FOLDING WING TIP AND ROTATING LOCKING MEMBER

Abstract

A rotatable locking member for locking an aircraft wing with a movable wing tip device. The rotatable locking member including a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin.

Claims

1. An aircraft including an aircraft wing, the aircraft wing comprising: a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the locked flight configuration such that the span of the aircraft wing is reduced, the aircraft wing further comprising: a locking mechanism for locking the folding wing tip device in the locked flight configuration, the locking mechanism comprising a rotatable locking member associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other of the folding wing tip device and the fixed wing, the locking pin being cylindrical and having a longitudinal central axis, the rotatable locking member comprising a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin, wherein the rotatable locking member comprises a toothed outer surface, and the toothed outer surface of the rotatable locking member is associated with a toothed actuator, the toothed actuator being arranged to be drive to move the rotatable locking member between the locked and unlocked positions.

2. The aircraft according to claim 1 wherein movement of the rotatable locking member from the unlocked to locked position comprises rotation of 180 degrees.

3.-5. (canceled)

6. The aircraft according to claim 1 wherein the rotatable locking member is associated with a secondary locking mechanism, the secondary locking mechanism arranged to prevent rotation of the rotatable locking member when the rotatable locking member is in the locked position.

7. The aircraft according to claim 1, wherein the rotatable locking member is located within a lock housing.

8. The aircraft according to claim 7 wherein the lock housing is fixed relative to the wing or wing tip device and arranged to allow rotational movement of the rotating locking member within the housing.

9. The aircraft according to claim 7, wherein the housing comprises a landing, the landing arranged to contact the locking pin when the rotatable locking member is in the locked position.

10. The aircraft according to claim 9 wherein the rotatable locking member comprises a slot associated with the landing, such that the rotatable locking member may extend to either side of the landing whilst still allowing for the rotational movement of the rotatable locking member.

11. The aircraft according to claim 1, wherein the rotatable locking member is associated with the fixed wing.

12. The aircraft according to claim 1, wherein the locking pin is associated with the wing tip device.

13. The aircraft according to claim 1, wherein the aircraft wing comprises a plurality of rotatable locking members and associated locking pins.

14. The aircraft according to claim 13 wherein the aircraft wing comprises a common drive source for actuating each of the rotatable locking members.

15. An aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the locked flight configuration such that the span of the aircraft wing is reduced, the aircraft wing further comprising a locking mechanism for locking the folding wing tip device in the locked flight configuration, the locking mechanism comprising: a rotatable locking member associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other of the folding wing tip device and the fixed wing, the locking pin being cylindrical and having a longitudinal central axis, the rotatable locking member comprising a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin, wherein the rotatable locking member comprises a toothed outer surface, and the toothed outer surface of the rotatable locking member is associated with a toothed actuator, the toothed actuator being arranged to be drive to move the rotatable locking member between the locked and unlocked positions.

16. A method of locking a wing tip device in a locked flight configuration on an aircraft according to claim 15, the method comprising the steps of: moving the wing tip device into the flight configuration and rotating the rotatable locking member around the central longitudinal axis of the locking pin, such that the rotatable locking member moves into the locked configuration.

17. The method of unlocking a wing tip device from a locked flight configuration on an aircraft according to claim 1, the method comprising the steps of: rotating the rotatable locking member around the central longitudinal axis of the locking pin, such that the rotatable locking member moves into the unlocked configuration.

Description

DESCRIPTION OF THE DRAWINGS

[0021] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which:

[0022] FIG. 1A shows a schematic view of an aircraft wing according to a first embodiment of the invention;

[0023] FIG. 1B shows a schematic view of an aircraft according to a second embodiment of the invention; and

[0024] FIGS. 2 to 7 show a locking mechanism according to a third embodiment of the invention.

DETAILED DESCRIPTION

[0025] FIG. 1A shows a wing 10 comprising a wing tip device 12 and a fixed wing 14. FIG. 1B shows an aircraft 100 comprising the wing 10. The wing tip device 12 is configurable between: (i) a locked flight configuration for use during flight, as shown in FIG. 1B and (ii) a ground configuration for use during ground-based operations, as shown in FIG. 1A, in which ground configuration the wing tip device 12 is moved away from the locked flight configuration such that the span of the aircraft wing 10 is reduced.

