STRUCTURAL ROD FOR AN AIRCRAFT, COMPRISING A ROD BODY WITH A SANDWICH STRUCTURE

Abstract

A method for manufacturing structural rods to make it easier to manufacture a structural rod for an aircraft and to improve performance. Each rod includes a rod body and two end portions disposed at either end of the rod body along a longitudinal central rod axis, each end portion comprising at least one mounting lug that protrudes from the rod body along the longitudinal axis. The method includes producing a sandwich panel including two skins gripping a cellular inner body, at least one of the two outer skins having a skin extension for forming a part of the at least one mounting lug of at least one of the two end portions of the rod, and cutting the panel along parallel cutting lines to obtain the structural rods.

Claims

1. A method for manufacturing a plurality of structural rods, each rod comprising a rod body and two end portions that are disposed at either end of the rod body along a longitudinal central rod axis, each end portion comprising at least one mounting lug that protrudes from the rod body along the longitudinal axis, the method comprising: producing a sandwich panel comprising two skins gripping a cellular internal core, at least one of the two outer skins having a skin extension for forming a part of the at least one mounting lug of at least one of the two end portions of the rod; and cutting the panel along parallel cutting lines to obtain the plurality of structural rods.

2. The method according to claim 1, wherein two lateral webs are placed in a manner respectively covering two sides of the cellular internal core.

3. The method according to claim 1, wherein the cuts are made simultaneously.

4. The method according to claim 1, wherein at least one of the two outer skins has two skin extensions for forming a part of the at least one mounting lug of each of the two end portions of the rod.

5. The method according to claim 1, wherein U-shaped closure pieces are joined to the ends of the cellular inner body.

6. The method according to claim 1, wherein transition pieces are put in place, the transition pieces having: a first part gripped between one of the two outer skins and an end of the cellular internal core in a direction of the longitudinal central axis, the first part of the transition piece having a thickness that increases as it extends in a direction of the associated lug, the first part having a first chamfer pressed against a second chamfer made at the end of the cellular internal core; a second part that extends the first part and is secured to the skin extension that forms an integral part of the associated lug.

7. The method according to claim 1, wherein the cellular internal core is made: from foam with closed or open pores; or from honeycomb; or using tubular elements that are secured to one another by being stacked in a stacking direction parallel to the longitudinal central axis, each tubular element having a cavity centered on a tubular element axis orthogonal to the longitudinal central axis of the rod.

8. The method according to claim 5: wherein transition pieces are put in place, the transition pieces having: a first part gripped between one of the two outer skins and an end of the cellular internal core in a direction of the longitudinal central axis, the first part of the transition piece having a thickness that increases as it extends in a direction of the associated lug, the first part having a first chamfer pressed against a second chamfer made at the end of the cellular internal core; a second part that extends the first part and is secured to the skin extension that forms an integral part of the associated lug; and wherein at least one of the end portions of the rod has two facing mounting lugs, each of the two lugs having: an external skin formed by the skin extension; a central body formed by the second part of the transition piece; and an internal skin formed by the closure piece of generally U-shaped section, the two legs of the U respectively forming the internal skin of each of the two facing lugs, and the base of the U being pressed against the end of the cellular internal core of the rod body, between the two lugs.

9. The method according to claim 1, wherein the sandwich panel is produced by hot pressing or in an autoclave.

10. A rod produced by the method according to claim 1.

11. An aircraft comprising at least one rod according to claim 10.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0033] This description will be provided with reference to the appended drawings, in which:

[0034] FIG. 1 shows a schematic front view of an aircraft;

[0035] FIG. 2 shows a perspective view of one of the landing gears with which the aircraft in FIG. 1 is equipped;

[0036] FIG. 3 shows a front view of a central wing box with which the aircraft in FIG. 1 is equipped;

[0037] FIG. 4 shows a perspective view of a structural rod with which the aircraft in FIG. 1 is equipped, the rod being in the form of a first preferred embodiment of the disclosure herein;

[0038] FIG. 5 shows a partial perspective view of the rod shown in the preceding figure, in section on the median longitudinal plane P in FIG. 4;

[0039] FIG. 6 shows an enlarged plan view of an end of the rod shown in FIG. 5;

