GB2582159A

GB2582159A - Load-transferring components

Info

Publication number: GB2582159A
Application number: GB1903419.8A
Authority: GB
Inventors: Tulloch William; Wilson Fraser
Original assignee: Airbus Operations Ltd
Current assignee: Airbus Operations Ltd
Priority date: 2019-03-13
Filing date: 2019-03-13
Publication date: 2020-09-16
Also published as: GB201903419D0; GB201915247D0

Abstract

A component for transferring a load applied to an opening 21 in the component to another location of the component comprises a matrix material and at least one longitudinal reinforcing clement 23 embedded in the matrix material which is under tension, arranged in a loop around the opening 21 and comprises a section that is aligned with the load path between the opening 21 and the other location of the component. The reinforcing element 23 contacts one or more pins 72a & 72b embedded within the matrix material and located inside the loop. The component comprises a further reinforcing element 24 arranged in a loop around the opening 21 and which forms at least a part of the surface of the opening 21. The component can be an aircraft rib which supports landing gear or an engine and can be made from an aluminium or titanium matrix with an aluminium oxide fibre, carbon fibre or silicon carbide fibre reinforcing element. The component can be made by casting, additive manufacturing, beam deposition or hot isostatic pressing.

Description

LOAD-TRANSFERRING COMPONENTS

TECHNICAL FIELD

[0001] The present invention relates to load-transferring components configured to transfer load from an opening in the component to a predetermined separate location on the component via a load path, to assemblies comprising such components, and to methods of manufacturing such components.

BACKGROUND

R10021 Metal matrix composites (MMCs) are composite materials comprising elements of a first material (such as fibres or spheres) distributed within a matrix of a second, metallic material. The presence of the first material elements typically changes one or more physical properties of the matrix material. Which properties are altered and to what degree depends on the nature of the first material elements, and/or on the relative proportions of the two materials.

[0003] Aircraft components, particularly components for commercial airliners, are preferably as lightweight as possible, whilst also being low cost and easy to manufacture. However; many aircraft components must withstand extreme environments during operation, and must be very reliable. Using conventional materials and techniques, it is often difficult to create certain aircraft components to have adequate physical properties without sacrificing weight, cost, or ease of manufacture. The present invention seeks to address this issue.

SUMMARY

[0004] A first aspect of the present invention provides a load-transferring component.

The component has an opening and is configured to, during operation of the component, transfer load from the opening to a predete -mined separate location on the component. via a load path. The component comprises a matrix material and at least one longitudinal reinforcing element embedded in the matrix material. The reinforcing element is arranged in a loop around the opening, and the loop comprises a section that is aligned with the load path between the opening and the predetermined separate location.

[0005] Optionally, the section is substantially straight.

[0006] Optionally, the opening is configured to receive a pin or spigot comprised in a further component.

[0007] Optionally, the reinforcing element is ai-ranged in a plurality of loops around the opening, and each loop comprises a section that is aligned with the load path between the opening and the predetermined separate location.

[0008] Optionally, the predetermined separate location is a location of a mechanism for transferring load from the component to a further component. Optionally the mechanism comprises a fastener connecting the component to the further component.

[0009] Optionally, the component comprises a further longitudinal reinforcing element embedded in the matrix material, and the further reinforcing element is arranged in a loop around the opening, wherein the shape of the loop matches the circumferential shape of the opening.

[0010] Optionally, the further reinforcing element is integrally formed with the reinforcing element.

[0011] Optionally, the further reinforcing element forms at least part of a circumferential surface of the opening.

[0012] Optionally, the reinforcing element is under tension.

[0013] Optionally, the component further comprises one or more pins embedded in the matrix material, and the one or more pins are within the loop of the reinforcing element and are in contact with the reinforcing element.

[0014] Optionally, the matrix material is aluminium.

[0015] Optionally, the reinforcing clement comprises one of: an aluminium oxide fibre; a carbon fibre; a silicon carbide fibre.

