# US 11,305,861 B2 · Wing assembly mount

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- Number: US 11,305,861 B2
- Document ID: US11305861B2
- Status: Granted
- Kind: B2
- Application number: 16/507,322
- Filed: 2019-07-10
- Published: 2020-01-16
- Granted: 2022-04-19
- Earliest claimed: 2018-07-12
- Assignees: Airbus Operations GmbH
- Applicants: Airbus Operations Limited
- Inventors: Henry Edwards
- Web page: https://patentgrep.com/patent/US11305861B2

## CPC

- B64C 1/26: Attaching the wing or tail units or stabilising surfaces
- B64C: AEROPLANES; HELICOPTERS

## Abstract

A wing assembly mount for mounting a wing to a fuselage of an aircraft. The wing assembly mount includes a spigot arrangement between a wing assembly and a fuselage assembly. The spigot arrangement is able to react a load between the wing assembly and the fuselage assembly.

## Claims

### Claim 1

An aircraft comprising:
a wing assembly;
a fuselage assembly above the wing assembly,
a wing assembly mount between the wing assembly and the fuselage assemble, the wing assembly mount including:
a spigot arrangement configured to react a load between the wing assembly and the fuselage assembly, wherein the spigot arrangement includes:
a spigot mounted to one of the wing assembly mount and the fuselage assembly, wherein the spigot is oriented along a z-direction of the aircraft, and
a spigot bush mounted to the other of the wing assembly mount and the fuselage assembly, wherein the spigot bush forms a sleeve oriented along the z-direction and configured to receive the spigot to allow the spigot to slide vertically within the sleeve.

### Claim 2 (depends on 1)

The aircraft of claim 1, wherein the spigot arrangement is configured to react loads acting in an plane defined by a x-direction and a y-direction of the aircraft, wherein the x-direction and the y-direction are both perpendicular to the z-direction, and wherein the spigot arrangement does not react to loads along the z-direction.

### Claim 3 (depends on 1)

The aircraft of claim 1, wherein the spigot is the only spigot on the wing assembly mount and on the fuselage assembly.

### Claim 4 (depends on 3)

The aircraft of claim 3, comprising a side load connection configured to react a load acting about the spigot arrangement.

### Claim 5 (depends on 1)

The aircraft of claim 1, wherein the spigot arrangement is offset from a centerline of the wing assembly.

### Claim 6 (depends on 1)

The aircraft of claim 1, wherein the wing assembly is a tip-to-tip wing assembly.

### Claim 7 (depends on 1)

The aircraft of claim 1, further comprising a connector arrangement configured to connect between the wing assembly and the fuselage assembly.

### Claim 8 (depends on 7)

The aircraft of claim 7, wherein the connector arrangement is configured to carry a load in the z-direction of the aircraft.

### Claim 9 (depends on 7)

The aircraft of claim 7, wherein the connector arrangement is configured to permit rotation about an axis extending in an x-direction of the aircraft.

### Claim 10 (depends on 7)

The aircraft of claim 7, wherein the connector arrangement comprises a plurality of shackle connections.

### Claim 11 (depends on 10)

The aircraft of claim 10, in which two of the shackle connections are disposed on one side of a centerline of the wing assembly, and wherein the spigot arrangement is disposed between the two of the shackle connections.

### Claim 12 (depends on 10)

The aircraft of claim 10, wherein at least two of the shackle connections are configured to mount to a forward spar of the wing assembly, and at least two additional ones of the shackle connections are configured to mount to a rearward spar of the wing assembly.

### Claim 13 (depends on 1)

The aircraft of claim 1, wherein the connector arrangement is configured to provide a hanging connection to carry the load of the wing assembly in the z-direction on the fuselage assembly.

### Claim 14 (depends on 1)

The aircraft of claim 1, wherein the spigot arrangement is configured to connect to a frame of the fuselage assembly.