RELATING TO WING CONSTRUCTION

Abstract

An aircraft wing structure (100) including a spar (101) and a systems module (200) that is releasably secured to brackets (300) on a first side of the spar (101) and the second, opposite side of the spar is configured to define a wall of a fuel tank of an aircraft wing.

Claims

1. An aircraft wing structure comprising: a spar, a systems module, and brackets mounted upon the spar, wherein the systems module is releasably secured to each of the brackets on a first side of the spar, wherein a second side of the spar, opposite the first side, is configured to define a wall of a fuel tank of an aircraft wing, wherein the systems module comprises a raceway module comprising a plate carrying a plurality of electrical cables, and wherein the plate is releasably secured to one or more of the brackets.

2. The aircraft wing structure of claim 1, wherein one or more of the brackets is fastened to the spar by a fastener configured such that, when the aircraft wing structure forms part of the aircraft wing, an end of the fastener is situated within the fuel tank of the aircraft wing.

3. The aircraft wing structure of claim 1, wherein at least one of the brackets is adhesively bonded to the spar.

4. The aircraft wing structure of claim 1, wherein at least one of the brackets comprises a main body and an intermediate member, and wherein the systems module is releasably secured to the intermediate member and the intermediate member is releasably secured to the main body.

5. The aircraft wing structure of claim 1, wherein the systems module is releasably secured to at least one of brackets by a fastener comprising a barrel nut, and wherein the barrel nut is configured to engage with a part of the bracket to prevent rotation of the barrel nut when rotating a bolt within the barrel nut to tighten or untighten the fastener.

6. An aircraft wing comprising the aircraft wing structure according to claim 1, wherein the spar of the aircraft wing structure defines the wall of a fuel tank of the aircraft wing.

7. An aircraft comprising the aircraft wing according to claim 6.

8. A kit of parts suitable for forming an aircraft wing structure, the kit comprising: a spar, a systems module comprising a plate carrying electrical cables, and brackets mounted to the spar, wherein the systems module is configured to be releasably secured to each of the brackets on a first side of the spar, wherein the plate of the systems module is configured to be releasably secured to at least one of the brackets, and wherein a second side of the spar is opposite to the first side of the spar and defines a wall of a fuel tank of an aircraft wing.

9. A method of removing a systems module from an aircraft wing structure, the systems module comprising a plate supporting electrical cables, wherein the aircraft wing structure comprises brackets mounted to a spar of the aircraft wing structure, the brackets are positioned on a first side of the spar and a second side of the spar, opposite to the first side, defines a wall of a fuel tank of an aircraft wing, wherein the systems module is releasably secured to each of the bracket brackets and the plate of the systems module is releasably secured to at least one of the brackets, and wherein the method comprises: releasing the systems module from each of the brackets, and moving the systems module away from the aircraft wing structure.

10. A method of installing a systems module upon a spar of an aircraft wing structure, the systems module comprising a plate carrying an electrical cables, wherein the aircraft wing structure comprises brackets mounted to the spar and the brackets are positioned on a first side of the spar and a second side of the spar, opposite to the first side, defines a wall of a fuel tank of an aircraft wing, wherein the method comprises: releasably securing the systems module to each of the brackets, and releasably securing the plate of the systems module to at least one of the brackets.

Description

DESCRIPTION OF THE DRAWINGS

[0024] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which:

[0025] FIG. 1 is a schematic drawing an aircraft wing structure according to a first embodiment of the invention comprising a systems module removably mounted to a wing spar;

[0026] FIG. 2 shows an aircraft having a wing comprising the aircraft wing structure shown in FIG. 1;

[0027] FIG. 3 is a schematic drawing of a bracket of the aircraft wing structure of FIG. 1;

[0028] FIG. 4 is a schematic cross-sectional view of the bracket shown in FIG. 3;

[0029] FIG. 5 is a schematic drawing of a bracket configured for removably mounting a systems module to a spar in an aircraft wing structure according to a second embodiment of the invention, the bracket is shown with its mounting block removed from its base plate; and

[0030] FIG. 6 is another schematic drawing of the bracket of FIG. 5, the bracket is shown with the mounting block in a position ready to be secured to its base plate.

