GB2588967A

GB2588967A - Aircraft structure having a composite laminate body and edge cap device

Info

Publication number: GB2588967A
Application number: GB1916738.6A
Authority: GB
Inventors: bloom Dominic; Seegel Hauke; Tarr Richard
Original assignee: Airbus Operations GmbH; Airbus Operations Ltd
Current assignee: Airbus Operations GmbH; Airbus Operations Ltd
Priority date: 2019-11-18
Filing date: 2019-11-18
Publication date: 2021-05-19
Also published as: GB201916738D0

Abstract

An aircraft structure 30, such as a stringer, rib, spar or rib attachment, comprises a composite laminate body 31 having an edge and an edge cap device 40 covering the edge wherein cured resin forming part of the body bonds the edge cap on the edge. A method of manufacturing an aircraft structure comprises providing a dry fibre preform of a structural component, covering an edge of the preform with an edge cap device, feeding or injecting uncured resin between the edge cap device and the edge of the preform to infuse the dry fibre preform and curing the resin. An edge cap device comprises a cap body arranged to cover the edge of a composite laminate body and a resin feed path (45, fig 5) configured to feed resin to the edge of the laminate body. A combination of a dry fibre preform for a composite component and an edge cap device is provided and a mould tool (63, 64 fig 8) comprising a mould chamber configured to receive and locate a dry fibre preform and an edge cap. The edge cap device acts to protect the edge of the laminate and is integrally formed with the body.

Description

AIRCRAFT STRUCTURE HAVING A COMPOSITE LAMINATE BODY AND EDGE CAP DEVICE

FIELD OF THE INVENTION

[0001] The present invention relates to an aircraft structure comprising a composite laminate body with an edge and an edge cap device covering the edge. The present invention also relates to an edge cap device for covering an edge of a composite laminate body; a combination of a dry fibre preform for a composite laminate component having an edge and an edge cap device arranged to cover the edge; a mould tool for use in manufacturing an aircraft structure; an uncured resin feed system comprising a mould tool and an edge cap device; an aircraft; and a method of manufacturing an aircraft structure for an aircraft.

BACKGROUND OF THE INVENTION

[0002] Many aircraft components are formed from composite laminate materials. Such aircraft components include stringers in an aircraft wing, stiffeners, spars, ribs, and covers. These components may be in the form of composite laminate structures. Such composite laminate structures are typically formed from a stack of plies infused or injected with a thermosetting epoxy resin material which is cured to form the component.

[0003] During manufacture of the structural components it is typically necessary to machine the edges of the component to eliminate an irregular edge and to remove flash. Such a machining process is a bottleneck in the manufacture of such composite aircraft structures as it is time consuming and requires further inspection steps. A layer of sealing material may then be applied to the edge.

[0004] Although composite laminate structures may be strong when loaded in the way in which they have been designed to be loaded, they may be vulnerable to impact damage. Particularly vulnerable are the edges of composite laminate structures at which the layers of composite laminate structure terminate. Impact at the component edge may be capable of damaging the bonding between the layers of the laminate. A further way in which the composite laminate structure may be damaged is as a result of wear over time.

[0005] When designing an aircraft, factors that affect the strength and other mechanical properties of composite laminate structures of the aircraft, such as those factors described above, are taken into account. As such, these factors typically mean that the composite laminate structures are provided with extra strength resulting in an increase in size and weight.

[0006] A known approach to strengthen an edge of a composite laminate structure is to apply an edge protector, for example as described in US2011/0220006 Al Such an edge protector is applied to a machined edge of the laminate composite to provide protection to the edge.

SUMMARY OF THE INVENTION

[0007] According to an aspect of the invention, there is provided an aircraft structure comprising: a composite laminate body having an edge; and an edge cap device covering the edge; wherein cured resin forming part of the composite laminate body mounts the edge cap device on the edge.

[0008] The provision of an edge cap device aids production rate of a composite laminate body. With such an arrangement, the cap provides a clearly defined and contained edge. A need to machine the edge of the aircraft structure during a manufacturing process is minimised or removed. Edge protection is provided.

[0009] During manufacture, an uncured resin may be fed, that is infused or injected, in a dry fibre arrangement and subsequently cured to form the composite laminate body.

[0010] The composite laminate body may comprise a ply stack integrated with the cured resin. The cured resin may protrude from the ply stack. In another arrangement, the composite laminate body may include a random array of fibres distributed with cured resin.

