Aircraft with a foldable wing tip device

• US 10,392,101 B2
• Filed: 04/02/2015
• Issued: 08/27/2019
• Est. Priority Date: 04/24/2014
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Axford, Tim, Fong, Tony, Alexander, Stuart
• Primary Examiner(s): Xavier, Valentina
• Application Number:
  US15/306,400
• Publication Number:
  US 20170043864A1
• Time in Patent Office: 1,608 Days
• CPC Class Codes: B64C 23/072 the wing tip airfoil devices being moveable in their entirety
• CPC Class Codes: B64C 3/185 Spars
• CPC Class Codes: B64C 3/54 Varying in area
• CPC Class Codes: B64C 3/546 by foldable elements
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

An aircraft including a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded inwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (6) is connected to the wing along a hinge axis (14) by spar beams (10 and 12) of the wing tip device, one of the beams being mounted for pivoting about a fixed axis and the other beam being mounted on a spherical bearing (15) to provide greater freedom of movement. Various actuator arrangements may be provided to pivot the wing tip device.

Claims

1. An aircraft comprising a wing and a wing tip device at the tip of the wing, the wing comprising first and second spars that converge towards the wing tip device, wherein the wing tip device is moveable between:

i. a flight configuration for use during flight, in which the wing tip device projects from the wing increasing the span of the aircraft, and

ii. a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is pivoted away from the flight configuration such that a span of the aircraft is reduced,

and wherein the wing tip device is connected to the wing by a hinge arrangement associated with the first spar and allowing pivoting about a fixed hinge axis perpendicular to the longitudinal axis of the first spar, and by a pivotal mounting arrangement associated with the second spar, the mounting arrangement being disposed in the second spar perpendicular thereto whilst mounting the wing tip device for pivoting about the fixed hinge axis, the hinge arrangement and the pivotal mounting arrangement being arranged to allow the wing tip device to rotate about the hinge axis between the flight configuration and the ground configuration.

2. An aircraft according to claim 1, in which the pivotal mounting arrangement comprises a spherical bearing mounted in the second spar.

3. An aircraft according to claim 1, wherein the wing tip device comprises a spar beam which has a first end fixed in the wing tip device and a second distal end which, in the flight configuration, is disposed in the wing.

4. An aircraft according to claim 3, wherein the spar beam passes through the hinge axis of the wing tip.

5. An aircraft according to claim 3, wherein the first and second spars comprise rear and front spars respectively and the distal end of the spar beam is disposed alongside the rear spar in the flight configuration.

6. An aircraft according to claim 1, in which a further spar is provided in the wing adjacent to the wing tip device, the further spar being disposed between the first and second spars.

7. An aircraft according to claim 5, in which the spar beam is interposed between the first spar and the further spar.

8. An aircraft according to claim 1, wherein the front and rear spars are of composite material.

9. An aircraft according to claim 1, wherein the wing tip device comprises a spar beam which has a first end fixed in the wing tip device and a second end which, in the flight configuration, is disposed in the wing wherein one or more actuators are provided for pivoting the wing tip device between the flight configuration and the ground configuration, the one or more actuators acting on the spar beam.

10. An aircraft according to claim 9, wherein a first actuator is provided for pivoting the wing tip device from the flight configuration to an intermediate configuration partway between the flight configuration and the ground configuration, and a second actuator is provided for pivoting the wing tip device from the intermediate configuration to the ground configuration.

11. An aircraft according to claim 10, wherein the first and second actuators are linear actuators.

12. An aircraft according to claim 9, wherein a single actuator is provided and is connected to a linkage that comprises a link that is connected to the spar beam and a link that is connected to the wing.

13. An aircraft according to claim 12, wherein the linkage comprises first and second links pivotally connected to each other at their first ends and pivotally connected to the spar beam and the wing respectively at their second ends, the actuator being pivotally connected to the first ends of the first and second links and to the wing.

14. An aircraft according to claim 12, wherein the single actuator is a linear actuator.

15. An aircraft according to claim 12, wherein the single actuator is a rotary actuator.

16. An aircraft according to claim 14, wherein the linkage comprises first and second links pivotally connected to each other at their first ends and connected by universal joints to the spar beam and the wing respectively at their second ends.

17. An aircraft according to claim 16, wherein a locking device is provided for locking the first ends of the links to the wing when the wing tip device is in the flight configuration.

18. An aircraft according to claim 16, wherein the first and second links extend along a substantially straight path when the wing tip device is in the ground configuration.

19. An aircraft according to any of claim 16, wherein top and bottom faces of the first and/or second links are effective to transfer loads between the wing tip device and the wing in the flight configuration of the wing tip device.

20. A wing for an aircraft according to claim 1.