[0040] FIG. 7 shows an exploded perspective view of the rod shown in FIGS. 4 to 6;

[0041] FIG. 8 is a perspective view schematically depicting a step for producing a sandwich panel, with a view to manufacturing a plurality of structural rods;

[0042] FIG. 9 is a perspective view schematically depicting a subsequent step for producing the sandwich panel;

[0043] FIG. 10 is a perspective view schematically depicting a further subsequent step for producing the sandwich panel;

[0044] FIG. 11 is a plan view schematically depicting a step of curing the sandwich panel;

[0045] FIG. 12 is a plan view schematically depicting an alternative embodiment for curing the sandwich panel;

[0046] FIG. 13 is a perspective view schematically depicting a step of trimming the sandwich panel;

[0047] FIG. 14 is a perspective view schematically depicting a step of cutting the sandwich panel so as to obtain the structural rods;

[0048] FIG. 15 is a perspective view schematically depicting a step of fastening the lateral webs to the structural rods;

[0049] FIG. 16 is a perspective view schematically depicting a step of finishing the end portions of one of the structural rods;

[0050] FIG. 17 is a perspective view of a structural rod similar to that in FIG. 4, according to an alternative embodiment;

[0051] FIG. 18 shows a perspective view of another structural rod in the form of a second preferred embodiment of the disclosure herein;

[0052] FIG. 19 shows a partial enlarged plan view of an end of the rod shown in FIG. 18;

[0053] FIG. 20 shows an exploded perspective view of the rod shown in FIGS. 18 and 19;

[0054] FIG. 21 is a perspective view schematically depicting a step of manufacturing the cellular internal core of the rod shown in FIGS. 18 to 20; and

[0055] FIG. 22 is a perspective view schematically depicting a step of cutting a sandwich pan& obtained with the core shown in FIG. 21 so as to obtain the structural rods.

DETAILED DESCRIPTION

[0056] FIG. 1 shows an aircraft 100 of the commercial airplane type, comprising two wings 2 that are fastened to a fuselage 3 and each support a turbomachine 1, such as a jet engine.

[0057] The two wings 2 are fastened to one another by a central wing box 4, an example of which is shown in FIG. 3. This central wing box 4 is conventionally produced using an upper wall 6, a lower wall 8, lateral walls 10 and structural rods 12 connecting the two walls 6, 8.

[0058] The aircraft 100 is also equipped with a plurality of landing gears 14, an example of which is shown in FIG. 2. It conventionally has a plurality of articulated structural rods 16.

[0059] The disclosure herein relates to structural rods intended to equip the aircraft, such as the rods described above, which form an integral part of the central wing box 4 or of the landing gears 14. Nevertheless, other applications can be envisaged for the structural rod according to the disclosure herein, which rod can be incorporated in any aircraft airframe, without departing from the scope of this disclosure herein.

[0060] With reference now to FIGS. 4 to 6, a structural rod 20 according to a first preferred embodiment of the disclosure herein is shown.

[0061] The structural rod 20 extends along a longitudinal central axis 24, parallel to a longitudinal direction 22 of this same rod. Overall, the rod 20 has a rod body 26 that extends along a great majority of the length of the rod, of which it constitutes the central portion with respect to the direction 22. At either end of the rod body 26, along the axis 24, two end portions 28 are provided. These end portions 28 have identical or different designs, but in all cases they allow the rod to be fastened to the two aircraft elements to be connected. In the first preferred embodiment that is envisaged, the two end portions 28 have identical designs, being arranged symmetrically with respect to a median transverse plane of the rod. Consequently, only one of the two end portions 28 will be described below.

[0062] The end portion 28 has at least one mounting lug 30, arranged so as to protrude from the rod body 26 along the axis 24. Preferably, two mounting lugs 28 equip the end portion 28, so as to form a fastening clevis, being parallel or substantially parallel to one another.

[0063] Each mounting lug 30 has an orifice 32 passing through it so as to receive a fastening member (not shown), such as a hinge pin intended to pass through the clevis.

