Aircraft wing section assembly

Patent metadata

Field	Value
Publication number	US-12286223-B2
Application number	US-202318494280-A
Country	US
Kind code	B2
Filing date	Oct 25, 2023
Priority date	Feb 8, 2021
Publication date	Apr 29, 2025
Grant date	Apr 29, 2025

Abstract

An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.

First claim

The invention claimed is:

1. An aircraft wing section assembly, comprising:
a structural spine extending in a spanwise direction of the wing section, and
a movement mechanism comprising:
a support rod extending in a chordwise direction of the wing section, through the structural spine, from a first end to a second end,
a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the first end of the support rod, for pivotal movement with respect to the support rod,
a second lever, for connection to and for moving a second moveable control surface, pivotally mounted to the second end of the support rod, for pivotal movement with respect to the support rod,
an actuation mechanism for actuating pivotal movement of the first lever with respect to the support rod, and
an elongate member extending in a spanwise direction connected to the first lever at a first connection point for pulling the first connection point to pivotally move the first lever with respect to the support rod and to cause the second lever also to pivotally move with respect to the support rod, thus causing movement of both the first and second moveable control surfaces.

2. An aircraft wing section assembly as claimed in claim 1 , wherein the structural spine comprises a monolithic box structure.

3. An aircraft wing section assembly as claimed in claim 1 , wherein the support rod comprises an elongate section extending internally through the structural spine between the first and second ends, wherein the first end comprises a first end stopper located adjacent to a first external side of the structural spine for preventing the first end from moving in a first direction through the first side, and wherein the second end comprises a second end stopper located adjacent to a second, opposite external side of the structural spine for preventing the second end from moving in a second direction, opposite to the first direction, through the second side.

4. An aircraft wing section assembly as claimed in claim 1 , wherein the elongate member is connected to a pull mechanism for pulling the elongate member such that the first connection point moves.

5. An aircraft wing section assembly as claimed in claim 4 , wherein the elongate member is in the form of a cable.

6. An aircraft wing section assembly as claimed in claim 1 , wherein the elongate member is in the form of a cable and the actuation mechanism further comprises a pulley and wherein the cable extends around the pulley.

7. An aircraft wing section assembly as claimed in claim 6 , wherein the cable is also connected to the first lever at a second connection point which is on an opposite side of the pulley to the first connection point, such that when the cable is pulled, the first connection point moves in a first direction and the second connection point moves in a second opposite direction.

8. An aircraft wing section assembly as claimed in claim 1 , wherein the elongate member is also connected to the first lever at a second connection point, such that when the elongate member is pulled to move the first connection point in a first direction, the second connection point moves in a second opposite direction.

9. An aircraft wing section assembly as claimed in claim 1 , wherein the actuation mechanism comprises a crank lever, mounted to the first lever such that it extends transverse to the first lever and wherein the first connection point is located on a first end of the crank lever, the first end of the crank lever being located to a first transverse side of the first lever.

10. An aircraft wing section assembly as claimed in claim 9 , wherein the second connection point is located on a second opposite end of the crank lever, the second opposite end of the crank lever being located to a second, opposite transverse side of the first lever.

11. An aircraft wing section assembly as claimed in claim 1 , wherein the elongate member is part of a movement mechanism which further comprises a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever with respect to the support rod causes pivotal movement of the second lever with respect to the support rod.

12. An aircraft wing section assembly as claimed in claim 11 , wherein the connection mechanism comprises at least one connector extending in a chordwise direction of the wing section, through the structural spine.

13. An aircraft wing section assembly as claimed in claim 12 , wherein the connection mechanism comprises a second connector extending in a chordwise direction of the wing section, through the structural spine.

14. An aircraft wing section assembly as claimed in claim 1 , wherein the first lever is part of a first lever mechanism for connection to the first moveable control surface, and wherein the first lever mechanism also comprises a connecting link pivotally mounted to the first lever at a connecting link connection point.

15. An aircraft wing section assembly as claimed in claim 14 , wherein the connecting link connection point is closer to the point of pivotal mounting of the first lever to the support rod than the location of the first connection point.

16. An aircraft wing section assembly as claimed in claim 14 , wherein the first lever mechanism further comprises a D-shaped crank pivotally connected to the structural spine and connected to the connecting link such that movement of the connecting link causes the D-shaped crank to pivot with respect to the structural spine.

17. An aircraft wing section assembly as claimed in claim 1 , wherein in addition to said movement mechanism there are one or more further movement mechanisms each with its own support rod, first lever, and second lever, the movement mechanisms all being spaced apart along the structural spine in the spanwise direction and all being controlled and moved by the same actuation mechanism.

18. An aircraft wing section assembly as claimed in claim 1 , further comprising a first moveable control surface connected to the first lever and a second moveable control surface connected to the second lever, wherein one or both of the moveable control surfaces comprise a flexible skin adjacent to connection of the surface to the lever.

19. An aircraft wing assembly including the aircraft wing section assembly of claim 1 , wherein the aircraft wing section assembly is located at a tip portion of the aircraft wing assembly.

20. An aircraft wing assembly as claimed in claim 19 , comprising a foldable wing tip portion being foldable about a fold line and wherein the aircraft wing section assembly is located in the foldable wing tip portion, such that it is located outboard of the fold line.

21. An aircraft wing assembly as claimed in claim 20 , wherein the elongate member is connected to a pull mechanism for pulling the elongate member such that the first connection point moves, the pull mechanism being located outboard of the fold line.

22. An aircraft wing assembly as claimed in claim 20 , wherein the elongate member includes a cable outboard of the fold line, there being a pull mechanism for pulling the cable such that the first connection point moves, the pull mechanism being located inboard of the fold line, and wherein the pull mechanism includes a cable link transfer mechanism to transfer movement of a cable inboard of the fold line into movement of the cable outboard of the fold line.

23. An aircraft comprising the aircraft wing section ass

Assignees

• Airbus Operations Ltd

Inventors

• KELLY Mark Shaun
• Kelly Peter
• Alexander Stuart Strachan

Classifications

• B64U10/25

  Fixed-wing aircraft (VTOL aircraft B64U10/20) · CPC title

• B64U40/10

  for adjusting control surfaces or rotors · CPC title

• B64U30/12

  Variable or detachable wings, e.g. wings with adjustable sweep · CPC title

• B64C3/48

  by relatively-movable parts of wing structures · CPC title

• B64C9/12

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