[0011] The cured resin acts to retain the edge cap device on the edge and so provide a one-piece component.

[OW 2] The cured resin may extend in the edge cap device [0013] The edge cap device may comprise a cured resin channel containing a part of the cured resin.

[0014] The edge cap device may comprise an edge retaining channel and the cured resin channel may extend along the edge cap device.

[0015] The composite laminate body and the edge cap device together form an integrally formed component. That is, the composite laminate body and the edge cap device are assembled together in a permanent assembly prior to curing of the composite laminate body.

[0016] The aircraft structure may comprise at least one of a stringer, a T-shaped stringer, a rib, a spar, a panel, and a rib attachment [0017] According to an aspect of the invention, there is provided an edge cap device for covering an edge of a composite laminate body, the edge cap device comprising a cap body arranged to cover the edge of the composite laminate body, and a resin feed path in the cap body configured to feed resin to the edge of the composite laminate body.

[0018] With such an arrangement, the provision of an edge cap device aids production rate of a composite laminate body. Provision of an edge cap device through which a resin is supplied leads to the removal of a machining step to remove flash and misaligned ply edges at the edge of the composite laminate body.

[0019] With this arrangement, the edge cap device is able to protect the edge of the composite laminate body. The edge cap device may be integrally formed with the composite laminate body. Resin fed to the edge and between plies of the composite laminate body is fed through the cap. As such, the resin communicates between the edge cap device and the composite laminate body.

[0020] The edge cap device may encapsulate ply edges at the edge of the composite laminate body. As such the presence of open fibres and protruding fibres is prevented.

[0021] The resin feed path may comprise a resin distribution channel configured to face the edge of the composite laminate body.

[0022] The resin feed path may comprise a plurality of resin distribution channels.

[0023] By providing one or more resin distribution channels in the edge cap device, the need to provide resin distribution channels in a mould tool is minimised or reduced. This provides for resin feed lines to no longer require demoulding.

[0024] The resin may therefore be significantly evenly distributed along the edge of the composite laminate body.

[0025] The resin feed path may comprise a resin injection inlet fluidly communicating with the resin distribution channel.

[0026] The cap body may comprise an edge retaining channel configured to retain the edge of the composite laminate body.

[0027] As such, the cap body may enclose the edge to improve protection of the edge.

[0028] The edge retaining channel may have a channel base. The channel base may act as an edge receiving face. The channel base may form a shoulder.

[0029] The resin feed channel may be in the channel base.

[0030] The resin distribution channel may extend in the cap body. A plurality of resin feed outlets may be configured to allow the flow of resin from the resin distribution channel.

[0031] The cap body may be elongate and the resin feed path may extend in an elongate direction of the cap body.

[0032] The resin feed path may comprise an air outlet. As such, air may be allowed to escape from the resin feed path.

[0033] The cap body may be formed from a thermoplastic. The cap body may be an elastomeric or polymeric polymer.

[0034] According to an aspect of the present invention, there is provided a combination of a dry fibre preform for a composite laminate component having an edge and an edge cap device arranged to cover the edge; wherein the edge cap comprises a resin feed path configured to feed resin to the edge during resin supply of the dry fibre preform.

[0035] With such an arrangement, the cap may be fitted during manufacture of the composite laminate component, and prior to feeding and curing of resin to form the composite laminate component.

[0036] According to an aspect of the invention there is provided a mould tool for use in forming an aircraft structure, the mould tool comprising: a mould chamber configured to receive and locate a dry fibre preform with an edge and an edge cap covering the edge of the dry fibre preform.

[0037] As such, the mould tool is able to receive the edge cap, and the edge cap and component formed by the dry fibre preform may be integrally formed.

[0038] The mould tool may comprise an uncured resin supply configured to supply uncured resin to the edge cap device. By providing the resin to the edge cap device, complex feed lines and exhaust paths are not required in the mould tool and so the mould tool may be simplified.

[0039] According to an aspect of the present invention, there is provided an uncured resin feed system comprising the mould tool as described above and an edge cap device configured to cover the edge and comprising a resin feed path configured to feed uncured resin to the edge of the dry fibre preform.

[0040] The resin feed system may comprise a resin supply mechanism. The resin supply mechanism may be a resin infusion mechanism. The resin supply mechanism may be a resin injection mechanism.

[0041] According to an aspect of the present invention, there is provided an aircraft comprising at least one of the edge cap device as described above, the aircraft structure as described above, and an aircraft structure formed by the combination as described above.

