Wing system for an aircraft with a flow body and a cover panel

Patent metadata

Field	Value
Publication number	US-11352122-B2
Application number	US-201916554963-A
Country	US
Kind code	B2
Filing date	Aug 29, 2019
Priority date	Aug 30, 2018
Publication date	Jun 7, 2022
Grant date	Jun 7, 2022

Abstract

A wing system ( 2 ) for an aircraft includes a movable flow body ( 6 ) and a cover panel ( 8 ), wherein the flow body ( 6 ) and the cover panel ( 8 ) both are movably supported on a main wing body ( 4 ). While the flow body ( 6 ) is actively driven into upwards or downwards deflected positions, the cover panel ( 8 ) is coupled with the flow body ( 6 ) to follow its motion. The cover panel covers a part of the flow body ( 6 ) and the main wing body ( 4 ) in order to provide a substantially continuous, closed outer contour.

First claim

The invention claimed is:

1. A wing system for an aircraft comprising:
a main wing body,
a movable flow body,
a cover panel,
a support structure attached to the main wing body,
a first link swivably coupled to the moveable flow body at a first end of the first link, and
a second link rigidly attached to an underside of the cover panel and swivably connected to the first link by a second joint at a distal end of the second link,
wherein the support structure protrudes through a contour of the main wing body,
wherein the moveable flow body is positioned downstream of the main wing body,
wherein the moveable flow body is swivably coupled to a first joint at an end of the support structure, such that the flow body is swivable around the first joint from a neutral position to upwards or downwards deflected positions,
wherein the cover panel is positioned between the main wing body and the moveable flow body,
wherein the cover panel is movably coupled to the main wing body and swivably coupled to a second end of the first link to follow motion of the moveable flow body at least partially,
wherein the main wing body, the cover panel and the moveable flow body are configured to create a closed wing contour at least in the neutral position, and
wherein the second link is not directly connected to the support structure.

2. The wing system of claim 1 , wherein the support structure protrudes downwards from a bottom side of the main wing body.

3. The wing system of claim 1 , wherein the first joint is arranged forward of a leading edge of the moveable flow body and underneath the cover panel while in the moveable flow body is in a neutral position.

4. The wing system of claim 1 , wherein the support structure is rigidly attached to the main wing body.

5. The wing system of claim 1 , further comprising a connecting structure attached to an underside of the moveable flow body and coupled to the first joint.

6. The wing system of claim 5 , wherein the connecting structure is rigidly attached to the moveable flow body.

7. The wing system of claim 1 , wherein the second link extends downwards and rearwards from the underside of the cover panel.

8. The wing system of claim 1 , wherein the second joint is below the moveable flow body at least while in the neutral position.

9. The wing system of claim 1 , wherein the second link at least partially extends parallel to a chord of the cover panel.

10. The wing system of claim 1 , wherein the first joint is arranged forward of the second joint while in the neutral position.

11. The wing system of claim 1 , wherein:
the first link is swivably coupled to the moveable flow body at a third joint at an underside of the moveable flow body, and
the third joint is directly above the second joint or displaced in a rearward direction along 25% of a length of a chord of the moveable flow body at a maximum while in the neutral position.

12. An aircraft comprising the wing system of claim 1 .

13. An aircraft wing comprising:
a main wing body having an upper skin and a trailing edge;
a support structure attached to the main wing body, and having a distal portion forming a first pivot point;
a cover panel in a slot in the main wing body and above the support structure;
a trailing edge flap aligned with the trailing edge of the main wing and at least partially rearward of the trailing edge, wherein the trailing edge flap is linked to the first pivot point and configured to swivel about the first pivot point between a neutral position and at least one of an upward deflected position and a downward deflected position;
a first link having a first end pivotably connected to the trailing edge flap, and
a second link having a distal end pivotably connected to a second end of the first link, wherein the second link is fixed to the cover panel, extends downwards from and rearward of an underside of the cover panel, and wherein the second link is not directly connected to the support structure.

14. The aircraft wing of claim 13 , wherein the second link has a dog-legged shape.

15. The aircraft wing of claim 13 , wherein the second link has a proximal end fixed to the cover panel.

16. The aircraft wing of claim 13 , wherein the support structure framework extends below a lower skin of the main wing body.

17. The aircraft wing of claim 13 , wherein the support structure framework is offset in a spanwise direction of the main wing body from the first and second links.

Assignees

• Airbus Operations Gmbh

Inventors

• Gibbert Markus
• Lorenz Florian

Classifications

• B64C9/16

  at the rear of the wing · CPC title

• B64C9/12 Primary

  surfaces of different type or function being simultaneously adjusted · CPC title

• B64C3/50 Primary

  by leading or trailing edge flaps · CPC title

• B64C9/04 Primary

  with compound dependent movements · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title