[0064] One of the particular features of the disclosure herein resides in the design of the rod 20, of which the rod body 26 has a sandwich structure. More specifically, the rod body 26 is made from two opposite outer skins 34, between which is gripped a cellular internal core 38, in this case a foam. The foam may have closed or open pores, exhibiting high stiffness. It may for example be a metal foam, but any foam that is the to be rigid is considered appropriate. In general, it can be a foam that is dense (density of between 30 and 300 kg/m.sup.3) and rigid, has a high compressive strength, is compatible with the transformation temperatures and is capable of adhesively bonding to composite materials.

[0065] At each of the two ends of the foam core 38, which are opposite to one another in the direction 22, a chamfer 40 is provided on each of the upper face and the lower face. The two opposite chamfers 40 bring about a reduction in the thickness of the foam core 38, in the direction 42 in which the elements of the sandwich structure are stacked. The stacking direction 42 is orthogonal to the longitudinal direction 22 of the rod.

[0066] Each of the two outer skins 34 has, at its two respective ends that are opposite to one another in the direction 22, two skin extensions 44 intended to form a part of one of the two mounting lugs 30 of each of the two end portions 28.

[0067] Furthermore, for each lug 30, a transition piece 46 is provided, one part of which is located in the rod body 26 and the other part of which is incorporated in the lug 30 in question. More specifically, the transition piece 46 first of all has a first part 46a gripped between one of the two outer skins 34 and one of the ends of the internal core 38. This first part 46a, which has a triangular overall shape, thus has a thickness that increases as it extends in the direction of its associated lug 30. This increasing thickness is embodied by the presence of a chamfer 48, called first chamfer, which is pressed against the chamfer 40 of the core 38, called second chamfer. The cooperation of these two chamfers 40, 48 allows the rod body 26 to have a constant overall thickness, as far as the terminal part of its two opposite longitudinal ends.

[0068] The transition piece 46 also has a second part 46b that extends the first part 46a and is integral therewith. The second part 46b has a constant or substantially constant thickness and is parallelepipedal.

[0069] With this design, each of the two lugs 30 of the clevis is formed by stacking, in the direction 42, an outer skin formed by the skin extension 44, a central body formed by the second part 46b of the transition piece, and an internal skin. These three stacked elements are secured to one another.

[0070] As regards the two internal skins of the two lugs 30 forming the clevis, these are formed by a closure piece 54 of generally U-shaped section, as is most clearly visible in FIG. 6. Specifically, the two legs 56 of the U respectively form the internal skin of each of the two facing lugs 30. In addition, the base of the U 58 is pressed against the end of the internal core 38 of which the thickness is reduced by the chamfers 40, being situated between the base of the two lugs 30.

[0071] Finally, in order to laterally form the rod and isolate the internal core 38 from the outside, two lateral webs 60 covering the two opposite sides of the core 38 are provided. Each lateral web 60 has two lips that are opposite one another in the direction 42, these lips pressing respectively against the two outer skins 34, so as to better contain the core 38.

[0072] With the exception of the internal core 38, all of the constituent elements of the rod that have been described above are preferably made using a composite material, and more preferentially a carbon fibre reinforced polymer material, also known as CFRP. Other composite materials can nevertheless be used, without departing from the scope of the disclosure herein.

[0073] There will now be described a method for manufacturing a plurality of structural rods 20, such as the rod that has just been described above.

[0074] First of all, various elements are joined together so as to produce a sandwich panel. During this joining together, which will be described with reference to FIGS. 8 to 10, the elements adhere to one another on account of the nature of their material, or on account of the interposition of adhesive layers.

[0075] First of all, with reference to FIG. 8, the U-shaped closure pieces 54 are joined to the ends of a cellular inner body in the form of a foam plate 38′, which has already been chamfered. Next, with reference to FIG. 9, the transition pieces 46 are put in place, followed by the outer skins 34, as can be seen in FIG. 16.

[0076] The panel 62 thus obtained then undergoes a step of curing, by polymerization. This curing step is carried out in a conventional manner, for example by hot pressing the panel 62, as is depicted schematically in FIG. 11, or in an autoclave 64, as can be seen in FIG. 12.

[0077] When the polymerization is complete, the resulting hardened panel 62 is trimmed along its periphery, along a trimming line 66 shown in FIG. 13. The aim of this trimming is to obtain a panel with protruding edges.