DETAILED DESCRIPTION

[0031] An aircraft wing structure 100 according to a first embodiment of the invention are shown in FIG. 1. The aircraft wing structure 100 is configured to form part of a wing 501 of the aircraft 500 shown in FIG. 2, and comprises a rear spar 101 and a systems module 200. The rear spar is configured to form part of the wing box of the aircraft wing 501. Other embodiments of the invention may alternatively or additionally comprise a front spar. In some embodiments of the invention the aircraft wing structure may form part of the aircraft wing, while in other embodiments the aircraft wing structure may not yet form part of the construction of a completed aircraft wing.

[0032] The systems module 200 comprises various electronic systems and associated cable raceways which have been integrated into a single module 200 that can be constructed separately from the spar 101, and which is configured to be installed in a relatively simple installation process, as will be described in more detail below. While the systems module 200 comprises electronic systems, in other embodiments the systems module may alternatively or additionally comprise hydraulic systems or bleed air. In some embodiments the systems module may include line replacement items, which must be replaced at key service intervals.

[0033] The systems module 200 is releasably secured to the spar 101 via a plurality of brackets 300 which are spaced apart along the spar 101 in a span-wise direction, as shown in FIG. 1. One of the brackets 300 is shown in isolation in FIG. 3. The bracket 300 is formed by a body having a generally U-shaped cross-section formed by two extending arms 301 connected by a base 303 which extends between the arms 301, as can be best seen in the cross-sectional view of FIG. 4. The bracket 300 is bolted to a first side 103 of the spar 101 by fasteners 107 which extend through the base 303 of the bracket 300 and through the spar 101. As can also been seen in FIG. 4, the second, opposite side 105 of the spar 101 forms a wall of a fuel tank 109 of the aircraft wing structure 100 such that the fasteners 107 penetrate the fuel tank 109.

[0034] In the presently described embodiment of the invention, the systems module 200 is secured to the each of the brackets 300 via a raceway plate 201 comprising a plate portion 203 that carries a plurality of electrical cables 205. The plate portion 203 is formed with a plurality of holes so that the plate portion 203 can be bolted to the bracket 300 using fasteners 207. As can be seen in FIG. 4, the raceway plate 201 is placed onto the distal ends of the arms 301 of the bracket 300 so that the raceway plate is oriented substantially parallel with the base 303. The bolts 211 of the fasteners pass through the holes in the raceway plates and into corresponding holes formed in the distal ends of the arms of the bracket 301. Each of the bolts 211 engage with a barrel nut 209 which is situated within an opening 305 formed in a side of the bracket 300. The size of each of the openings 305 is such that barrel nuts 209 cannot rotate within the openings 305 when the bolt 211 of the fastener 207 is screwed into or out of the barrel nut 209. Accordingly, when fastening and unfastening each of the fasteners 207, there is no need to access the barrel nut 209 with a tool. The use of fasteners 207 comprising barrel nuts 209 is therefore advantageous because it simplifies fastening and unfastening of the fasteners 207, and removes the design constraint of being needing to be able to access the nut of the fastener with a tool.

[0035] In other embodiments of the invention, fasteners comprising conventional nuts, or other methods of releasably securing the systems module to the aircraft structure may of course be used. Additionally, other embodiments of the invention may use alternative mountable members of the systems module instead of raceway plates. For example, a mountable member of the systems module may be configured to clip into the bracket, or vice versa, or the systems module may be retained in position upon the bracket by pins or a clasp arrangement.

[0036] The embodiment of the invention described above facilitates modular wing construction, whereby the spar 101 and the systems module 200 can be constructed in parallel, following which the systems module 200 can be installed upon the brackets 300 in a relatively quick and straightforward manner. This potentially enables a reduction in the time taken to manufacture a wing when compared to prior art methods where the spar is constructed and then each of the electronic systems are separately installed upon the wing structure. Additionally, because the systems module 200 is releasably secured to the bracket 300, when it becomes necessary to remove the systems module 200 from the aircraft wing, for example during servicing or for replacement, there is no need to break the seal of the fuel tank because there is no need to remove the spar fasteners. The bracket 300 can effectively be left permanently mounted to the spar 101.

