GB2529473A

GB2529473A - Support device

Info

Publication number: GB2529473A
Application number: GB1414943.9A
Authority: GB
Inventors: Saravan Sundaravadanam
Original assignee: Airbus Operations Ltd
Current assignee: Airbus Operations Ltd
Priority date: 2014-08-22
Filing date: 2014-08-22
Publication date: 2016-02-24
Also published as: GB201414943D0

Abstract

The present disclosure relates to a support device 20 for supporting the foot 10 of an aircraft rib 18 especially during a manufacturing or maintenance procedure relating to an aircraft or aircraft component. The invention also concerns a method of using a support device during the manufacture or maintenance of an aircraft or aircraft component. The aircraft rib foot support comprises a rib webbing engagement-face 22and a rib foot engagement-face. The rib webbing engagement face and rib foot engagement face are spaced apart from each other. An aperture 26 is associated with the rib foot engagement face to allow drilling. The support 20 is located between and engaged with the rib foot 10 and the rib webbing 16 prior to a drilling operation on the rib foot 10. The support 20 adds rigidity to the rib foot 10 during drilling reducing the likelihood of the rib foot 10 deflecting causing misalignment of drilled holes.

Description

SUPPORT DEVICE

BACKGROUND OF THE INVENTION

100011 The present invention relates to a support device for supporting the foot of an aircraft rib. More particularly, but not exclusively, the present invention concerns a support device for supporting the foot of an aircraft rib during a manufacturing or maintenance procedure relating to an aircraft or aircraft component. The invention also concerns a method of using a support device during the manufacture or maintenance of an aircraft or aircraft component.

100021 Aircraft wings are typically made up of wing spars which run approximately along the length of the aircraft wing, and ribs that run approximately perpendicular to the spars, extending from the leading edge to the trailing edge of a wing. A wing skin encloses the internal structure of the wing, and is also secured to at least some of the internal structure with, for example, rivets. Tn order to enable the wing skin to be secured to a rib structure, the rib includes "feet", which comprise a tab extending in a plane approximately parallel with the wing skin. The wing skin may be riveted to the rib feet using standard riveting processes, As part of the riveting process, holes must be drilled thorough the wing skin and the rib feet, This is done with the skin positioned in the desired location and a hole being drilled through both the skin arid a wing foot at the same time.

10003] However, the rib foot and/or rib niay be flexible, leading to the pressure used during drilling the hole deforming the rib foot and/or rib. This may cause a misalignment of the holes in the wing skin and wing foot once the drilling is stopped and the load removed from the rib, Such a misalignment may cause a malfunction in the riveting process, and/or require remedial action to be taken in before the holes are

suitable for use.

100041 The present invention seeks to mitigate the above-mentioned problems.

SUMMARY OF THE TNVENTTON

100051 The present invention provides, according to a first aspect, an aircraft rib foot support comprising, a rib webbing engagement-face, a rib foot engagement-face, the rib webbing engagement-face arid rib foot engagement-face being spaced apart from each other, and an aperture associated with the rib foot engagement-face.

10006] As will be understood by a skilled person, an aircraft rib webbing is a section of the rib spaced opposite to and adjacent an aircraft rib foot and provides a surface against which the support may be braced during use of the support.

10007] The aircraft rib foot support may be used during the manufacture or maintenance of an aircraft or aircraft component to securely hold a rib foot in the correct position during drilling. As such, deflection of the rib foot during drilling, and hence the incidence of misalignment between the hole in an aircraft rib foot support and a wing skin or cover, may be reduced, 10008] The spacing between the rib webbing engagement-face and rib foot engagement-face may be adjustable. Providing an adjustable support may improve the usability of the support. The spacing between a rib webbing and an associated rib foot may vary across a rib, so an adjustable support may allow a single support to be used across a section or all of a rib, Fewer supports may therefore be required, and it may speed up the manufacturing or maintenance process which includes use of the support.

10009] The support may comprise a first section and a second section, wherein the first section is movable in relation to the second section. The first section may be movable in relation to the second section such that the spacing between the first section and second section is adjustable. The first section may be movable in relation to the second section such that the orientation of the first section in relation to the second section is adjustable, The support may comprise a crimped adjustable portion, The support may comprise a first threaded section and a second threaded section, such that screwing the first section and second section together allows the spacing to be adjustable.

