Swing wing tip

Patent metadata

Field	Value
Publication number	US-2017152016-A1
Application number	US-201615364865-A
Country	US
Kind code	A1
Filing date	Nov 30, 2016
Priority date	Nov 30, 2015
Publication date	Jun 1, 2017
Grant date	—

Abstract

An aircraft including a wing 10 having a fixed wing 12 and a swing wing tip device 14 pivotably mounted about a pivot 16 at the tip of the fixed wing, wherein the swing wing tip device 14 is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations, where the span of the aircraft wing is reduced. The swing wing tip device 14 includes a receiving portion 48 arranged such that in the ground configuration, portions of the upper wing skin and lower wing skin of the fixed wing which are exposed in the flight configuration are at least partially received within the receiving portion 48 of the swing wing 14.

First claim

The invention is:

1 . An aircraft comprising a wing, the wing comprising a fixed wing and a swing wing tip device pivotably mounted about a pivot at the tip of the fixed wing, wherein the swing wing tip device is configurable between:
(i) a flight configuration for use during flight; and (ii) a ground configuration for use during ground-based operations, in which ground configuration the swing wing tip device is swung rearwardly, away from the flight configuration, such that the span of the aircraft wing is reduced; wherein the swing wing tip device comprises a leading edge, a trailing edge, an upper wing skin and a lower wing skin, and a receiving portion located between the upper wing skin and lower wing skin, and the fixed wing comprises a leading edge, a trailing edge, an upper wing skin and a lower wing skin, wherein when the swing wing tip device is in the flight configuration, the upper and lower wing skins of the swing wing tip device are substantially continuous with the respective upper and lower wing skins of the fixed wing, and the leading and trailing edges of the swing wing tip device are continuations of the respective leading and trailing edges of the fixed wing, and wherein the receiving portion of the swing wing tip is arranged such that in the ground configuration, portions of the upper wing skin and lower wing skin of the fixed wing, which are exposed in the flight configuration, are at least partially received within the receiving portion of the swing wing.

2 . The aircraft as claimed in claim 1 , wherein the swing wing tip device comprises a frame located between the upper wing skin and lower wing skin of the swing wing tip device, the frame being pivotably mounted on the pivot and the frame having an upper portion proximate to the upper wing skin of the swing wing tip device and a lower portion proximate to the lower wing skin of the swing wing tip device, and
wherein the receiving portion of the swing wing tip device is located between the upper portion and lower portion of the frame.

3 . The aircraft as claimed in claim 1 , wherein the upper wing skin of the fixed wing and the upper wing skin of the swing wing tip device each comprises an interfacing edge, and the lower wing skin of the fixed wing and the lower wing skin of the swing wing tip device each comprises an interfacing edge, and
wherein, during movement of the swing wing tip device from the flight configuration, to the ground configuration, part of the interfacing edges of the swing wing tip device is moved over part of the interfacing edges of the fixed wing.

4 . The aircraft as claimed in claim 3 , wherein at least a portion of an interfacing edge extends in a direction along the length of the wing.

5 . The aircraft as claimed in claim 3 , wherein at least a portion of an interfacing edge extends in an arc with a centre point located approximately at the pivot.

6 . The aircraft as claimed in claim 1 , wherein at least 80% of the span of the wing comprises the fixed wing.

7 . The aircraft as claimed in claim 1 , wherein the fixed wing comprises a front spar and the swing wing tip device comprises a front spar, and in the flight configuration the front spar of the fixed wing and the front spar of the swing wing tip device at least partially overlap.

8 . The aircraft as claimed in claim 7 , further comprising a locking mechanism associated with the front spar of the fixed wing and the front spar of the swing wing tip device, arranged to lock the front spar of the fixed wing to the front spar of the swing wing tip device when the swing wing tip device is in the flight configuration, such that the front spar of the swing wing tip device becomes an extension of the front spar of the fixed wing.

9 . The aircraft according to claim 8 , wherein the locking mechanism comprises one or more pins extending from one of the front spar of the fixed wing and the front spar of the swing wing tip device into a locking aperture in the other of the front spar of the fixed wing and the front spar of the swing wing tip device,
and wherein the longitudinal axes of the locking pins and the apertures are tangential to a notional circle, centred on the pivot, passing through the locking pins and apertures.

10 . The aircraft as claimed in claim 1 , wherein the fixed wing comprises a rear spar and the swing wing tip device comprises a rear spar, and in the flight configuration the rear spar of the fixed wing and the rear spar of the swing wing tip device at least partially overlap.

11 . The aircraft as claimed in claim 10 , further comprising a locking mechanism associated with the rear spar of the fixed wing and the rear spar of the swing wing tip device, arranged to lock the rear spar of the fixed wing to the rear spar of the swing wing tip device when the swing wing tip device is in the flight configuration, such that the rear spar of the swing wing tip device becomes an extension of the rear spar of the fixed wing.

12 . The aircraft as claimed in claim 11 , wherein the locking mechanism associated with the rear spar of the fixed wing and the rear spar of the swing tip device, is also arranged to lock the front spar of the swing wing tip device to the fixed wing when the swing wing tip device is in the ground configuration.

13 . The aircraft as claimed in claim 1 , wherein the swing wing tip device comprises an open box structure.

14 . An aircraft wing for use as the wing in claim 1 .

15 . A swing wing tip device for use as the swing wing tip device in claim 1 , wherein the swing wing tip device comprises a leading edge, a trailing edge, an upper wing skin and a lower wing skin, and a receiving portion located between the upper wing skin and lower wing skin,
wherein the swing wing tip device is arranged to be configurable between: (i) a flight configuration for use during flight; and (ii) a ground configuration for use during ground-based operations, in which ground configuration the swing wing tip device is swung rearwardly, away from the flight configuration, such that the span of the aircraft wing is reduced; wherein when the swing wing tip device is arranged such that in the flight configuration, the upper and lower wing skins of the swing wing tip device are configured to be substantially continuous with the respective upper and lower wing skins of the fixed wing, and the leading and trailing edges of the swing wing tip device are configured to be continuations of the respective leading and trailing edges of the fixed wing, and the receiving portion of the swing wing tip is arranged such that in the ground configuration, upper and lower portions of the fixed wing which are arranged to be exposed in the flight configuration are at least partially received within the receiving portion of the swing wing.

16 . A fixed wing for use as the fixed wing in claim 1 , the fixed wing having a leading edge, a trailing edge, an upper wing skin and a lower wing skin, and the fixed wing being configured to receive a swing wing tip device, the swing wing tip device being configurable between: (i) a flight configuration for use during flight; and (ii) a ground configuration for use during ground-based operations, in which ground configuration the swing wing tip device is swung rearwardly, away from the flight configuration, such that the span of the aircraft wing is reduced;
and wherein when the swing wing tip device is in the flight configuration, the upper and lower wing skins of the swing wing tip device are configured to be substantially continuous with the respective upper and lower wing skins of the fixed wing, a

Assignees

• Airbus Operations Ltd

Inventors

• Napier Stefan
• Hart Robert
• Harding Matthew
• Livings Nick

Classifications

• B64C3/185

  Spars · CPC title

• B64C3/56 Primary

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title