[0016] Optionally, the component is an aircraft component. Optionally, the component is a gear rib.

[0017] A second aspect of the invention provides an assembly comprising a component according to the first aspect, connected to a further component. The component is configured to transfer load to the further component and the predetermined separate location is located at a join between the component and the further component.

[0018] Optionally, the component is connected to the further component by a fastener and the predetermined separate location is the location of the fastener.

[0019] Optionally, the component is formed integrally with the further component.

[0020] Optionally, the assembly further comprises a second further component engaged with the opening such that the second further component exerts a force on the component in a radial direction of the opening during operation of the assembly, and the component is configured to transfer load from the second further component to the further component.

[0021] A third aspect of the invention provides an aircraft comprising the component.

according to the first aspect or the assembly according to the second aspect.

[0022] A fourth aspect of the invention provides a method of manufacturing a load-transferring structure having an opening and being configured to transfer load from the opening to another part of the structure. The method comprises: arranging a longitudinal reinforcing member such that it forms a loop enclosing the intended location of the opening, wherein the loop has a section extending between the intended location of the opening and the intended location of the other part of the structure, the section being aligned with a direction along which load is intended to be transferred during operation of the structure; and forming the structure by arranging a matrix material on the reinforcing member such that the matrix material at least partially surrounds the reinforcing member, and defines the opening and forms the other part of the structure.

[0023] Optionally, the method further comprises arranging a further longitudinal reinforcing member around the intended location of the opening, such that the further reinforcing member will lie adjacent the circumferential surface of the opening in the completed structure.

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which: [0025] Figure la is a schematic cross-section through a first example component according to the invention; [0026] Figure lb is a schematic cross-section through an assembly comprising the first example component connected to a further component; [0027] Figure 2 is a schematic perspective view of a second example component according to the invention; [0028] Figure 3 is a schematic perspective view of a third example component according to the invention; [0029] Figure 4 is a schematic perspective view of a fourth example component according to the invention; [0030] Figure 5 is a schematic front view of an example aircraft comprising a component according to the invention; [0031] Figure 6 is a flow chart illustrating an example method of manufacturing a component according to the invention; and [0032] Figures 7a and 7b show example moulds for manufacturing a component according to the invention, during a manufacturing process.

DETAILED DESCRIPTION

[0033] The examples described herein relate to load-transferring components, assemblies comprising such components, and methods of manufacturing such components. Each example load-transferring component has an opening and is configured to, during operation of the component, transfer load from the opening to a predetermined separate location on the component via a load path. Each example component comprises a matrix material and at least one longitudinal reinforcing element embedded in the matrix material. In each example the reinforcing element is arranged in a loop around the opening, the loop comprising a section that. is aligned with the load path between the opening and the predetermined separate location.

[0034] By virtue of arranging the reinforcing element aligned with a load path, the reinforcing element specifically provides additional strength in the most highly loaded regions of the component. This enables the surrounding matrix material to he a material which is not, by itself, particularly strong. It is anticipated that the volume of matrix material will be significantly larger than the volume of reinforcing elements in the component, so the overall cost, weight and machinability of the component is largely determined by the choice of matrix material. The invention permits components which must transfer large loads during operation to be formed mainly from relatively weak materials such as aluminium, which are desirable because they are relatively lightweight, low cost and and/or easily machinable compared to intrinsically stronger alternatives such as titanium.

[0035] Figure la is a cross-section through an example load-transferring component 10 according to the invention. The component 10 may be a component of a vehicle, or of any other mechanical system. In some examples the component 10 is an aircraft component. In this example the component 10 is a lug. The component 10 has an opening 11 which extends completely through the component 10 (that is, the opening has the form of a through-hole). Other examples are possible in which the opening does not extend completely through the component 10, but instead has the form of a recess. In the illustrated example the opening 11 is circular, although that need not be the case in other examples. The opening 11 may be configured to receive a pin, spigot, bearing, or the like, such that loads are transferred into the component 10 from the pin, spigot, bearing or the like, via the opening 11. The component 10 is configured to receive loads acting radially with respect to the axis of the opening 11.

