Spar arrangement in a wing tip device

Patent metadata

Field	Value
Publication number	US-11643183-B2
Application number	US-201816007555-A
Country	US
Kind code	B2
Filing date	Jun 13, 2018
Priority date	Jun 15, 2017
Publication date	May 9, 2023
Grant date	May 9, 2023

Abstract

An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

First claim

The invention claimed is:

1. An aircraft comprising:
a wing,
a wing tip device at a tip of the wing extending upwardly from the tip of the wing as the wing tip device extends outboard of the wing in a spanwise direction of the wing, wherein the wing tip device includes a front spar, a rear spar, and a cross-brace spar linking the front spar to the rear spar,
a first rib and a second rib each extending in a chordwise direction of the wing tip device between the front spar and the rear spar, wherein the first rib is adjacent a joint between the wing tip device and the wing and the second rib is outboard of the first rib along the spanwise direction,
wherein an inboard end of the cross-brace spar is adjacent the second rib,
wherein the cross-brace spar is oriented oblique to the front and rear spars, and
wherein the cross-brace spar extends upwardly from an inboard location proximate one of the rear spar and the front spar to an outboard location proximate another of the front spar and the rear spar.

2. The aircraft according to claim 1 , further comprising a third rib extending in the chordwise direction from the front spar to the rear spar and being a nearest rib to a tip of the wing tip device,
wherein an outboard end of the cross-brace spar is adjacent the third rib, and
wherein the second rib, the third rib, the front spar and the rear spar form a structural box and the cross-brace spar extends diagonally across the structural box.

3. The aircraft according to claim 1 , wherein the wing tip device further comprises:
a third rib extending in the chordwise direction from the front to the rear spar, and the third rib is a nearest rib to a tip of the wing tip device, and
a fourth rib extending in the chordwise direction from the front spar to the rear spar, and the fourth rib is between the second rib and the third rib along the spanwise direction,
wherein the fourth rib has an upper edge adjacent a first skin of the wing tip device along an entire length of the fourth rib and has a lower edge adjacent a second skin of the wing tip device along the entire length of the intermediate rib, wherein the cross-brace spar is linked to a middle region of the fourth rib.

4. The aircraft according to claim 1 , wherein the wing tip device is swept back.

5. The aircraft according to claim 1 , wherein the wing tip device is twisted about a span wise axis of the wing tip device.

6. The aircraft according to claim 1 , wherein the wing tip device comprises a winglet.

7. The aircraft of claim 1 , wherein the wing includes a front wing spar and a rear wing spar, and the front spar of the wing tip device is fixed to an end region of the front wing spar and the rear spar of the wing tip device is fixed to an end region of the rear wing spar.

8. A wing assembly comprising:
a wing including a tip, and
a wing tip device at the tip of the wing, wherein the wing tip device extends upwardly from the tip of the wing as the wing tip device extends outbound of the wing in a spanwise direction of the wing, and the wing tip device includes a front spar, a rear spar, and a cross-brace spar linking the front and rear spars, wherein the cross-brace spar is oriented oblique to the front and rear spars, and extends upwardly from an inboard location proximate one of the rear spar and the front spar to an outboard location proximate another of the front spar and the rear spar, and
a first rib and a second rib each extending in a chordwise direction of the wing tip device between the front spar and the rear spar, wherein the first rib is adjacent a joint between the wing tip device and the tip of the wing and the second rib is outboard of the first rib along the spanwise direction,
wherein an inboard end of the cross-brace spar is adjacent the second rib.

9. The wing assembly according to claim 8 wherein the cross-brace spar links an inboard location on the rear spar to an outboard location on the front spar.

10. The wing assembly of claim 8 , wherein the wing includes a front wing spar and a rear wing spar, and the front spar of the wing tip device is fixed to an end region of the front wing spar and the rear spar of the wing tip device is fixed to an end region of the rear wing spar.

11. The wing assembly of claim 8 , further comprising a third rib which is a rib nearest a tip of the wing tip device,
wherein an outboard end of the cross-brace spar is at the third rib, and
wherein a structural box is formed in the wing tip device by the front spar, the rear spar, the cross-brace spar, the second rib and the third rib.

12. A wing tip device including:
a front spar,
a rear spar,
a cross-brace spar linking the front and rear spars and is oriented oblique to the front and rear spars,
a first rib and a second rib each extending in a chordwise direction of the wing tip device between the front spar and the rear spar, wherein the first rib is configured to be adjacent a joint between a wing attached to the wing tip device tip device, and the second rib is outboard of the first rib along the spanwise direction,
wherein an inboard end of the cross-brace spar is adjacent the second rib,
wherein the wing tip device extends upwardly from a tip of the wing as the wing tip device extends outbound of the wing in a spanwise direction of the wing, and
wherein the cross-brace spar extends upwardly from an inboard location proximate one of the rear spar and the front spar to an outboard location proximate another of the front spar and the rear spar.

13. The wing tip device according to claim 12 wherein the cross-brace spar links an inboard location on the rear spar to an outboard location on the front spar.

14. The wing tip device of claim 12 , wherein the wing includes a front wing spar and a rear wing spar, and the front spar of the wing tip device is fixed to an end region of the front wing spar and the rear spar of the wing tip device is fixed to an end region of the rear wing spar.

15. The wing tip device of claim 12 , further comprising a third rib which is a rib nearest a tip of the wing tip device,
wherein an outboard end of the cross-brace spar is at the third rib, and
wherein a structural box is formed in the wing tip device by the front spar, the rear spar, the cross-brace spar, the second rib and the third rib.

16. A method of manufacture of a wing tip device for use with a wing of an aircraft, wherein the wing tip device includes a front spar, a rear spar, a first rib and a second rib each extending between the front and rear spars, wherein the first rib is adjacent an inboard edge of the wing tip device and the second rib is outboard of the first rib, the method comprising:
linking the front spar and the rear spar of the wing tip device directly to a cross-brace spar, orienting the cross-brace spar oblique to the front and rear spars, and linking an inboard end of the cross-brace spar directly to the second rib,
wherein the cross-brace spar extends upwardly from an inboard location proximate one of the rear spar and the front spar to an outboard location proximate another of the front spar and the rear spar, and
wherein the wing tip device is configured to attached to a tip of the wing, and extends upwardly from a tip of the wing as the wing tip device extends outbound of the wing.

17. The method of claim 16 , further comprising:
configuring the front spar of the wing tip device to be fixed to an end region of a front wing spar of the wing, and
configuring the rear spar of the wing tip device to be fixed to an end region of a rear wing spar of the wing.

18. The

Assignees

• Airbus Operations Ltd

Inventors

• Bhatia Sarabpal-Singh
• Phillips Samuel

Classifications

• B64C3/18 Primary

  Spars; Ribs; Stringers · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C23/069

  using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title

• B64C3/58

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

• B64C3/185 Primary

  Spars · CPC title