an actuator assembly configured to drive each of said upper and lower spoilers.

10 . A wing assembly for an aircraft comprising a wing structure, a slat extending from a leading edge of said wing structure and a control device according to claim 1 mounted to the leading edge of said wing structure behind said slat.

11 . The wing assembly according to claim 10 , wherein the slat is fixed in position.

12 . The wing assembly according to claim 10 , wherein each of said upper and lower spoilers are pivotally mounted to the leading edge of said wing structure and extend in a direction towards the slat when in the neutral and deployed positions.

13 . The wing assembly according to claim 11 , wherein the wing structure comprises an upper and lower surface and the upper spoiler lies flush with said upper surface in said neutral position.

14 . The wing assembly according to claim 13 , wherein the upper spoiler extends below said upper surface in said enabled position.

15 . The wing assembly according to claim 13 , wherein the lower spoiler lies flush with said lower surface in said neutral position.

16 . The wing assembly according to claim 15 , wherein the lower spoiler extends above said lower surface in said enabled position.

17 . A wing for an aircraft comprising a wing assembly according to claim 10 .

18 . The wing according to claim 17 , comprising an inboard portion and an outboard portion, the outboard portion being foldable relative to the inboard portion, wherein the wing assembly is located in the foldable outboard portion.

19 . The wing according to claim 17 , comprising an inboard portion and an outboard portion, the outboard portion being foldable relative to the inboard portion, wherein the wing assembly is located in the inboard portion.

20 . An aircraft comprising a wing according to claim 17 .

21 . A wing assembly for an aircraft comprising:
a wing structure; a leading edge slat mounted to a leading edge of the wing structure; a control device between the wing structure and the leading edge slat, wherein the control device includes an upper spoiler and a lower spoiler, and linkages coupling the control device, the upper spoiler and the lower spoiler, the control device configured to move the upper spoiler and a lower spoiler between a neutral position and a deployed position, wherein the upper spoiler, while in the neutral position, has an upper surface bridging a gap between an upper skin surface of the leading edge slat and an upper skin surface of the wing structure, wherein the upper spoiler, while in the deployed position, extends above the upper skin surfaces of the leading edge slat and the wing structure; wherein the lower spoiler, while in the neutral position, has an lower surface bridging a gap between a lower skin surface of the leading edge slat and lower skin surface of the wing structure, and wherein the lower spoiler, while in the deployed position, extends below the lower skin surface of the wing structure.

Assignees

• Airbus Operations Ltd

Inventors

• Wright Philip

Classifications

• B64C3/58 Primary

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title

• B64C9/26 Primary

  by multiple flaps · CPC title

• B64C21/025

  for simultaneous blowing and sucking · CPC title

• B64C9/24 Primary

  by single flap · CPC title