Folding wing tip device with rotatable lock

Abstract

The invention relates to a locking mechanism for a folding wing tip. The locking mechanism has a locked configuration, in which a first part is received in a second part such that the first part may not be withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part may be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism.

Claims

1. An aircraft, comprising: 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 wing tip device in the locked flight configuration, the locking mechanism having a longitudinal axis and comprising a first part associated with one of the fixed wing and the wing tip device, and a second part associated with the other of the fixed wing and wing tip device, the locking mechanism having a locked configuration, in which the first part is received in the second part such that the first part is prevented from being withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part is free to be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism, wherein the first part is a male locking pin having a longitudinal axis shared with the locking mechanism, with one or more flanges extending in a direction perpendicular to the longitudinal axis of the locking pin, wherein the second part is a female receiving portion, with an opening aperture shaped to allow passage of the male locking pin in a longitudinal direction when the locking mechanism is in the unlocked configuration, and wherein the female receiving portion comprises at least one internal receiving chamber, the receiving chamber arranged to receive a flange of the male locking pin and prevent longitudinal movement of the male locking pin when the locking mechanism is in the locked configuration.

2. The aircraft as claimed in claim 1, wherein the flange of the male locking pin is configured to be moved into and out of the internal receiving chamber by rotational movement of at least one of the male locking pin and female receiving member around the longitudinal axis of the locking mechanism.

3. The aircraft as claimed in claim 1, wherein the internal receiving chamber decreases in dimensions in the direction of rotation of the male locking pin when moving into the locked configuration.

4. The aircraft as claimed in claim 1, wherein the male locking pin comprises two, three, four, or five flanges extending in a direction perpendicular to the longitudinal axis of the locking pin.

5. The aircraft as claimed in claim 4, further comprising a female receiving portion comprising a corresponding number of internal receiving chambers, each chamber arranged to receive individual flanges when the locking mechanism is in the locked configuration.

6. The aircraft as claimed in claim 5, wherein the female receiving portion comprises an opening aperture with two, three, four, or five sections shaped to correspond to, and allow passage of, the flanges extending from the male locking pin.

7. The aircraft as claimed in claim 1, wherein the female receiving portion comprises one or more internal receiving chambers with at least a partial thread.

8. The aircraft as claimed in claim 1, wherein the first part and/or second part includes a toothed surface suitable for being driven by a similarly toothed drive unit.

9. The aircraft as claimed in claim 1, wherein the first part comprises a male locking pin comprising one or more locking channels.

10. The aircraft as claimed in claim 9, wherein the second part comprises one or more internal pins arranged to engage with a corresponding locking channel.

11. The aircraft as claimed in claim 9, wherein the one or more locking channels extend initially in a longitudinal direction and then in a direction perpendicular to the longitudinal direction.

12. 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 wing tip device in the locked flight configuration, the locking mechanism having a longitudinal axis and comprising a first part associated with one of the fixed wing and the wing tip device, and a second part associated with the other of the fixed wing and wing tip device, the locking mechanism having a locked configuration, in which the first part is received in the second part such that the first part is prevented from being withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part is free to be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism, wherein the first part is a male locking pin having a longitudinal axis shared with the locking mechanism, with one or more flanges extending in a direction perpendicular to the longitudinal axis of the locking pin, wherein the second part is a female receiving portion, with an opening aperture shaped to allow passage of the male locking pin in a longitudinal direction when the locking mechanism is in the unlocked configuration, and wherein the female receiving portion comprises at least one internal receiving chamber, the receiving chamber arranged to receive a flange of the male locking pin and prevent longitudinal movement of the male locking pin when the locking mechanism is in the locked configuration.

13. A method of locking a wing tip device on an aircraft as claimed in claim 1, the method comprising the steps of moving the wing tip device into the flight configuration, such that the first part is received within the second part of the locking mechanism, and rotating the first part and/or second part relative to the longitudinal axis of the locking mechanism such that corresponding elements of the first part and second part obstruct each other, thereby preventing relative movement of the first part and second part in the longitudinal direction.

14. A method of unlocking a wing tip device on an aircraft as claimed in claim 1, the method comprising the steps of rotating the first part and/or second part relative to the longitudinal axis of the locking mechanism such that corresponding elements of the first part and second part do not obstruct each other, thereby allowing relative movement of the first part and second part in the longitudinal direction.

