CROSS RELATED APPLICATION

This application claims priority to United Kingdom Patent Application GB 1905750.4, filed Apr. 25, 2019, the entire contents of which is hereby incorporated by reference.

TECHNICAL FIELD

The present invention relates to components configured to be joined to further components, to assemblies of such components joined to further components, to aircraft comprising such components, and to methods of joining components.

BACKGROUND

Most conventional aircraft have engines mounted to the wings by engine mounting pylons. For commercial airliners there is a trend toward higher bypass ratio engines, which have larger diameters than lower bypass ratio engines. To accommodate large diameter engines whilst maintaining sufficient clearance between the engine and the ground it is desirable to minimize the vertical distance between the top of the engine and the lower surface of the wing.

In order to minimize the vertical distance between the top of the engine and the lower surface of the wing, it is desirable to attach the engine mounting pylon directly to the wing. However; the lower surface of the wing is curved, due to the aerofoil shape whilst the upper surface of an engine mounting pylon is typically substantially flat (planar). The upper surface of the engine mounting pylon will therefore only abut the lower surface of the wing over a relatively small area. In order to allow fastening together of the pylon and the wing, and effective load transmission therebetween, it is therefore desirable to provide some sort of interface component to fill the gaps between the upper surface of the pylon and the lower surface of the wing, at least in the locations where fasteners joining the pylon and wing are present.

SUMMARY

A first aspect of the present invention provides a component which is configured to be joined to a further component in a preselected relative orientation of the component and the further component. The further component has an interface surface and the component is configured to contact the interface surface when joined to the further component. The component comprises: a surface disposed on a side of the component intended to face the interface surface when the component is joined to the further component, a plurality of recesses formed in the surface, and a plurality of spacer elements. Each recess has a preselected orientation relative to the component, the preselected orientation being selected in dependence on the preselected relative orientation of the component and the further component. Each spacer element comprises a contact surface configured to contact the interface surface when the component is joined to the further component. Each spacer element is disposed in one of the recesses such that the orientation of a given contact surface is defined by the orientation of the corresponding recess.

Optionally, the curvature of the surface is different to the curvature of the interface surface. Optionally, the surface is curved and the interface surface is substantially flat.

Optionally, the shape of each spacer element matches the shape of the recess in which it is disposed. Optionally, each recess and each spacer element is cylindrical.

Optionally, all of the recesses have substantially the same diameter.

Optionally, all of the recesses have the same orientation relative to the component.

Optionally, there is an interference fit between each spacer element and the recess in which it is disposed.

Optionally, a fastener hole extends through at least one spacer element in a direction substantially perpendicular to the contact surface.

Optionally, each recess comprises a counterbore.

A second aspect of the invention provides an assembly. The assembly comprises a first structure which defines a datum plane for the assembly, and a second structure fixedly attached to the first structure such that the second structure has a preselected orientation relative to the datum plane. The first structure comprising a first surface and the second structure comprises a second surface. The first surface comprises a plurality of sockets extending into the first surface at a predefined angle to the datum plane. Each socket contains an interface component having a first end in contact with a base of the socket and a second end in contact with the second surface.

Optionally, the second end of each interface component comprises an interface surface which is in contact with the second surface, and the orientation of each interface surface is set by the orientation of the corresponding socket.

Optionally, the first structure is fixedly attached to the second structure by at least one fastener, and the fastener extends through one of the interface components.

Optionally, the fastener comprises a tension bolt.

Optionally, the assembly further comprises a third structure attached to the second structure such that the first structure is between the third structure and the second structure. Optionally, the first structure comprises a plate having a further surface opposite to the first surface, and the further surface is configured to match a surface of the third structure which faces the first structure.

Optionally, the third structure is comprised in a first aircraft structure and the second structure is comprised in a second aircraft structure. Optionally, the first aircraft structure is a wing and the second aircraft structure is an engine mounting pylon.

A third aspect of the invention provides an aircraft comprising the component of the first aspect or the assembly of the second aspect.

A fourth aspect of the invention provides a method of joining a first component to a second component in a predetermined relative position and orientation of the first and second components. The method comprises:providing a first component having a first surface;providing a second component having a second surface;forming a plurality of recesses in the first surface, such that each recess is oriented relative to the first component based on a desired relative orientation of the first and second components when joined;providing a plurality of spacer elements, each spacer element being configured to be received in one of the recesses and having a contact surface configured to contact the second surface when the second component is joined to the first component;inserting a spacer element into each recess;arranging the second component on the spacer elements such that the contact surfaces of the spacer elements are in contact with the second surface and the first component and the second component are in the desired relative position and orientation; andconnecting the first component to the second component.

Optionally, the first component and the plurality of spacer elements together comprise a component according to the first aspect.

Optionally, performance of the method results in the formation of an assembly according to the second aspect.

