LEADING-EDGE COMPONENT FOR AN AIRCRAFT

Abstract

A leading-edge component for an aircraft includes at least a part of a flow body having a front skin, a hollow space at least partially delimited by the front skin and at least one separate retention device. The at least one retention device comprises a flexible structure with a mesh, a web, a fabric or a plurality of strings. The retention device is arranged behind the front skin in a distance thereto and extends along a main extension direction of at least a section of the front skin. The retention device is configured to retain a front skin that deforms to move into the hollow space upon an impact of a foreign object.

Claims

1-12. (canceled)

13. A leading-edge component for an aircraft, comprising at least a part of a flow body having a front skin, a hollow space at least partially delimited by the front skin and at least one separate retention device, wherein the at least one retention device comprises a flexible structure with a mesh, a web, a fabric or a plurality of strings, wherein the retention device is arranged behind the front skin in a distance thereto and extends along a main extension direction of at least a section of the front skin, and wherein the retention device is configured to retain a portion of the front skin that deforms to move into the hollow space upon an impact of a foreign object.

14. The leading-edge component of claim 13, wherein the retention device is pre-tensioned at least in a spanwise direction.

15. The leading-edge component according to claim 13, wherein the retention device comprises a plurality of individual strings arranged at a distance from each other.

16. The leading-edge component according to claim 13, wherein the retention device comprises a mesh.

17. The leading-edge component according to claim 13, wherein the at least one retention device comprises at least one dampening element that is configured to absorb impact energy.

18. The leading-edge component according to claim 13, further comprising a plurality of ribs, which are arranged at a distance to each other in the hollow space, wherein the at least one retention device is coupled with two neighboring ribs.

19. The leading-edge component according to claim 18, wherein the ribs comprise a plurality of openings for attaching the at least one retention device.

20. The leading-edge component according to claim 13, further comprising a spar arranged in the hollow space, wherein the at least one retention device is coupled with the spar.

21. The leading-edge component according to claim 13, wherein the at least one retention device comprises a plurality of retention devices in a consecutive arrangement.

22. A wing for an aircraft, having a leading-edge component according to claim 13.

23. The wing according to claim 22, further comprising a fixed leading edge, wherein the leading-edge component is movable between a retracted position directly forward the fixed leading-edge and at least one extended position at a further distance to the fixed leading edge.

24. An aircraft having at least one wing of claim 22.

25. An aircraft having at least one leading-edge component according to claim 13.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other characteristics, advantages and potential applications of the present invention result from the following description of the exemplary embodiments illustrated in the figures. In this respect, all described and/or graphically illustrated characteristics also form the object of the invention individually and in arbitrary combination regardless of their composition in the individual claims or their references to other claims. Furthermore, identical or similar objects are identified by the same reference symbols in the figures.

[0030] FIGS. 1a, 1aa, 1b and 2 show an exemplary embodiment of a leading-edge component in schematic sectional views.

[0031] FIG. 3 shows an exemplary embodiment of a leading-edge component in a schematic lateral sectional view.

[0032] FIG. 4 shows an exemplary embodiment of a leading-edge component in a schematic lateral sectional view.

[0033] FIG. 5 shows an exemplary embodiment of a leading-edge component in a schematic lateral sectional view.

[0034] FIGS. 6a and 6b show an exemplary embodiment of a retention device with different mesh setups.

[0035] FIG. 7 shows another exemplary embodiment of a leading-edge component in a schematic top sectional view.

[0036] FIGS. 8a to 8c show exemplary arrangements of multiple retention devices in schematic top sectional views.

[0037] FIG. 9 shows an aircraft.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0038] FIG. 1a shows a schematic sectional view of a part of a leading-edge component 2 for an aircraft. Here, the leading-edge component 2 comprises at least a part of a flow body 4 having a front skin 6 and a hollow space 8, which is at least partially enclosed by the front skin 6. Exemplarily, two ribs 10 are arranged in the hollow space 8 and are attached to the front skin 6. The front 6 comprises a curved shape with a leading edge 12 as seen in FIG. 1aa. Exemplarily, as indicated by the coordinate system in the drawing plane on the top left, the leading edge 12 is swept back. The flow body 4 may thus be a part of a swept back wing of a commercial aircraft. The ribs 10 extend in a chordwise direction and are substantially arranged perpendicular to the leading edge 12.

[0039] In some situations, for example during take-off or landing of the aircraft, the front skin 6 may be hit by a foreign object 14, such as a bird. If this is the case, the front skin 6 deforms and the impact energy is at least partially absorbed during the deformation. With an increasing weight of the foreign object 14, the impact energy to be absorbed by the front skin 6 increases. Depending on an impact position 16, ruptures may occur in the front skin 6. If these are significant enough, the foreign object 14 may enter the hollow space 8. The energy absorption by the front skin 6 then stops. For avoiding this, a retention device 18 is spanned up between two neighboring ribs 10.

[0040] A retention device 18 may comprise surface-like dimensional extensions and is arranged in a distance to the front skin 6. It exemplarily extends along the front skin 6, preferably at a constant distance. In the case shown in FIG. 1a, the retention device 18 is attached to the ribs 10 through dampening elements 20, which provide a dampening function. They may comprise a cylindrical shape. The ribs 10 may comprise openings 22, through which at least a part of the respective retention device 18 is lead. The dampening elements 20 in this example also comprise a continuous borehole 24, through which the respective part of the retention device 18 is fed through. By providing a certain degree of pretension, the retention device 18 and the dampening elements 20 are fixed in their installation positions. For preventing the retention device 18 to slip back through the openings 22 and the boreholes 24, they are secured by separate attachment devices 26. The dampening elements 20 allow an absorption of a part of the impact energy by being compressed.