[0036] The component 10 is configured to, during operation of the component 10, transfer load from the opening 11 to a predetermined separate location on the component 10 via a load path. "Operation" of the component 10 means that the component 10 is receiving a load (e.g. from a further component engaged with the opening 11) of a type that it is designed to transfer. Where the component 10 is designed to he connected to one or more further components in order to perform its function, operation of the component should he understood to mean that such connections are present. Operation of the component 10 may (but need not) mean operation of a vehicle or other mechanical system in which the component 10 is comprised.

[0037] The predetermined separate location to which load is transferred may typically be located at an edge of the component 10. The predetermined separate location may he located on a surface of the component 10. The predetermined separate location may be the location of a mechanism for transferring load from the component 10 to a further component. Such a mechanism may be, for example, a fastener connecting the component 10 to the further component. In some examples the predetermined separate location may be located at a join between the component 10 and a further component. In the illustrated example, the component 10 is configured to transfer load from the opening 11 to each of the corners of the component 10, as will he explained in more detail with reference to Figure 1 b.

[0038] The component 10 is formed from a metal matrix composite (MMC). The composite comprises reinforcing elements 13, 14, embedded within a metal matrix 12. The reinforcing elements 13, 14 comprise longitudinal dements. A "longitudinal" element is any structure having one dimension that is significantly longer than any other dimension. For example wires, fibres, tapes, threads and the like are all considered to he longitudinal elements. The reinforcing elements 13, 14 may comprise a flexible material (although it will he appreciated that flexing of the reinforcing elements 13, 14 is substantially or entirely prevented when the reinforcing elements 13, 14 are embedded in the matrix material 12).

[0039] The reinforcing elements 13, 14 are arranged in loops around the opening 11 (that is, each loop encloses the opening 11). In the illustrated example, each reinforcing element 13, 14 comprises a fibre. The reinforcing elements may, for example, comprise aluminium oxide fibres, silicon carbide fibres, galvanic-coated carbon fibres, or any other high strength fibres. The matrix material 12 is a metallic material, such as aluminium, titanium, or any other metallic material. Preferably the matrix material is relatively lightweight, low cost, and easy to machine.

[0040] A first reinforcing element 13 comprises one or more loops, each of which has a substantially straight portion which is aligned with a load path between the opening 11 and another location on the component 10. The number of loops may depend, for example, on the magnitude of the load required to be transferred by the component 10. In the illustrated example, each loop of the first reinforcing element 13 has three substantially straight portions 13a, 13b, 13c. The straight portions 13a and 13b are aligned with load paths between the opening 11 and other locations on the component 10, whereas the straight portions 13c are not aligned with any such load path and merely serve to connect the straight portions 13a and 13b in an efficient manner. In the illustrated example the loops comprised in the first reinforcing element 13 differ in size. In particular, the outermost loop extends significantly closer to the corners than the innermost loop. This arrangement advantageously distribute the reinforcing element 13 over the most highly loaded regions of the component 10. In some examples the first reinforcing element 13 may comprise a single structure -that is, a single continuous fibre may form all of the loops of the first reinforcing element 13. In other examples the first reinforcing element 13 may comprise multiple separate structures. For example, each loop may be formed by a different fibre.

[0041] The first reinforcing clement 13 is under tension. The first reinforcing element 13 being under tension is advantageous for manufacturing the component, as it facilitates maintaining a desired arrangement of the fibres of the first reinforcing element during the manufacturing process. Additionally, tension in the first reinforcing element 13 provides an internal compressive pre-load in the component 10, which enhances the ability of the component 10 to resist crack initiation.