[0078] Next, the panel 62 is cut multiple times, along mutually parallel cutting lines 68 that are also parallel to the longitudinal direction 22 of the rods 20 obtained after these cuts. FIG. 14 schematically shows these cuts, which can be made in succession, or simultaneously for increased productivity.

[0079] A single panel 62 can give rise to a large number of structural rods 20, this number depending on the initial size of the panel and on the size of the desired rods.

[0080] Once the rods 20 have been obtained, the lateral webs 60 are placed, for example by adhesive bonding to the outer skins 34, so as to close a sealed envelope in which the cellular internal core 38 is located. This step is schematically depicted in FIG. 15.

[0081] Finally, the method for manufacturing the rods 20 is completed by the optional machining of the mounting lugs 30 and the drilling of their orifices 32. The machining consists in or comprises rounding the lugs 30 at each of the two end portions 28, as can be seen in FIG. 16.

[0082] With reference now to FIG. 17, an alternative embodiment is shown, in which the cellular internal core 38 is replaced by a honeycomb bar. The cells of the honeycomb bar are oriented parallel to the direction 42 in which the elements of the sandwich structure are stacked.

[0083] The other elements of the rod 20 are similar to those presented in the description of the first preferred embodiment, and the manufacturing method likewise remains identical or similar.

[0084] With reference now to FIGS. 18 to 20, a rod 20 according to a second preferred embodiment of the disclosure herein will be described. The rod 20 has a large number of features in common with the rod described above in the context of the first preferred embodiment. Thus, in the figures, elements that bear the same numerical references correspond to elements that are identical or similar.

[0085] In the second preferred embodiment, it is essentially the nature of the cellular internal core 38 that is different, and the lateral webs 60 can also optionally be omitted.

[0086] The cellular internal core 38 is in this case produced using tubular elements 70, 70′ that are secured to one another by being stacked in a stacking direction 72, corresponding to the longitudinal direction 22 of the rod 20 and parallel to the axis 24. Each tubular element 70, 70′ has a cavity 74 centered on a tubular element axis 76 orthogonal to the axis 24 of the rod. The cavities 74, also called cells, thus remain open laterally on both sides of the rod 20, on the side of the ends of the tubular elements. For example, between five and thirty of them are provided, and preferably more than ten.

[0087] With the exception of the two tubular elements 70′ situated respectively at the two opposite longitudinal ends of the core 38, these tubular elements 70 preferably have a square or rectangular section. For the two end tubular elements 70′, the section has a trapezoidal shape, so that each of the two of them defines the two second chamfers 40 intended to cooperate with the transition pieces 46.

[0088] In order to manufacture the rods 20, provision is in this case also made to manufacture a sandwich panel, of which the production of the cellular inner body 38′ is schematically depicted in FIG. 21. It consists in or comprises arranging a plurality of tubes 78 adjacent to one another, in the stacking direction 72 orthogonal to the axis of these tubes 78.

[0089] Once the central plate 38′ has been assembled in this way, the operations of joining together the other components and the step of curing the panel are then carried out in a manner identical or similar to that set out in the context of the description of the first preferred embodiment.

[0090] The cuts are then made along cutting lines 68 that are parallel to the stacking direction 72 and therefore orthogonal to the tubular element axes 76, as is schematically depicted in FIG. 22.

[0091] By virtue of the skin extensions 44, the disclosure herein allows better transmission of the loads from the rod body 26 to the mounting lugs 30. This transmission of loads is further improved by the presence of the transition pieces 46, ensuring the join between the rod body 26 and the end portions 28.

[0092] Even with a lighter mass, the structural rod 20 according to the disclosure herein affords excellent mechanical properties, in particular in tension and in compression, but also in bending in a direction orthogonal to the longitudinal direction 22 of this rod.

[0093] Finally, the design of the structural rod 20 allows quick, easy and inexpensive manufacture, in particular by producing a sandwich panel with a large surface area, which is then intended to be cut so as to obtain a plurality of identical rods.

[0094] Of course, a person skilled in the art can make various modifications to the disclosure herein which has just been described, purely by way of non-limiting examples, and within the limits of the scope of the appended claims.

[0095] While at least one example embodiment of the 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 example embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a”, “an” or “one” do not exclude a plural number, and the term “or” by 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.