100101 The support may comprise a first section and a second section, wherein the first section is a sleeve in which the second section is accommodated, such that the first section and second section overlap and may slide with respect to each other. The support may comprise a telescopic section. The support may comprise a biasing element, for example a spring, biasing the first section against and away from the second section. Such a support device may be compressed in length, located in position, and then the compression released. The support will then adjust to the optimum length as required.

100111 The support may comprise a plastics material. The plastics material may comprise nylon. The support may comprise other suitable materials, such as wood or metal.

100121 The aperture associated with the rib foot engagement-face allows a drill to pass through at least a section of the support without damage to the support. The aperture associated with the rib foot engagement-face may extend through the support to the rib webbing engagement-face. Such an arrangement may allow for a rib foot and wing skin to be drilled either from the direction of the wing skin to the rib foot, or from the rib foot to the wing skin, 100131 According to a second aspect, the invention provides a method of drilling a hole in an aircraft wing skin and aircraft wing rib foot, comprising the steps of: providing a support, the support as described in relation to the first aspect of the invention; locating the support between the aircraft wing rib foot and webbing of the aircraft wing rib; and drilling a hole in the aircraft wing skin and aircraft wing foot with the support in place, 100141 The support has been found to add rigidity to the aircraft wing rib and rib foot during the drilling process, thereby reducing or eliminating the possibility of misalignment of the holes after the drilling process is complete.

100151 The method may comprise using an adjustable support. The method may comprise the step of adjusting the support when locating the support between the aircraft wing rib foot and webbing of the aircraft wing rib. Providing an adjustable support may allow the support to be used across a number of wing rib configurations.

100161 Tt will of course be appreciated that features described in relation to one aspect of the present invention may be incorporated into other aspects of the present invention.

For example, the method of the invention may incorporate any of the features described with reference to the apparatus of the invention and vice versa.

DESCRIPTION OF THE DRAWINGS

10017] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which: 100181 Figure 1 shows a plan view and cross-sectional view of an aircraft wing rib and panel with good quality holes between the rib foot and panel; 10019] Figure 2 shows a plan view and a cross-sectional view of an aircraft wing rib and panel with mismatched holes between the rib foot and panel; 10020] Figure 3 shows an aircraft wing rib without a support located between the webbing and the rib foot; 100211 Figure 4 shows an aircraft wing rib with a support according to an embodiment of the invention located between the rib webbing and the rib foot; 10022] Figure 5 shows an aircraft rib foot support according to a second embodiment of the invention; and 10023] Figure 6 shows a cross-sectional view of an aircraft rib support according to a third embodiment of the invention.

DETAILED DESCRIPTION

100241 Figure I shows an aircraft rib foot 10 and a panel 12 adjacent to and in contact with the rib foot 10. A hole, or aperture, 14 has been drilled in both the rib foot 10 and panel 12, and the edges of the hole are exactly aligned between the rib foot 10 and the panel 12. Figure 2 shows a similar arrangement, with a rib foot 10', a panel 12', and a hole 14'. However, as can be seen, the edges of the hole 14' in the rib foot 10' and the panel 12' are misaligned. This may be caused by flexing of the rib foot during the drilling process. The present invention seeks to reduce or eliminate the occurrence of misaligned holes during the drilling process.

100251 Figure 3 shows a view of a wing rib foot 10" located adjacent to and in contact with a panel 12". The wing rib foot 10" extends from the main webbing section 16 of the rib 18.

100261 Figure 4 shows a support 20 according to the invention located between the rib foot 10" and the rib webbing 16. The support 20 comprises a rib webbing engagement- face 22, a rib foot engagement-face 24 spaced apart from the rib webbing engagement-face 22, and an aperture 26 associated with the rib foot engagement-face and extending through the support 20 to the rib webbing engagement-face 22. The support 20 is located between and engaged with the rib foot 10" and the rib webbing 16 prior to a drilling operation on the rib foot 10". The support 20 adds rigidity to the rib foot 10" during the drilling operation, reducing the likelihood of the rib foot 10" deflecting during the drilling, thus resulting in misaligned holes once the drilling has been completed. After the drilling operation is completed, the support 20 is removed from the rib foot 10" and rib webbing 16, 100271 Figure 5 shows a support device 50 according to a second embodiment of the invention, The support device 50 is approximately cylindrical in shape and comprises a rib foot side 52 and a webbing side 54. The rib foot side 52 comprises a rib foot engagement-face 56 and the webbing side comprises a rib webbing engagement-face 58.