[0042] A second reinforcing clement 14 conforms closely to the circumference of the opening 11. The second reinforcing element 14 comprises one or more loops, which are disposed within the innermost loop of the first reinforcing element 13. The number of loops may depend, for example, on the magnitude of the load required to he transferred by the component 10. Each loop of the second reinforcing element 14 conforms to the shape of the opening 11 (which in this example is circular) and all the loops have substantially the same diameter. In the illustrated example a thin layer of the matrix material 12 lies inside the first reinforcing element 14, such that the inner surface of the opening comprises matrix material 12. Other examples are envisaged in which the inner surface of the opening 11 is at least partially formed by the second reinforcing element 14. In some examples the second reinforcing element 14 is formed integrally with the first reinforcing element 13. That is, the first reinforcing element 13 may comprise a first part of a fibre and the second reinforcing element 14 may comprise a second, different part of the same fibre. In other examples the second reinforcing element 14 is a separate structure to the first reinforcing element 13. In some examples the second reinforcing element 14 may comprise multiple structures, such as multiple fibres. The second reinforcing clement 14 is under tension. It is advantageous for the second reinforcing element 14 to be under tension, for the same reasons as the first reinforcing element 13, as discussed above.

[0043] Figure lb shows an example assembly 1. The assembly 1 comprises the example load-transferring component 10 connected to a further component 15 by a pair of fasteners 16a, 16b. The fasteners 16a, 16b are located at the corners of the component 10, at. each of the predetermined separate locations to which the component 10 is configured to transfer load from the opening 11. It can be seen that, in the assembly 1, the predetermined separate locations are located at the join between the component 10 and the further component 15. During operation of the component 10, a load L is applied to the opening in a radial direction of the opening (for example by a second further component engaged with the opening), as indicated by the large block arrow. The component 10 transfers load from the opening 11 to each of the fasteners 16a, lob. The fasteners 16a, 16b then transfer this load to the further component 15. The load paths Li and Ln by which load is transferred within the component 10 are illustrated by the small block arrows. It can be seen in this figure how the straight portions 13a of the first reinforcing element. 13 are aligned with the load path Li and the straight portions 13b of the first reinforcing element 13 are aligned with the load path Lo.

[0044] Figure 2 is a perspective view of a second example load-transferring component according to the invention. The features of the second example component 20 are substantially the same as corresponding features of the first example component 10, except where explicitly described otherwise. The component 20 is approximately T-shaped, and comprises a lug part 22a extending perpendicularly from a substantially flat base part 22b. The lug part 22a and the base part 22b are formed integrally from a matrix material. The lug part 22a comprises an opening 21, which is configured to receive a radial load L as indicated by the block arrow. The component 20 is configured to be connected to a further component (not illustrated) by four fasteners 26 which extend through the base part 22b.

[0045] A first reinforcing element 23 and a second reinforcing clement 24 are embedded in the lug part 22a. The shape of the lug part 22b is substantially the same as the shape of the first example component 10. However, in operation of the second example component 20 load is transferred from the opening 21 to the join between the lug part 22a and the base part 22b, and then to the locations of the fasteners 26. The predetermined separate locations to which the component 20 is configured to transfer load are therefore the locations of the fasteners 26. The load paths extending between the opening 21 and the locations of the fasteners 26 extend substantially vertically between the edges of the opening 21 and the join between the lug part 22a and the base part 22b. It can be seen that the first reinforcing element 23 has two straight sections which align with these load paths. In the illustrated example, the first reinforcing element 23 is present only in the lug part 22a. However, other examples are envisaged in which at least some loops of the first reinforcing element 23 extend into the base part 22h.

[0046] Figure 3 is a perspective view of a third example load-transferring component according to the invention. The component 30 has a lug part 32a, base part 32b, opening 31, fasteners 36, first reinforcing element 33 and a second reinforcing element 34 which are substantially the same as the corresponding parts of the second example component 20 except for the following differences.