[0042] According to an aspect of the present invention, there is provided a method of manufacturing an aircraft structure for an aircraft comprising: providing a dry fibre preform of a structural component; covering an edge of the dry fibre preform with an edge cap device; distributing uncured resin between the edge cap device and the edge of the dry fibre preform to feed the uncured resin in the dry fibre preform; and curing the resin.

[0043] The method may comprise feeding uncured resin through the edge cap device to between the edge cap device and the edge of the dry fibre preform.

[0044] The method may comprise, following curing, together removing the structural component and the edge cap device from a mould tool.

[0045] The curing the resin may form a one piece component of the structural component and the edge cap device.

BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Embodiments of the invention will now be described with reference to the accompanying drawings, in which: [0047] Figure 1 is a perspective view of an aircraft; [0048] Figure 2 is a schematic plan view of a wing of the aircraft; [0049] Figure 3 is a schematic cross-sectional end view of a stringer with a composite laminate body and an edge cap device; [0050] Figure 4 is a schematic perspective view of the stringer including the structural component and the edge cap device; [0051] Figure 5 is a schematic close-up cross-sectional view of a distal end of the stringer; [0052] Figure 6 is a schematic exploded view of a dry fibre preform of the composite laminate body and the edge cap device; [0053] Figure 7 is a schematic perspective view of a mould tool receiving the dry fibre preform of the composite laminate body and the edge cap device; [0054] Figure 8 is a schematic cross-sectional end view of the mould tool with the dry fibre preform of the composite laminate body and the edge cap device received therein; [0055] Figure 9 is a schematic cross-sectional side view of the mould tool receiving the dry fibre preform and the edge cap device showing the flow of resin in the mould tool to feed the dry fibre preform to form the stringer; [0056] Figure 10 is a schematic cross-sectional end view of an alternative stringer with a different edge cap device; and [0057] Figure 11 is a schematic close-up cross-sectional end view of a distal end of an alternative stringer with a further different edge cap device.

DETAILED DESCRIPTION OF EMBODLMENT(S)

[0058] Figure 1 shows an aircraft 10. The aircraft 10 has a fuselage 11, and starboard and port fixed wings 12. An engine 13 is mounted to each wing 12. The aircraft 10 is a typical jet passenger transport aircraft but the invention is applicable to a wide variety of fixed wing aircraft types, including commercial, military, passenger, cargo, jet, propeller, general aviation, etc. with any number of engines attached to the wings or fuselage. The invention is also applicable to other aircraft, such as helicopters. The aircraft also comprises starboard and port horizontal stabilisers 14 and a vertical stabiliser 15.

[0059] A schematic view of a wing box 20 of the starboard wing 12 is shown in Figure 2. The port wing is similar in construction and so only a description of the starboard wing is provided herein. The wing 12 has a cantilevered structure with a length extending in a span-wise direction from a wing root 16 to a wing tip 17, with the root 16 being joined to the aircraft fuselage 11. The wing 12 has a leading edge 18 and a trailing edge 19 as shown in Figure 1. The leading edge 18 is at the forward end of the wing 12 and the trailing edge 19 is at the rearward end of the wing 12. The wing 12 comprises the wing box 20 and leading and trailing edge assemblies.

[0060] The wing 12 has a spanwise axis which extends in a direction from the wing root 16 to the wing tip 17, and a chordwise axis which extends in the direction from the leading edge 18 to the trailing edge 19.

[0061] The wing box 20 forms a structural assembly. The wing box 20 including forward and rearward spars 21, 22 extending in a spanwise direction; ribs 23 extending between the forward and rear spars 21, 22 in a chordwise direction; upper and lower covers 24 on the upper and lower sides of the wing box 20; and stringers 30. Further components form the wing box 20. The stringers 25 extend in a spanwise direction. The stringers 30 are mounted to the covers 24.

[0062] The stringer 30 acts as an aircraft structure. Although a description is provided herein with reference to the stringer 30, it will be understood that the invention is applicable to other aircraft structures.

[0063] Referring now to Figures 3 to 5, the stringer 30 comprises a composite laminate body 31 and an edge cap device 40. The composite laminate body 31 comprises a laminate structure formed from a stack of sheets, commonly known as plies 32. Each sheet comprises a plurality of unidirectional carbon fibres. A curable resin 33 is fed, for example by infusion and/or injection, into the stack of sheets, also known as a ply stack 34, to form the composite laminate body 31 when the resin 33 is cured. The resin 33 is a thermosetting epoxy-resin, although the type of resin may differ. The component formed by the ply stack 34 prior to supply with the resin 33 is conventionally known as a dry fibre preform 50. The dry fibre preform 50 is shown in Figures 6 to 8. Individual plies are shown schematically in Figure 5 but are not shown in the other figures for purposes of clarity. The dry fibre preform 50 is also known as a charge. The stringer 30 is a fibre reinforced composite laminate component with a thermoplastic cap, although the use of alternative materials is envisaged.

