Locking device

Patent metadata

Field	Value
Publication number	US-10569858-B2
Application number	US-201715849583-A
Country	US
Kind code	B2
Filing date	Dec 20, 2017
Priority date	Dec 21, 2016
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof. The 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 the ground configuration with span of the wing is reduced. The wing further comprises a locking mechanism including a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush.

First claim

The invention claimed is:

1. An aircraft wing comprising:
a fixed wing, and a wing tip device at the tip of the fixed wing, wherein the 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, wherein in the ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced,

a locking mechanism for locking the wing tip device in the flight configuration, the locking mechanism comprising:
a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device,
a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin when the wing tip device is in the flight configuration such that movement of the wing tip device out of the flight configuration is prevented,
a bush housing within which is the bush and the bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush,
wherein a frictional force to be overcome to allow movement of the bush relative to the bush housing in the direction of the longitudinal axis is less than a frictional force to be overcome to allow movement of the locking pin relative to the bush in the direction of the longitudinal axis.

2. The aircraft wing as in claim 1 , wherein the locking pin is associated with an actuator arranged to move the locking pin into and out of engagement with the bush.

3. The aircraft wing as in claim 1 , wherein the wing tip device and the fixed wing are separated along an oblique cut plane passing through the upper and lower surfaces of the wing, the oblique cut plane being orientated normal to the axis of rotation.

4. The aircraft wing as in claim 1 , wherein the wing tip device and fixed wing are connected by a rotational joint, and the movement between the flight configuration and ground configuration comprises rotational movement around the rotational axis of the rotational joint.

5. The aircraft wing as in claim 4 , wherein the rotational joint comprises a slew ring.

6. The aircraft wing as in claim 5 , wherein the slew ring comprises an inner race fixed to one of the fixed wing and wing tip device, and an outer race fixed to the other of the fixed wing and wing tip device, and the bush is configured to stop relative rotational movement of the inner race and outer race when the locking mechanism is in the locked configuration.

7. The aircraft wing as in claim 1 , wherein the bush comprises an aperture shaped to receive the locking pin.

8. The aircraft wing as in claim 1 , wherein the locking pin comprises flatted edge portions.

9. The aircraft wing as in claim 1 , wherein an interface between the bush and the bush housing comprise one or more flexible washers.

10. The aircraft wing as in claim 1 , wherein an interface between the bush and the bush housing comprise one or more O-rings.

11. The aircraft wing as in claim 1 , wherein an interface between the bush and the bush housing allows relative rotational movement between the bush and bush housing.

12. An aircraft comprising the aircraft wing in claim 1 .

13. A method of locking an aircraft wing, the aircraft wing as claimed in claim 1 , the method comprising the steps of: moving the wing tip device into the flight configuration, and moving the locking pin into the bush, such that movement of the wing tip device out of the flight configuration is prevented.

14. The method of claim 13 , further comprising: moving the locking pin out of the bush, such that movement of the wing tip device out of the flight configuration is allowed.

Assignees

• Airbus Operations Ltd

Inventors

• Brakes David
• Wildman Eric

Classifications

• F16F2222/04

  Friction · CPC title

• F16F1/38

  with a sleeve of elastic material between a rigid outer sleeve and a rigid inner sleeve or pin {, i.e. bushing-type (hydraulically-damped bushes F16F13/14; suppression of vibrations in rotating systems by making use of elastomeric spring members between rotating elements, driveline torque being transmitted therebetween F16F15/126, by making use of a dynamic damping mass attached to a rotating element by means of elastomeric springs F16F15/14; pivots per se F16C11/00; elastic or yielding bearings or bearing supports F16C27/00; parts of sliding-contact bearings, e.g. bushes F16C33/04)} · CPC title

• F16F1/32

  Belleville-type springs (friction-clutch diaphragm springs F16D13/583) · CPC title

• F16B21/00

  Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it (riveted or deformable spigots F16B19/04; for gudgeon pins F16J1/18); Stud-and-socket releasable fastenings · CPC title

• B64C23/072

  the wing tip airfoil devices being moveable in their entirety · CPC title