[0047] The lug part 32a of the third example component 30 is asymmetric, such that it contains more material to the right-hand side of the opening than to the left-hand side. This is because the third example component 30 is configured, during operation, to receive a radial load L (as indicted by the block arrow) that is not perpendicular to the plane of the base part 32b. A sloping edge of the lug part 32a is substantially parallel to the direction of the load L. This shape of the lug part 32a facilitates transfer of the load L from the opening to the locations of the fasteners 36. As a consequence of the asymmetric shape of the lug part 32a, the base part 32h is wider than the base part 22h of the second example component 20. An extra pair of fasteners 36 is provided to join the base part 32b to a further component. This may enable the third example component 30 to transfer higher loads than the second example component. 20.

[0048] There is a load path extending from the opening 31 to the locations of each of the fasteners 36. The first reinforcing element 33 has a first straight section aligned with the load path between the opening 31 and the left-hand-most fasteners 36 and also has a second straight section aligned with the load path between the opening 31 and the right-hand-most. fasteners 36. The second straight section is longer than the first straight section, due to the asymmetric configuration of the component 30. In some examples the first reinforcing element 33 may also comprise a section which is aligned with a load path between the opening 31 and the centre fasteners 36.

[0049] Figure 4 shows a fourth example load-transferring component 40 according to the invention. The component 40 has a complex shape which includes three separate openings 41a-c, each of which is configured to receive a radial load L during operation of the component 40. The component 40 is configured to he joined to further structures or components above and below by fasteners 46. In this example the component 40 is an aircraft gear rib, and is configured to be attached to upper and lower covers of an aircraft wing by the fasteners 40. A main landing gear of the aircraft is connectable to the gear rib 40 via the openings 4 la-c, and during operation the gear rib 40 transfers the loads L received from the main landing gear from the locations of the openings 41a-c to a vertical part 47 of the gear nb structure.

[0050] Each opening 41a-c is comprised in a separate lug part 42a-c of the gear rib 40.

The lug parts 42a-c are formed integrally with the vertical part 47, and with the other parts of the gear rib structure (i.e. the top and bottom plates through which the fasteners 46 extend). The gear rib structure is formed from a matrix material, which may have any of the features described above in relation to Figure la. It may be advantageous in this particular example for the matrix material to comprise aluminium.

[0051] Each lug part 42a-c of the gear rib 40 has an asymmetric shape similar to the shape of the lug part 32a of the example component 30 shown in Figure 3. Each lug part 42a-c comprises a first reinforcing element 43a-c and a second reinforcing element 44a-c, which may have any of the features of any of the other example first and second reinforcing elements described above. The lug parts 42a-c are configured to transfer load from the openings 41a-c to the corners of the lug parts 42a-c where the lug parts 42a-c join the vertical part 47. The shape of each lug part 42a-c is slightly different, so the load paths through each lug part 42a-c are also slightly different. However; for each lug part 42a-c the respective first reinforcing element 43a-c is arranged in a plurality of loops which each comprise a section aligned with a load path through that lug part 42a-c.

[0052] Figure 5 shows an example aircraft 500 comprising one or more load-transferring components according to the invention. The aircraft 500 has a fuselage 501 to which a pair of wings 502a, 502b is mounted. An engine 503a, 503b and a main landing gear 504a, 5046 is mounted to each of the wings. More particularly, each wing 502a, 5026 comprises a gear rib of the type shown in Figure 4, to which the respective main landing gear is attached. The gear ribs are load-transferring components according to the invention. One or more components of the engine mounting mechanism by which each engine 503a, 503h is mounted to the corresponding wing 502a, 502h may also he load-transferring components according to the invention. For example, an aft-pickup (APU) connecting an engine mounting pylon to one of the wings 502a, 503a may comprise a load-transferring component according to the invention. In general, any load-transferring component of the aircraft 500 which is configured to transfer a load from an opening to a predetermined separate location may advantageously be a load-transferring component according to the invention.

[0053] Example methods suitable for manufacturing load-transferring components according to the invention will now be described with reference to Figure 6.

