RELATED APPLICATION

This application claims priority United Kingdom Patent Application GB 1811409.0, filed Jul. 12, 2018, the entirety of which is incorporated by reference.

FIELD OF THE INVENTION

The present invention relates to a wing assembly mount. In particular, the present invention relates to a wing assembly mount for mounting the wing assembly to a fuselage assembly of an aircraft. The present invention also relates to an aircraft assembly and a method of assembling a wing assembly with a fuselage assembly of an aircraft.

BACKGROUND OF THE INVENTION

Different methods are known for joining the wing and fuselage of an aircraft. Typically, the wing will comprise a centre wing box and two outer wing sections extending from the centre wing box. The centre wing box is connected to the fuselage by a wing box to fuselage joint, and the outer wing sections are each joined to the centre wing box by an outer wing section to wing box joint. These joints are typically rigid joints and use a combination of buttstraps, crown fittings and threaded fastener joints to join these assemblies together. Such an assembly process is complicated and time consuming. With this assembly process, the centre wing box to fuselage joint is assembled first, with the outer wing section to wing box joints being subsequently connected to the centre wing box-fuselage assembly.

In another assembly process it is known to provide a fully assembled wing, also known as a tip-to-tip wing, which is assembled prior to connecting with the fuselage. By providing a tip-to-tip wing assembly, it is possible to remove the need to have a captive centre wing box and allows the wing assembly to be assembled separately to the fuselage. However, such an approach leads to a less weight efficient construction and has a complicated assembly.

It is necessary to constrain the forces acting in all directions at the wing to fuselage joint in order to prevent the wing and fuselage moving relative to each other. As such, rigid joints such as direct lug connections may be used to join the tip-to-tip wing to the fuselage.

SUMMARY OF THE INVENTION

According to an aspect of the invention, there is provided a wing assembly mount for mounting the wing assembly to a fuselage assembly of an aircraft, the mount comprising a spigot arrangement configured to react a load between the wing assembly and the fuselage assembly.

With such an arrangement it is possible to simplify assembly of the fuselage and wing assembly. Alignment of fixings between the assemblies may be simplified.

The spigot arrangement may comprises a spigot configured to extend in a z-direction of the aircraft.

With such an arrangement, the alignment of the wing and fuselage assemblies is simplified during assembly. The spigot arrangement provides a discrete attachment point, which simplifies alignment of the remainder of the joint. The reaction of loads through the mount may be simplified, and reduce undesired loads from being transferred through the mount. Drag loads and side loads may be carried by the spigot arrangement.

An “x-direction” of an aircraft relates to a roll axis direction. That is, in a longitudinal axis direction of a fuselage of the aircraft. A “y-direction” of an aircraft relates to a pitch axis direction. That is, in a wingspan direction of a wing. The “z-direction” of an aircraft relates to a yaw axis direction. The yaw axis direction is substantially perpendicular to the x-direction along the longitudinal axis of a fuselage of the aircraft and substantially perpendicular to the y-direction along the wingspan direction of a wing.

The spigot arrangement may be configured to react loads acting in an x-direction and a y-direction of the aircraft.

The mount may comprise a spigot-receiving bush. The bush may be a plain bearing. The spigot may be configured to be on one of the wing assembly and the fuselage assembly. The spigot-receiving bush may be configured to be on the other of the wing assembly and the fuselage assembly.

The spigot arrangement may be limited to one spigot configured to extend in a z-direction of the aircraft.

With such an arrangement, unnecessary bending loads may be restricted from being transferred through the spigot arrangement.

The mount may comprise a side load connection configured to react loads about an axis of the spigot.

With such an arrangement, the transfer of loads may be simplified.

The side load connection and the spigot arrangement may be spaced in the y-direction of the aircraft, and may be disposed on opposing sides of the centreline of the wing assembly.

The side load connection may be a shackle connection.

The spigot arrangement may be offset from a centreline of the wing assembly.

Such a configuration helps to minimise fuselage crushing due to wing bend about the x-direction. Wear of the spigot arrangement may be minimised.

The wing assembly may be a horizontally-extending wing assembly. The wing assembly may be a low-wing assembly.

The wing assembly may be a tip-to-tip wing assembly.

The mount may further comprise a connector arrangement configured to connect between the wing assembly and the fuselage assembly.

The connector arrangement may be configured to carry a load in a z-direction of the aircraft. As such, the load in the z-direction may be carried by the mount in a straightforward manner.

The connector arrangement may be configured to permit rotation about an axis extending in an x-direction of the aircraft. As such, the transfer of wing bending loads to the fuselage assembly may be minimised.

The connector arrangement may comprise a plurality of shackle connections.

Two of the shackle connections may be disposed on one side of a centreline of the wing assembly. The spigot arrangement may be disposed between the two of the shackle connections.

By locating the spigot arrangement between two of the shackle connections it is possible to minimise relative displacement of the shackle and shackle bush in the z-direction. Such movement may result from wing-bending.

The connector arrangement may be configured to provide a hanging connection to carry the load of the wing assembly in the z-direction on the fuselage assembly.

The spigot arrangement may be configured to connect to a frame of the fuselage assembly.

At least two shackle connections may be configured to mount to a forward spar of the wing assembly, and at least two further shackle connections may be configured to mount to a rearward spar of the wing assembly.

According to a further aspect of the invention, there is provided a wing assembly mount for mounting the wing assembly to a fuselage assembly of an aircraft, comprising a spigot arrangement, and a shackle arrangement.

According to a further aspect of the invention, there is provided an aircraft assembly comprising a wing assembly, a fuselage assembly and a wing assembly mount as described above.

The aircraft assembly may be an off-wing mounted engine configuration, such as a rear mounted engine configuration.

According to a further aspect of the invention, there is provided a method of assembling a wing assembly with a fuselage assembly of an aircraft, the method comprising: locating the wing assembly relative to the fuselage assembly with a spigot; connecting a connector arrangement between the wing assembly and the fuselage assembly to support the wing assembly on the fuselage assembly.