[0026] FIG. 2 shows a locking mechanism 20 comprising a locking pin 22 and a rotatable locking member 24. The locking pin 22 may be associated with a wing tip device 12, and the locking mechanism 20 associated with the wing 10, or vice versa. The locking pin 22 comprises a cylinder with a central longitudinal axis A. The rotatable locking member 24 comprises a U-shaped receiving portion 26, which is shaped to receive the locking pin 22. The receiving portion 26 has a wide mouth to allow easy location of the locking pin 22. As can be seen, the width of the U-shaped receiving portion 26 tapers away from the mouth of the receiving portion 26. This allows easy seating of the locking pin 22 within the receiving portion 26 whilst allowing the locking pin to be securely held in the locked position. The rotatable locking member 24 is rotatably mounted within a housing 28. The rotatable locking member 24 includes a toothed outer edge 30 which is engaged with the toothed drive wheel 32 of a drive shaft 34, the drive shaft connected to and driven by an actuator. The drive shaft 34 may be driven such that the toothed drive wheel 32 causes the rotatable locking member 24 to rotate within the housing 28.

[0027] FIG. 2 shows the locking mechanism 20 prior to movement of the locking pin 22 into the receiving section 26. When the wing tip device is moved into the flight configuration, the locking pin 22 will move into the receiving portion 26. The locking mechanism 20 is in the unlocked configuration, meaning that the locking pin 22 can move into and out of the receiving portion 26. To move the locking mechanism 20 into the locked configuration, and thus the wing 10 into the locked flight configuration, the drive shaft 34 is used, via the drive wheel 32 and the toothed outer surface 30, to rotate the rotatable locking member 24 around the axis A. FIG. 3 shows the locking mechanism 20 in the locked configuration, where the rotatable locking member 24 has been rotated approximately 180 degrees around the axis A, and the locking pin 22 is no longer able to move out of the receiving portion 26. In order to unlock the locking mechanism, the drive shaft 34 is used to drive the rotatable locking member 24 in the opposite direction, such that the locking pin 22 may be removed from the receiving portion 26.

[0028] FIG. 4 shows the reverse side of the locking mechanism 20 in a similar position to that shown in FIG. 2. The drive shaft 34 includes a secondary locking mechanism 36. The secondary locking mechanism 36 may be used to prevent the rotational movement of the rotatable locking member 24. In particular, a catch 38 may be rotated into engagement with a portion of the rotatable locking member 24 to prevent rotational movement of the rotatable locking member 24. The secondary locking mechanism may be driven by the toothed wheel 40 and a separate actuator (not shown). Whilst coaxial with the drive shaft 34, the secondary locking mechanism 36 is independently operated.

[0029] FIG. 5 shows the secondary locking mechanism 36 locking the rotatable locking mechanism 24 in the locked position, corresponding to that shown in FIG. 3. As can be seen, the catch 38 prevents the rotatable locking member 24 being rotated into the unlocked configuration. Therefore, the security of the locking mechanism 20 is increased.

[0030] FIG. 6 shows the housing 28 with a landing 40. The landing 40 is located such that the landing 40 contacts the locking pin 22 when the locking pin 22 is brought into the receiving portion 26. When the rotatable locking member 24 has been rotated into the locked configuration, the landing 40 acts to support the locking pin 22, and work against the locking pin 22 hogging, or bending, under load. In order to allow the landing 40 to be located in the approximate centre of the housing 28, the rotatable locking member 26 includes a slot which receives the landing 40, thereby allowing rotational movement of the rotatable locking member 24 as required.

[0031] FIG. 7 shows a possible arrangement of a plurality of locking members 20. Four locking members 20 are provided (corresponding locking pins not shown), and each drive shaft 34 is driven by a common actuator 42, via an actuator drive shaft 44. Such an arrangement allows a simple locking mechanism to be used, with reduced complexity compared to each locking member 20 having an individual drive system.

[0032] Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein. By way of example only, certain possible variations will now be described.

[0033] The locking mechanism may be applied to alternative aircraft components, for example, cargo doors.

[0034] Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.