[0064] The composite laminate body 31 and the edge cap device 40 together form a structural component. The composite laminate body 31 and the edge cap device 40 are formed together as a one piece component. As such, the composite laminate body 31 and the edge cap device 40 are integrally formed. The edge cap device 40 is mounted on the composite laminate body 31 during formation of the composite laminate body 31. The composite laminate body 31 comprises the ply stack 34 and integrated cured resin 33. The composite laminate body 31 in embodiments may be formed from a single dry fibre preform 50 or from a plurality of dry fibre preforms. As such, the edge cap device 40 may extend over a plurality of dry fibre preforms.

[0065] The composite laminate body 31 comprises a web 35 and a pair of feet 36. The web 35 upstands from the feet 36. The feet 36 are flanges extending from the web 35. The web 35 and feet 36 of the composite laminate body 31 form the stringer web and stringer feet. Such an arrangement forms a T-shaped stringer configuration. It will be appreciated that alternative configurations are possible, for example the composite stringer 30 may be L-shaped. The web 35 has a distal end 37. The stringer 30 is elongate and extends in an axial direction. The distal end 37 extends in an axial direction of the stringer 30. The composite laminate body 31 has an edge 38. The edge 38 is formed at the distal end 37 of the web 35. In other embodiments, the edge 38 is formed at an alternative edge of the ply stack 34. The edge 38 is formed by the plurality of ply edges 39 of the ply stack 34. The ply edges 39 are substantially aligned, although there may be some misalignment of the edges of the plies 32. As such, the edge 38 is not completely uniform. The resin 33 is fed into the ply stack 34 from the distal end 37.

[0066] The edge cap device 40 caps the edge 38. The edge cap device 40 covers the ply edges 39. As such, the edge cap device 40 forms an edge of the stringer 30. The edge cap device 40 extends in the axial direction on the composite laminate body 31. The edge cap device 40 is formed from a thermoplastic. Alternative materials may be used. The edge cap device 40 may be formed for example, by an additive layer manufacturing process, an injection moulding process, or a continuous profile extrusion process.

[0067] The edge cap device 40 comprises a cap body 41. The cap body 41 is an elongate member. The cap body 41 is configured to cover the edge 38 of the composite laminate body 31. The cap body 41 includes an edge retaining channel 42. The edge retaining channel 42 extends over the edge 38. The edge 38 is received in the edge retaining channel 42. The cap body 41 has opposing body flanges 43. The body flanges 43 define the edge retaining channel 42. The edge retaining channel 42 has a channel base 44. When the edge 38 is received in the edge retaining channel 42 part of the edge 38 abuts against the edge retaining channel 42 to locate the edge cap device 40 on the edge 38. The edge cap device 40 encloses the ply edges 39.

[0068] The edge cap device 40 includes a resin feed path 45. The resin feed path 45 is in the cap body 41. Resin 33 is received in the resin feed path 45. Curable resin is fed along the resin feed path 45 to feed curable resin to the edge 38. As such, curable resin may be fed in the ply stack 34 at the edge 38. Cured resin 33 is retained in the edge cap device 40. Cured resin 33 extends between the edge cap device 40 and the composite laminate body 31. The cured resin 33 mounts the edge cap device 40 on the edge 38 of the composite laminate body 31. Cured resin 33 protruding from the edge 38 is retained in the edge cap device 40. The cured resin exposed at the edge 38 forms a cured resin protrusion 46.

[0069] The cured resin protrusion 46 upstands from the edge 38. The protrusion 46 is elongate and extends in the axial direction along the edge 38. The protrusion 46 extends in the resin feed path 45. As such, the resin feed path 45 acts as a resin filled channel. The resin feed path 45 comprises a resin distribution channel 47 and a resin injection inlet 48. The resin distribution channel 47 is provided to distribute uncured resin 33 along the edge 38. Upon curing, resin in the resin distribution channel 47 is retained to act as an edge cap device mounting feature. As such, cured resin 33 connects the edge cap device 40 with the composite laminate body 31.