An aperture 60 runs through the centre of the support device, from the rib foot engagement-face 56 to the rib webbing engagement-face 58. In this embodiment, the

-C -

support device 50 is of two piece construction, with the rib foot side 52 comprising a first part, and the webbing side 54 comprising a second part. The rib foot side 52 comprises a threaded section which is received within a correspondingly threaded section in the webbing side 54. By screwing the rib foot side 52 into or out of the webbing side 54, the overall length of the support device 50 may be decreased or increased. This allows the support device to be used across a number of rib configurations.

100281 Alternative arrangements for adjusting the length of a support device may be provided. Figure 6 shows a schematic view of a support device 60 according to a third embodiment of the invention. In this embodiment, a rib foot side 62 fits within a sleeve 64 in the webbing side 66 of the support 60. A biasing device, comprising a spring (not shown) is located between the rib foot side 62 and the webbing side 66 of the support 60. The biasing device is arranged to allow the rib foot side 62 to slide within the sleeve 64 of the webbing side 66 when compressed by a user of the support device 60.

This compression may allow the support device 60 to be placed in position with respect to a rib foot and corresponding rib webbing. Once the user stops holding the support device 60 in compression, the biasing device may expand to securely hold the support in position.

100291 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.

By way of example only, certain possible variations will now be described.

100301 Various different arrangements to make the support device adjustable may be used. Described above is a threaded arrangement, and a biased arrangement including a sleeve. An alternative arrangement may include a crimped section in the support device aflowing the support device to be increased or decreased in ength, A crimped section may introduce a certain amount of latera' flexibility to the support device, which may be advantageous when putting the support into position. In an alternative arrangement, the support device may be rigid, and rather than adjust the sizing of the support device for different wing ribs, a set of support devices of various sizes may be provided.

100311 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. 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.

Claims

CLAIMS1 An aircraft rib foot support comprising, a rib webbing engagement-face, a rib foot engagement-face, the rib webbing engagement-face and rib foot engagement-face being spaced apart from each other, and an aperture associated with the rib foot engagement-face.
2. An aircraft rib foot support as claimed in claim 1, wherein the spacing between the rib webbing engagement-face and rib foot engagement-face is adjustable.
3. An aircraft rib foot support as claimed in claim 1 or claim 2, wherein the support comprises a first section and a second section, wherein the first section is movable in relation to the second section.
4, An aircraft rib foot support as claimed in any preceding claim, wherein the support comprises a crimped adjustable portion.
5. An aircraft rib foot support as claimed in any of claims 1 to 3, wherein the support comprises a first threaded section and a second threaded section, such that screwing the first section threaded and second threaded section together allows the spacing between the two sections to be adjustable.
6. An aircraft rib foot support as claimed in claim 3, wherein the first section is a sleeve in which the second section is accommodated, such that the first section and second section overlap and may slide with respect to each other.
7. An aircraft rib foot support as claimed in claim 3, wherein the support comprises a telescopic section.
8. An aircraft rib foot support as claimed in any of claims 3 to 7, wherein the support may comprise a biasing element, biasing the First section against the second section.
9. An aircraft rib foot support as claimed in any preceding claim, wherein the support comprises a plastics material.
10. An aircraft rib foot support as claimed in any preceding claim, wherein the aperture associated with the rib foot engagement face extends through the support to the rib webbing engagement face.
1 I. An aircraft rib foot support as claimed in any preceding claim, wherein the aperture associated with the rib foot engagement face allows a drill to pass through at least a section of the support without damage to the support.
12. A method of drilling a hole in an aircraft wing skin and aircraft wing rib foot, comprising the steps of: providing a support, the support as claimed in any of claims ito II; locating the support between the aircraft wing rib foot and webbing of the aircraft wing rib; and drilling a hole in the aircraft wing skin and aircraft wing foot with the support in place.
13. A method as claimed in claim 12, comprising the step of using an adjustable support.
14. A method as claimed in claim 13, comprising the step of adjusting the support when locating the support between the aircraft wing rib foot and webbing of the aircraft wing rib.
15. An aircraft rib foot support substantially as described herein, with reference to the accompanying figures 3 to 6.
16. A method of supporting an aircraft wing rib foot as substantially described herein, with reference to the accompanying figures 3 to 6.