[0054] Figure 6 is a flow chart illustrating an example method of manufacturing a load-transferring structure having an opening and being configured to transfer load from the opening to another part of the structure. Such a structure may he, for example, any of the example load-transferring components discussed above.

[0055] In a first block 601, a longitudinal reinforcing member is arranged such that it forms a loop enclosing the intended location of the opening. The longitudinal reinforcing member may have any of the features of the example first reinforcing members described above. The loop has a section extending between the intended location of an edge of the opening and the intended location of the other part of the structure, and the section is aligned with a direction along which load is intended to be transferred during operation of the structure being manufactured.

[0056] Arranging the longitudinal reinforcing member may comprise winding the longitudinal reinforcing member around one or more support structures. In some examples in which the structure is to he formed by casting, the one or more support structures may he formed into a casting mould. In other examples the support structures may comprise structures that will become incorporated into the finished structure. In one such example, the support structures comprise pins fixed (by any suitable mechanism) in a rigid arrangement corresponding to the desired configuration of the loop. Such pins may be formed from a hard material which does not react with a material intended to he used as the matrix material of the structure. In some examples the support structures comprise steel pins. In sonic examples some of the support structures are formed into a casting mould and others of the support structures are separate from the casting mould.

[0057] Arranging the longitudinal reinforcing member may comprise tensioning the longitudinal reinforcing member. Where support structures are used to arrange the loops of longitudinal reinforcing member, the support structures are configured to withstand a desired amount of tension in the longitudinal reinforcing member without deforming. As discussed above, tensioning the longitudinal reinforcing member can advantageously facilitate the longitudinal reinforcing member maintaining the desired arrangement during further steps of the manufacturing process.

[0058] In some examples arranging the longitudinal reinforcing member comprises arranging a plurality of separate longitudinal elements, such as fibres. For example, a bundle of fibres may be simultaneously wound around supporting elements to efficiently form a plurality of loops. Alternatively, a single longitudinal element may be wound multiple times until a desired number of loops is formed. In some examples, a plurality of longitudinal elements may be pre-woven into an interlinked arrangement before being arranged on support structures. The winding of the longitudinal elements may be performed manually, or using an automated tool. Any technique known for arranging fibres in the manufacturing of carbon fibre reinforced plastic (CFRP) components may be used to arrange the longitudinal elements.

[0059] In an optional block 602, a further longitudinal reinforcing member is arranged around the intended location of the opening, such that the further reinforcing member will lie adjacent the circumferential surface of the opening in the completed structure. Block 602 is performed when the structure being created comprises a second reinforcing element (such as the second reinforcing element 14 of the example component 10) in addition to a first reinforcing element. Block 602 may he performed in substantially the same manner as block 601. However; a support structure for arranging the further longitudinal reinforcing member will generally comprise part of the mould. In particular, an upstanding rim feature of the mould by which the opening is formed can serve as a support structure for arranging the further longitudinal reinforcing member. Additional support structures in the form of pins or the like are not required. In examples in which casting is not used to form the structure (such that there is no mould), a support structure defining the circumference of the opening may he provided for the sole purpose of arranging the further longitudinal reinforcing member. Arranging the further longitudinal reinforcing member may comprise tensioning the further longitudinal reinforcing member, to substantially the same degree as the longitudinal reinforcing member.

[0060] Block 602 may be performed before, after or simultaneously with block 601. In some examples, the further longitudinal reinforcing member is continuous with the longitudinal reinforcing member, and the loops of the longitudinal reinforcing member and the loops of the further longitudinal reinforcing member are arranged in the same winding and tensioning process.