Description

DESCRIPTION OF THE DRAWINGS

(1) Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which:

(2) FIG. 1A shows a schematic view of a wing according to a first embodiment of the invention;

(3) FIG. 1B shows a schematic view of an aircraft comprising a wing as shown in FIG. 1A

(4) FIG. 2 shows a schematic view of a first part of a locking mechanism according to a first embodiment of the invention;

(5) FIG. 3 shows a schematic view of a second part of a locking mechanism according to the first embodiment of the invention; and

(6) FIG. 4 shows a cross sectional view of the locking mechanism according to the first embodiment of the invention in the locked configuration;

(7) FIG. 5 shows a cross sectional view of the locking mechanism according to the first embodiment of the invention in the unlocked configuration;

(8) FIG. 6 shows a cross sectional view of the locking mechanism according to the first embodiment of the invention in the locked configuration;

(9) FIG. 7 shows a second embodiment of the invention with a threaded female receiving portion;

(10) FIG. 8 shows a male locking pin according to a third embodiment of the invention; and

(11) FIG. 9 shows a female receiving portion according to the third embodiment of the invention.

DETAILED DESCRIPTION

(12) 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 and (ii) a ground configuration for use during ground-based operations, 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. FIG. 1A shows the wing tip device 12 in the ground configuration and FIG. 1B shows the wing tip device in the locked flight configuration.

(13) FIG. 2 shows a first part 20 of a locking mechanism, the locking mechanism present on a wing 10 as shown in FIG. 1. The first part comprises a male locking pin 22 with a three flanges 24, 26, and 28, which extend from the outer surface of the male locking pin 22 in a direction perpendicular to the longitudinal axis indicated by the letters L-L. FIG. 3 shows a second part 30 of a locking mechanism. The second part 30 includes an opening with a central aperture 32 shaped to allow passage of the male locking pin 22 in the longitudinal direction. The opening also includes outer apertures 34, 36, and 38 which correspond in approximate size and position relative to the central aperture 32 as the flanges 24, 26, and 28 to the locking pin 22. The second part 30 includes three internal chambers 40, 42, and 44, as shown in FIGS. 4, 5, and 6.

(14) The first part 20 is associated with the wing tip device 12, and the second part 30 is associated with the fixed wing 14. When the wing tip device 12 is moved from the ground configuration to the flight configuration the first part 20 is moved from a position away from the second part 30, to a position where the first part 20 is inserted into the second part 30, such that the male locking pin 22 including the flanges 24, 26, and 28, passes through the central aperture 32, and outer apertures 34, 36, and 38, in a longitudinal direction. In this position, the first part and second part of the locking mechanism are engaged, but in the unlocked configuration, as shown in FIG. 5. In this position, the first part 20 may still be removed from the second part 30, by moving the two parts away from each other in the longitudinal direction. In order to move the locking mechanism into the locked configuration, at least one of the first part 20 and second part 30 is rotated such that the flanges 24, 26, 28, move into the corresponding internal chambers 40, 42, 44. The locked configuration is shown in both FIGS. 4 and 6. Once the locking mechanism is in the locked configuration, the internal chambers 40, 42, and 44, obstruct the removal of the first part from the second part in the longitudinal direction. Therefore, wing tip device 12 is then in the locked flight configuration and suitable for flight. In order to move the locking mechanism to the unlocked configuration, so that the wing tip device 12 may be moved to the ground configuration, at least one of the first part and second part is rotated such that the flanges 24, 26, and 28, are not obstructed by the internal chambers 40, 42, 44, and may be withdrawn by longitudinal movement along the outer apertures 34, 36, 38.

(15) At least one of the first part and second part may include a toothed outer surface. The toothed outer surface may be driven by a toothed drive unit, in order to rotate the first part or second part, thereby moving the locking mechanism between the locked configuration and unlocked configuration.

(16) FIG. 7 shows a second embodiment of the invention, where the second part 70 includes internal chambers 72, 74, and a third internal chamber (not shown), with a threaded orientation. The first part corresponds with the first part as described with respect to the first embodiment of the invention, so will not be described separately again. The thread within the chambers 72, 74, means that as the first part or second part is rotated to move the locking mechanism into the locked configuration, the thread acts on the first part to pull in the longitudinal direction, thereby tightening the connection between the first part 20 and the second part 70. This may provide a more secure locking mechanism. The thread may also act to compensate for any wear in the first part and second part by preloading the locking mechanism as the first part 20 and second part 70 are tightened together.

(17) FIG. 8 shows a male locking pin 80 with locking channels 82, 84, 86, located in the outer surface of the male locking pin. FIG. 9 shows a cross section of a female receiving portion 90 which includes a number of pins 92, 94, 96, to engage with the corresponding locking channels.

(18) 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.

(19) The flanges extending from the male locking member may be tapered. The tapered flanges may be oriented such that rotating the male locking member into the locked configuration tightens the engagement between the male locking member and the female receiving portion.

(20) 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.