[0041] In the example illustrated in FIG. 1a, the impact position 16 is directly adjacent to a flange 28 of a rib 10. By this, an excessive shearing force acts onto the front skin 6 during the impact, which leads to a rupture, if the impact load is high enough.

[0042] In FIG. 1b, the object 14 has created a rupture 30 into the front skin 6, such that a section 32 of the front skin 6 is torn out and folds inwardly. Here, it reaches onto the retention device 18, such that it does not fold further. The object 14 does not reach through the ruptures 30. Instead, it further deforms the front skin 6 in a further lateral direction. More kinetic energy can thus be absorbed. This is further supported by the dampening elements 20, which are compressed through the action on to the retention device 18.

[0043] FIG. 2 shows a further effect based on another impact position 16 of the object 14. Here, also a section 32 of the front skin 6 folds inwardly and reaches the retention device 18. In doing so, the object 14 is deflected into a further lateral motion, which avoids the object 14 entering further into the hollow space 8.

[0044] In FIG. 3 another exemplary embodiment of a leading-edge component 34 is shown. Here, a retention device 36 is shown, which comprises a plurality of parallelly arranged strings 38. They are all fed through openings 22 of neighboring ribs 10.

[0045] In FIG. 4, a leading-edge component 40 is illustrated, which comprises a plurality of cutouts 42 at a forward edge 44 of a rib 10, where strings 38 reach through.

[0046] FIG. 5 shows a leading-edge component 46 with a single cutout 42, through which a single string 38 extends. The cutout 42 is arranged directly behind the front skin 6 and in the vicinity of the leading edge 12. An object 14 that impinges onto the leading-edge component 46 may be divided or split into several parts that are deflected and thus travel on different motion paths into the hollow space 8. The individual kinetic energies of the separate parts are clearly less than the original kinetic energy of the object 14.

[0047] FIG. 6a shows a leading-edge component 48 with a retention device 50 that comprises a plurality of strings 52, which are combined to form a mesh. In some sections 54, the mesh comprises a higher density than in other sections 56. For example, in sections 50 and 52 directly adjacent to flanges 28, the mesh has a higher density, since more likely ruptures occur there.

[0048] Since the retention device 50 is based on strings 52, ends of the strings 52 may be fed through openings 22 of ribs 10 and through dampening elements 20 that follow directly behind the openings 22. As shown in FIGS. 6b and 6c, other alternative connections are possible. In FIG. 6b, two strings 52 are combined to form a single end 58 that is fed through a single opening 22 of a rib 10. In FIG. 6c, a string 52 is fed through two neighboring openings 20 of a rib 10 subsequently, such as with a shoelace.

[0049] In FIG. 7, a leading-edge component 60 is shown, which additionally comprises a spar 62 that is arranged at a distance from the leading edge 12. Here, retention devices 64 are arranged with a non-constant distance from the leading edge 12 and extending at an angle to the leading edge 12 from ribs 10 to the spar 62.

[0050] In FIGS. 8a, 8b and 8c, a plurality of retention devices 18 or retention devices 18 that extend through several ribs 10 are illustrated. In FIG. 8a, two neighboring retention devices 18 extend through a pair of dampening elements 20 arranged on two opposed sides of a rib 10. In the drawing plane, one of the retention devices 18 extends to the left to a left rib 10, while the other one extends to the right and is attached to a right rib 10.

[0051] In FIG. 8b, an enlarged single dampening element 20 is arranged on the rib 10 in the middle, while both retention devices 18 extend through the enlarged dampening element 20 and extend to the right and the left as in FIG. 8a.

[0052] In FIG. 8c, an enlarged retention device 18 extends through the rib 10 in the middle and is fed through two laterally arranged dampening elements 20.

[0053] FIG. 9 shows an aircraft 64 having wings 66, which exemplarily comprise leading-edge components 2 according to FIG. 1. Also, leading-edge components 34, 40, 46, 48 or 60 may be used. A vertical tail plane 68, horizontal tail planes 70 or engines 72 may be equipped with at least one of the above explained leading-edge component.

[0054] In addition, it should be pointed out that “comprising” does not exclude other elements or steps, and “a” or “an” does not exclude a plural number. Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments may also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference characters in the claims are not to be interpreted as limitations.

[0055] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.

REFERENCE NUMERALS

[0056] 2 leading-edge component [0057] 4 flow body [0058] 6 front skin [0059] 8 hollow space [0060] 10 rib [0061] 12 leading edge [0062] 14 foreign object [0063] 16 impact position [0064] 18 retention device [0065] 20 dampening element [0066] 22 opening [0067] 24 borehole [0068] 26 attachment device [0069] 28 flange [0070] 30 rupture [0071] 32 section [0072] 34 leading-edge component [0073] 36 retention device [0074] 38 string [0075] 40 leading-edge component [0076] 42 cutout [0077] 44 forward edge [0078] 46 leading-edge component [0079] 48 leading-edge component [0080] 50 retention device [0081] 52 string [0082] 54 section [0083] 56 section [0084] 58 single end [0085] 60 leading-edge component [0086] 62 spar [0087] 64 aircraft [0088] 66 wing [0089] 68