[0061] Figures 7a and 7h show how support structures can he used to facilitate arranging longitudinal reinforcing members (and further longitudinal reinforcing members) in loops having particular shapes, in a cast component. Figure 7a shows a mould 70a for forming the example load-transferring component 20 of Figure 2 during a process of manufacturing the component 20. The matrix material has not yet been introduced into the mould 70a. The mould 70a has an upstanding circular rim 71, configured to form the opening 21 in the finished component 20. There are also two pins 72a, 72b located in the corners of the mould. The pins 72a, 72b may be formed integrally with the mould, in which case they will not form part of the finished component 20. Alternatively, the pins 72a, 72h may be temporarily fixed to the mould 70a such that they remain in the finished component 20 when the mould 70a is removed. The first reinforcing element 23 is formed by winding a longitudinal reinforcing member (e.g. a fibre) around the top edge of the rim 71 and the pins 72a, 726, such that the longitudinal reinforcing member forms one or more loops, each of which encloses the rim 71, pin 72a and pin 72b. The second reinforcing element 24 is formed by winding a longitudinal reinforcing member around the rim 71 to form one or more loops which match the configuration of the rim 71. The loops comprised in the second reinforcing element 24 contact the entire circumference of the rim 71.

[0062] Figure 7h shows a mould 70h for forming the example load-transferring component 30 of Figure 3 by casting, during a process of manufacturing the component 30 at a stage when the matrix material has not yet been introduced into the mould 70b. The mould 70h is similar to the mould 70a in that it has an upstanding circular rim 73 for forming the opening 31 of the component 30, and two pins 74a, 74b disposed in corners of the mould adjacent the predetermined separate locations to which the component 30 is configured to transfer load. The components of the mould 70b are substantially the same as the corresponding components of the mould 70a except where explicitly stated otherwise. As with the Figure 7a example, the second reinforcing element 34 of the component 30 is formed by winding a longitudinal reinforcing member in loops around the rim 73 such that each loop conforms to the shape of the rim 73. The first reinforcing element 33 of the component 30 is formed by winding a longitudinal reinforcing member in loops around the top surface of the rim 73, the pin 74a and the pin 74h, such that each loop encloses the rim 73, pin 74a and pin 74b. The mould 70b differs from the mould 70 in that it is asymmetrically shaped, and in that the pins 74a and 74b are different sizes. In particular, the pin 74b has a smaller diameter than the pin 74a, in order to create a tighter-radius corner in the first reinforcing element 33 at this location. A tighter-radius corner is desirable at this location in order to enable the first reinforcing element 33 to align more closely with the load path between the opening 31 and the right-hand-most fasteners of the component 30.

[0063] Returning to Figure 6, in block 603 the load-transferring structure is formed by arranging a matrix material on the reinforcing member such that. the matrix material at least. partially surrounds the reinforcing member, and defines the opening and forms the other part of the structure. The matrix material may have any of the features of the example matrix materials described above. In examples in which the structure is formed by casting, arranging the matrix material on the reinforcing member comprises proving the matrix material in a fluid state, flowing the matrix material into a mould containing the reinforcing member, and then solidifying the matrix material. The fluid matrix material flows around the reinforcing member during this process, such that the reinforcing member is partially or completely embedded in the matrix material when it has solidified.

[0064] In other examples, an additive manufacturing process may be used to arrange the matrix material on the reinforcing member. In such examples a mould is not required. Instead the matrix material is built up layerwise around and on the reinforcing member, according to a predetermined design corresponding to the desired shape of the component. Any suitable additive manufacturing process known in the art could be used, depending on the type of the matrix material. An additive manufacturing process used to arrange the matrix material on the reinforcing member would he tailored such that the arrangement of the reinforcing member is not disturbed (either physically or chemically) during deposition of the matrix material. Various alternative techniques could also be used to arrange the matrix material on the reinforcing member, including (hut not limited to) electron beam deposition, laser deposition, and hot isostatic pressing (HIP).

[0065] The completion of block 603 results in a load-transferring structure having an opening and being configured to transfer load from the opening to another part of the structure. The resulting structure comprises a longitudinal reinforcing member that forms a loop enclosing the opening, wherein the loop has a section extending between the location of the opening and the location of the other part of the structure. The section is aligned with a direction along which load is intended to be transferred during operation of the structure. The main body of the structure is formed from a matrix material which at least partially surrounds the reinforcing member. The matrix material defines the opening and forms the other part of the structure to which load is transferred during operation of the structure. The resulting load-transferring structure may be a component according to the invention, or apart of a component according to the invention.