[0037] In an aircraft wing structure according to a second embodiment of the invention the brackets 300′ are adhesively bonded to the spar 101′, as shown in FIG. 5 and FIG. 6. Adhesively bonding the brackets 300′ to the spar 101′, as opposed to mechanically fastening the brackets using fasteners, provides an advantage of avoiding having to provide holes in the spar 101′.

[0038] The brackets 300′ comprise a base portion 302′ comprising a base plate 303′ which is co-bonded to the spar 101′, and two parallel arms 301′ which are spaced apart and extend perpendicularly from the base plate 303′, away from the spar 101′. The brackets 300′ further comprise a generally cuboidal mounting block 307′ which is removably mounted between the arms 301′ of the base portion via fasteners 309′ which pass through each of the arms 301′ and through the mounting block 307′.

[0039] The systems module 200′ of the second embodiment of the invention is releasably secured to the each of the mounting blocks 307′ via a plate 201′ of the systems module 200′. The plate 201′ is formed with a plurality of holes so that the plate 201′ can be bolted to the bracket 300′ using fasteners 207′. As can be seen in FIG. 6, the plate 201′ is placed onto the mounting block 307′ of the bracket 300′ and is removably mounted to the mounting block 307′ using fasteners 207′. The bolts 211′ of the fasteners 207′ pass through the holes in the plate 201′ and into corresponding holes formed in the mounting block 307′. Each of the bolts 211′ engage with a barrel nut 209′ which is situated within an opening 305′ formed in a side of the mounting block 307′. The size of each of the openings 305′ is such that barrel nuts 209′ cannot rotate within the openings 305′ when the bolt 211′ of the fastener 207′ is screwed into or out of the barrel nut 209′. Accordingly, when fastening and unfastening each of the fasteners 207′, there is no need to access the barrel nut 209′ with a tool. In other embodiments of the invention other methods of releasably secured the systems module to the aircraft structure may of course be used. For example, a mountable member of the systems module may be configured to clip into the mounting block, or vice versa, or the systems module may be retained in position upon the mounting block by pins or a clasp arrangement.

[0040] The bracket 300′ arrangement of the second embodiment of the invention therefore provides an advantageous way of mounting a systems module to the spar 101′ of the aircraft wing where is it undesirable to use fasteners. For example, the use of the bracket 300′ can avoid the use of fasteners which penetrate a fuel tank. The base portion 302′ of the bracket 300′ can be left permanently mounted to the spar 101 because the systems module 200′ is releasably secured to the base portion 302′ via the mounting block 307′, which serves as an intermediate member between the systems module 200′ and the base portion 302′. The systems module 200′ can be removed from the aircraft wing by either unfastening the plate 201′ from the mounting block 307′ or by unfastening the mounting block 307′ from the base portion 302′. However, because the base portion 302′ of the bracket 300′ is bonded to the spar, and therefore not easily removable, it may be preferable to reduce wear and tear of the base portion 302 and leave the mounting block 307′ semi-permanently mounted to the base portion 302′. The mounting block 307′ can then be replaced in the event that it becomes damaged or overly worn from repeated fastening and unfastening of the systems module 200′ from the mounting block 307′.

[0041] Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein. For example, it should be understood that an aspect of the invention is that it provides, in its broadest sense, a wing structure wherein a systems module is removably mounted to a spar via plurality of brackets. This aspect of the invention is not itself limited to the types of bracket described above in relation to the first and second embodiments of the invention. The skilled person will be aware of other types of bracket which are suitable for use in removably mounting a systems module. Additionally, it should be noted that a bracket of the type described with respect to the first embodiment of the invention could be bonded to the spar and that a bracket of the type described with respect to the second embodiment of the invention could be mechanically fastened to the spar.

[0042] Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. The word “or” means and/or unless clearly indicated otherwise. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.