Rotational joint for an aircraft folding wing and method of assembly

Patent metadata

Field	Value
Publication number	US-10633076-B2
Application number	US-201715618977-A
Country	US
Kind code	B2
Filing date	Jun 9, 2017
Priority date	Jun 9, 2016
Publication date	Apr 28, 2020
Grant date	Apr 28, 2020

Abstract

A method of rotatably couple a wing tip device (4) to a fixed wing (3) by a rotational joint (101) having an outer race (8) and an inner race (9) that is received in the outer race (8) one of the inner and outer races comprises a male member (76) and the other is a two-part assembly comprising a first part (9a) and a second part (9b) that together form a female member (72), the method brings the first and second parts together to form the female member (72) about the male member (76) such that the male member (76) is received in the female member (72) and fixing the first and second parts (9a, 9b) such that the race that is rotationally fixed relative to the wing tip device (4) is axially and radially retained relative to the race that is rotationally fixed relative to the fixed wing (3).

First claim

The invention claimed is:

1. A method of assembly of an aircraft wing, the aircraft wing comprising a fixed wing and a wing tip device at the tip of the fixed wing, the wing tip device being rotatable relative to the fixed wing between:
a flight configuration for use during flight, and
a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is rotated relative to the fixed wing such that the span of the wing is reduced,
the aircraft wing comprising a rotational joint that rotatably couples the wing tip device to the fixed wing, to allow the wing tip device to rotate relative to the fixed wing between the flight and ground configurations,
the rotational joint comprising an outer race and an inner race that is received in the outer race, radially inwardly of the outer race, configured such that the inner and outer races are rotatable relative to each other about a rotational axis,
one of the inner and outer races is rotationally fixed relative to the wing tip device and the other is rotationally fixed relative to the fixed wing such that as the wing tip device rotates relative to the fixed wing, the inner and outer races are rotated relative to each other about the rotational axis,
one of the inner and outer races comprises a male member and the other comprises a female member, configured such that when the male member is received in the female member, the race that is rotationally fixed relative to the wing tip device is axially and radially retained relative to the race that is rotationally fixed relative to the fixed wing,
wherein the race that comprises the female member is a two-part assembly comprising a first part and a second part that together form the female member and
wherein the method comprises the steps of assembling the rotational joint by receiving the inner race in the outer race by bringing the first and second parts together to form the female member about the male member such that the male member is received in the female member and fixing the first and second parts relative to each other such that the race that is for being rotationally fixed relative to the wing tip device is axially and radially retained relative to the race that is for being rotationally fixed relative to the fixed wing,
wherein, when the aircraft wing is assembled, the wing tip device and the fixed wing are separated along an oblique cut plane passing through upper and lower surfaces of the wing, and the wing tip device is rotatable between the flight and ground configurations, about an axis of rotation oriented normal to the oblique cut plane, such that the fixed wing and the wing tip device do not clash when rotating between the flight and ground configurations.

2. The method of assembly according to claim 1 wherein the inner race is received in the outer race by bringing the first and second parts together from opposite axial sides of the male member to form the female member about the male member such that the male member is received in the female member.

3. The method of assembly according to claim 1 wherein the outer race comprises the male member and the inner race comprises the female member, wherein assembling the rotational joint comprises receiving the inner race in the outer race by receiving the first and second parts through opposite axial ends of the outer race and bringing the first and second parts together to form the female member about the male member.

4. The method of assembly according to claim 1 wherein the inner and outer races are configured such that when the male member is received in the female member, the radially inner periphery of the outer race and the radially outer periphery of the inner race cooperate such that the race that is for being rotationally fixed relative to the wing tip device is radially retained relative to the race that is for being rotationally fixed relative to the fixed wing.

5. The method of assembly according to claim 1 wherein the male and female members are configured such that when the male member is received in the female member, the male and female members axially overlap such that the race that is for being rotationally fixed relative to the wing tip device is radially retained relative to the race that is for being rotationally fixed relative to the fixed wing.

6. The method of assembly according to claim 5 wherein an internal face of the female member defines a space for receiving the male member and, when the male member is received in the female member, the internal face of the female member axially overlaps the male member such that the race that is for being rotationally fixed relative to the wing tip device is radially retained relative to the race that is for being rotationally fixed relative to the fixed wing.

7. The method of assembly according to claim 1 wherein when the male member is received in the female member, the inner and outer races are radially fixed relative to each other.

8. The method of assembly according to claim 7 wherein when the male member is received in the female member, the inner race forms a radial fit with the outer race.

9. The method of assembly according to claim 7 wherein when the male member is received in the female member, the male member forms a radial fit with the female member.

10. The method of assembly according to claim 1 wherein the male and female members are configured such that when the male member is received in the female member, the inner and outer races are axially fixed relative to each other.

11. The method of assembly according to claim 1 wherein the male and female members are configured such that when the male member is received in the female member, the male member forms a zero clearance fit with the female member.

12. The method of assembly according to claim 1 wherein the male and female members are configured such that as the inner and outer races are rotated relative to each other, the male and female members cooperate with each other to guide the relative rotation.

13. A method of assembling an assembly of an aircraft comprising the method of assembling the aircraft wing according to the method of claim 1 and further comprising assembling the aircraft wing with an aircraft fuselage.

14. A method of assembly a rotational joint for rotatably coupling a wing tip device to a fixed wing such that the wing tip device is rotatable relative to the fixed wing between:
a flight configuration for use during flight, and
a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is rotated relative to the fixed wing such that the span of the wing is reduced,
the rotational joint comprising an outer race and an inner race that is received in the outer race, radially inwardly of the outer race, configured such that the inner and outer races are rotatable relative to each other about a rotational axis,
one of the inner and outer races is configured to be rotationally fixed relative to a wing tip device and the other is configured to be rotationally fixed relative to a fixed wing, wherein the inner and outer races are rotated relative to each other about the rotational axis,
one of the inner and outer races comprises a male member and the other comprises a female member, configured such that when the male member is received in the female member, the race that is rotationally fixed relative to the wing tip device is axially and radially retained relative to the race that is rotationally fixed relative to the fixed wing,
wherein the race that comprises the female member is a two-part assembly comprising a first part and a

Assignees

• Airbus Operations Ltd

Inventors

• Bishop Benjamin

Classifications

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C3/56 Primary

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

• Y02T50/10

  Drag reduction · CPC title