[0066] Although the invention has been described above with reference to one or more preferred examples or embodiments, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.

[0067] Where the term -or" has been used in the preceding description, this term should be understood to mean "and/or", except where explicitly stated otherwise.

Claims

CLAIMS: 1. A load-transferring component, wherein the component has an opening and is configured to, during operation of the component, transfer load from the opening to a predetermined separate location on the component via a load path, the component comprising: a matrix material; and at least one longitudinal reinforcing element embedded in the matrix material; wherein the reinforcing element is arranged in a loop around the opening, the loop comprising a section that is aligned with the load path between the opening and the predetermined separate location.
2. A component according to claim 1, wherein the section is substantially straight.
3. A component according to claim 1 or claim 2_ wherein the opening is configured to receive a pin or spigot comprised in a further component.
4. A component according to any preceding claim, wherein the rein forcing element is arranged in a plurality of loops around the opening, and each loop comprises a section that is aligned with the load path between the opening and the predetermined separate location.
5. A component according to any preceding claim, wherein the predetermined separate location is a location of a mechanism for transferring load from the component to a further component.
6. A component according to claim 5, wherein the mechanism comprises a fastener connecting the component to the further component.
7. A component according to any preceding claim, comprising a further longitudinal reinforcing element embedded in the matrix material, wherein the further reinforcing element is arranged in a loop around the opening, and wherein the shape of the loop matches the circumferential shape of the opening.
8. A component according to claim 7, wherein the further reinforcing element is integrally formed with the reinforcing element.
9. A component according to claim 7 or claim 8, wherein the further reinforcing element forms at least part of a circumferential surface of the opening.
10. A component according to any preceding claim, wherein the reinforcing element is under tension.
11. A component according to any preceding claim, Further comprising one or more pins embedded in the matrix material, wherein the one or more pins are within the loop of the reinforcing clement and are in contact with the reinforcing clement.
12. A component according to any preceding claim, wherein the matrix material is aluminium.
13. A component. according to any preceding claim, wherein the reinforcing element. comprises one of: an aluminium oxide fibre; a carbon fibre; a silicon carbide fibre.
14. A component according to any preceding claim, wherein the component is an aircraft component.
15. A component according to claim 14, wherein the component is a gear rib.
16. An assembly comprising a component. according to any of claims 1 to 15, connected to a further component, wherein the component is configured to transfer load to the further component and wherein the predetermined separate location is located at a join between the component and the further component.
17. An assembly according to claim 16, wherein the component is connected to the further component by a fastener and the predetermined separate location is the location of the fastener.
18. An assembly according to claim 17, wherein the component is formed integrally with the further component.
19. An assembly according to any of claims 16 to 18, further comprising a second further component engaged with the opening such that the second further component exerts a force on the component in a radial direction of the opening during operation of the assembly, wherein the component is configured to transfer load from the second further component to the further component.
20. An aircraft. comprising the component. according to any of claims 1 to 15 or the assembly according to any of claims 16 to 19.
21. A method of manufacturing a load-transferring structure having an opening and being configured to transfer load from the opening to another part of the structure, the method comprising: arranging a longitudinal reinforcing member such that it forms a loop enclosing the intended location of the opening, wherein the loop has a section extending between the intended location of the opening and the intended location of the other part of the structure, the section being aligned with a direction along which load is intended to be transferred during operation of the structure; and forming the structure by arranging a matrix material on the reinforcing member such that the matrix material at least partially surrounds the reinforcing member, and defines the opening and forms the other part of the structure.
22. A method according to claim 21, further comprising arranging a further longitudinal reinforcing member around the intended location of the opening, such that the further reinforcing member will lie adjacent the circumferential surface of the opening in the completed structure.