[0070] The resin distribution channel 47 forms the resin filled channel of the edge cap device 40. In the Figures, a single resin distribution channel 47 is shown, however it will be understood that the resin feed path 45 may comprise a plurality of resin distribution channels. Two or more of the resin distribution channels 47 may extend in parallel and/or in series with each other. The resin injection inlet 48 fluidly communicates with the resin distribution channel 47. The resin injection inlet 48 provides a path for injecting resin into the resin distribution channel 47 and therefore along the edge 38 of the composite laminate body 31. The resin injection inlet 48 communicates with a resin injection arrangement (not shown).

[0071] The resin distribution channel 47 is formed in the channel base 44. As such, the channel base 44 acts as a shoulder for locating the edge 38. Air outlets 49 communicate the resin distribution channel 47 with external of the edge cap device 40 to allow the outflow of air in the channel 47 through the air outlet 49 as resin is injected into the resin feed path 45. The air outlets 49 are exposed at the peripheral end of the resin distribution channel 47. It will be understood that the edge cap device 40 accommodates misaligned ply edges 39.

[0072] With reference in particular to Figures 6 to 9, a method of manufacturing the stringer 30 will now be described. The dry fibre preform 50 for forming a composite laminate component is arranged with the edge cap device 40. The dry fibre preform 50 and the edge cap device 40 are arranged in a mould tool 60. The mould tool 60 has a mould chamber 61. The mould chamber 61 is configured to receive the dry fibre preform 50 and the edge cap device 40. The mould chamber 61 is configured to enclose the dry fibre preform 50 and edge cap device 40. The edge cap device 40 is received over the edge 38 of the dry fibre preform 50.

[0073] The mould tool 60 and the edge cap device 40 form part of an resin feed system 62 which is configured to feed a curable resin in the dry fibre preform 50 which is then cured to form the stringer 30. The mould tool 60 includes a first mould part 63 and a second mould part 64. The first and second mould parts 63, 64 are separable to provide access to the mould chamber 61. When the mould parts 63, 64 are brought together, the dry fibre preform 50 and the edge cap device 40 may be retained there between. The uncured resin feed system 62 further includes an uncured resin supply 65. The uncured resin supply 65 feeds a curable resin into the resin feed path 45 provided in the edge cap device 40. As such, the feed path of the curable resin 33 is provided in the edge cap device 40. Such an arrangement removes or minimises the need for resin feed channels to be provided in the mould tool 60 itself [0074] The edge cap device 40 is provided on the end of the dry fibre preform 50 prior to injection of resin into the dry fibre preform. As shown in Figure 9, the uncured resin feed system is assembled with the dry fibre preform 50 and the end cap device 40 received in the mould chamber 61. Resin is then injected by the uncured resin supply 65 through the resin injection inlet 48 to the dry fibre preform 50. The dry fibre preform 50 is fed with resin by resin flowing through the edge cap device 40 along the resin distribution channel 47 to be distributed along the edge 38 of the ply stack 34. Curable resin provided at the edge 38 is fed into the ply stack 34 by flowing from the resin distribution channel 47.

[0075] When the feeding process is completed, a curing process is undertaken. The curing process cures the resin 33 in the ply stack 34 and retained in the resin feed path 45 of the edge cap device 40. As such, the cured resin 33 acts to retain the edge cap device 40 on the edge 38 of the composite laminate body 31. The edge cap device 40 and the composite laminate body 31 are therefore formed as a one piece component with the cured resin 33 connecting the edge cap device 40 with the composite laminate body 31. The combined composite laminate body 31 and edge cap device 40, following cure, are demoulded from the mould tool 60 as a single component. The cured resin provides a strong interface between the edge cap device 40 and the composite laminate body 31. It will be understood that the cured resin at the edge 38 compensates for any misaligned edges of the plies 32.

[0076] Referring to Figure 10, an alternative edge cap device 70 is provided. The edge cap device 70 has a generally similar arrangement to the edge cap device 40 described above and so a detailed description will be omitted herein. However, the edge cap device 70 shown in Figure 10 has a barrier 71 between the resin distribution channel 47 and the edge 38 of the composite laminate body 31. Resin feed outlets 72 provide a fluid passage between the resin distribution channel 47 and the edge 38. In the present embodiment, the resin feed outlets comprise an array of holes distributed along the bather 71. The bather 71 may be a perforated panel. It will be understood that the arrangement of the barrier and resin feed outlets may vary. The bather '71 acts as a shoulder for the edge 38 of the composite laminate body 31. The provision of the barrier 71 aids the distribution of the uncured resin along the edge 38 of the dry fibre preform 50. In another embodiment as shown in Figure 11, the cap body 41 has chamfer faces 74 on the body flanges 43. The chamfer faces 74 act as locating faces for peripheral edges of the edge 38. It will be understood that alternative shoulder arrangements may be provided to locate the edge 38 with the cap body 41.

[0077] Where the word 'or' appears this is to be construed to mean 'and/or' such that items referred to are not necessarily mutually exclusive and may be used in any appropriate combination.

[0078] Although the invention has been described above with reference to one or more preferred 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.

Claims

CLAIMS1. An aircraft structure comprising: a composite laminate body having an edge; and an edge cap device covering the edge; wherein cured resin forming part of the composite laminate body mounts the edge cap device on the edge.
2. The aircraft structure of claim I, wherein the composite laminate body comprises a ply stack formed with the cured resin, and the cured resin protrudes from the ply stack.
3. The aircraft structure of claim I or claim 2, wherein the cured resin extends in the edge cap device.
4. The aircraft structure of any preceding claim, wherein the edge cap device comprises a cured resin channel containing a part of the cured resin.
5. The aircraft structure of claim 4, wherein the edge cap device comprises an edge retaining channel and the cured resin channel extends in the edge retaining channel.
6. The aircraft structure of any preceding claim, wherein the composite laminate body and the edge cap device together form an integrally formed component.
7. The aircraft structure of any preceding claim, wherein the aircraft structure comprises at least one of a stringer, a T-shaped stringer, a rib, a spar, and a rib attachment.
8. An edge cap device for covering an edge of a composite laminate body, the edge cap device comprising: a cap body arranged to cover the edge of the composite laminate body, and a resin feed path in the cap body configured to feed resin to the edge of the composite laminate body.
9. The edge cap device of claim 8, wherein the resin feed path comprises a resin distribution channel configured to face the edge of the composite laminate body.
10. The edge cap device of claim 9, wherein the resin feed path comprises a resin feed inlet fluidly communicating with the resin distribution channel.
11. The edge cap device of claim 9 or 10, wherein the cap body comprises an edge retaining channel configured to retain the edge of the composite laminate body.
12. The edge cap device of claim 11, wherein the edge retaining channel has a channel base and the resin distribution channel is in the channel base.
13. The edge cap device of any of claims 8 to 12, wherein the resin distribution channel extends in the cap body and a plurality of resin feed outlets are configured to allow a flow of resin from the resin distribution channel.
14. The edge cap device of any of claims 8 to 13, wherein the cap body is elongate and the resin feed path extends in an elongate direction of the cap body.
15. The edge cap device any of claims 8 to 14, wherein the resin feed path comprises an air outlet.
16. The edge cap device of any of claims 8 to 15, wherein the cap body is formed from a thermoplastic.
17. A combination of a dry fibre preform for a composite laminate component having an edge and an edge cap device arranged to cover the edge; wherein the edge cap device comprises a resin feed path configured to feed resin to the edge during resin feeding of the dry fibre preform.
18. A mould tool for use in manufacturing an aircraft structure, the mould tool comprising: a mould chamber configured to receive and locate a dry fibre preform with an edge and an edge cap covering the edge of the dry fibre preform.
19. The mould tool of claim 18, comprising a resin supply configured to supply uncured resin to the edge cap device.
20. An uncured resin feed system comprising the mould tool of claim 18 or 19 and an edge cap device configured to cover the edge and comprising a resin feed path configured to feed uncured resin to the edge of the dry fibre preform.
21. An aircraft comprising at least one of the aircraft structure of any of claims 1 to 7, the edge cap device of any of claims 8 to 16, and an aircraft structure formed by the combination of claim 17.
22. A method of manufacturing an aircraft structure for an aircraft comprising: providing a dry fibre preform of a structural component; covering an edge of the dry fibre preform with an edge cap device; distributing uncured resin between the edge cap device and the edge of the dry fibre preform to feed the uncured resin in the dry fibre preform; and curing the resin.
23. The method of claim 22, comprising feeding uncured resin through the edge cap device between the edge cap device and the edge of the dry fibre preform.
24. The method of claim 22 or 23, comprising following curing together removing the structural component and the edge cap device from a mould tool.
25. The method of any of claims 22 to 24, wherein curing the resin forms a one piece component of the structural component and the edge cap device.