METHOD FOR PRODUCING A TORSION BOX FOR A STRUCTURE OF AN AIRPLANE AND A TORSION BOX FOR A STRUCTURE OF AN AIRPLANE

Abstract

A method for producing a torsion box for a structure of an airplane. The method includes providing a first component made of a fiber composite material, the first component has a first planar base having a first inner side and a first outer side, first stiffening elements on the first inner side forming a composite with the first base. A second component is provided of a fiber composite material and has a second planar base having a second inner side and a second outer side. Second stiffening elements are on the second inner side and form a composite with the second base. The method includes superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side. The methods includes connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

Claims

1. A method for manufacturing a torsion box for a structure of an aircraft, comprising: providing a first component made of a fiber composite material, the first component having a first flat base with a first inner side and a first outer side, wherein multiple first stiffening elements are on the first inner side and form a composite with the first base; providing a second component made of a fiber composite material, the second component comprising a second flat base with a second inner side and a second outer side, wherein multiple second stiffening elements are on the second inner side and form a composite with the second base; superimposition of the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side, and the second stiffening elements lie, at least in some areas, on the first inner side; and connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

2. The method of claim 1, wherein providing the first component or of the second component comprises forming scrims on a molding tool, covering the scrims with a closing device, impregnating the scrims with a resin, curing, and removing the closing device.

3. The method of claim 2, wherein forming the scrims comprises arranging a base scrim to form the base and of stiffening scrims to form the stiffening elements.

4. The method of claim 1, wherein the first stiffening elements and or the second stiffening elements are adhered or welded to their associated base, to form the composite with the associated base.

5. The method of claim 1, wherein the first stiffening elements or the second stiffening elements extend along a same spatial direction.

6. The method of claim 1, wherein connecting comprises producing riveted connections.

7. The method of claim 1, wherein the second stiffening elements are aligned transversely to the first stiffening elements.

8. The method of claim 7, wherein the first stiffening elements are configured to be at least partially interrupted in some areas to realize the second stiffening elements.

9. The method of claim 1, wherein the first stiffening elements are stiffening ribs.

10. The method of claim 1, wherein the second stiffening elements are spars.

11. A torsion box for a structure of an aircraft, comprising: a first component made of a fiber composite material, the first component having a first flat base with a first inner side and a first outer side, wherein multiple first stiffening elements are on the first inner side and form a composite with the first base; and a second component made of a fiber composite material, the second component comprising a second flat base with a second inner side and a second outer side, wherein multiple second stiffening elements are on the second inner side and form a composite with the second base; wherein the first base and the second base are superimposed such that the first stiffening elements lie, at least in some areas, on the second inner side, and the second stiffening elements lie, at least in some areas, on the first inner side; and wherein the first stiffening elements and the second base and the second stiffening elements and the first base are connected to one another in a form-fitting, force-fitting or substance-bonded manner.

12. The torsion box of claim 11, wherein the first stiffening elements are stiffening ribs, wherein the second stiffening elements are spars, and wherein the first and the second stiffening elements are arranged transversely to one another.

13. An aircraft comprising at least one structural component, in which at least one torsion box of claim 11 is integrated.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Further features, advantages and possible applications of the disclosure herein emerge from the following description of the example embodiments and the figures. All of the features described and/or depicted in the figures, individually and in any combination, form the subject matter of the disclosure herein, regardless of their composition in the individual claims or their dependencies. In the figures, the same reference signs continue to be used for the same, or similar, objects.

[0025] FIG. 1 shows a schematic, block-based diagram of a method for manufacturing a torsion box for a structure of an aircraft.

[0026] FIGS. 2A and 2B show the first and the second component in two different views.

[0027] FIGS. 3A and 3B show the manufacture of a first component on a forming tool.

[0028] FIG. 4 shows an aircraft which has a torsion box.

DETAILED DESCRIPTION

[0029] FIG. 1 shows a method 2 for manufacturing a torsion box for a structure of an aircraft. According to the block diagram shown, the method may comprise the following steps. To begin with, a first component made of a fiber composite material is provided 4, which component has a first flat base with a first inner side and a first outer side, wherein multiple first stiffening elements are arranged on the first inner side 6 and form a composite with the first base. A second component made of a fiber composite material is then provided 8. The second component has a second flat base with a second inner side and a second outer side, wherein multiple second stiffening elements are arranged on the second inner side 10 and form a composite with the second base. The first component and the second component are then superimposed on one another 12, in such a manner that the first stiffening elements lie on the second inner side, at least in areas, and the second stiffening elements lie on the first inner side, at least in areas. The first stiffening elements are then connected to the second base and the second stiffening elements to the first base 14. The provision 4 or 8 may involve the formation 16 or 18 of first or second scrims on a forming tool, the covering 20 or 22, the impregnation 24 or 26 with a resin, the curing 28 or 30, and the removal 32 or 34. The formation 16 or 18 of the scrims may include the arrangement 16a of a base scrim for formation of the base and the arrangement of stiffening scrims 16b for formation of the stiffening elements. The connection 14 may involve the making of riveted connections.

[0030] FIGS. 2A-2B show a first component 36 which comprises a first flat base 38. The first base 38 has a first outer side 40 and a first inner side 42. First stiffening elements 44 are arranged on the first inner side 42 and extend parallel to one another along the same direction and are configured as ribs, for example. By way of example, the first base 38 and the first stiffening elements 44 are configured as a coherent scrim and can be jointly infiltrated with resin and cured.

[0031] A second component 46 has a second base 48 with a second outer side 50 and a second inner side 52. There are second stiffening elements 54 located on top of the base which are designed as spars. As can be seen in the sectional depiction, which is characterized as A-A in the right drawing plane, the first stiffening elements 44 have multiple interruptions 56 through which the second stiffening elements 54, which are arranged transversely to the first stiffening elements 44, can run. The first component 36 and the second component 46 are superimposed on one another and connected to one another.

[0032] FIG. 3A shows in highly schematic form a forming tool 58, on which a first base scrim 60 is placed to form the first base 38. Attached to this are first stiffening scrims 62 which are arranged on the first base scrim 60. A first closing device 64 is placed over the scrim 60 and 62 and ends flush with the forming tool 58. Gaps between the first stiffening scrims 62 are likewise covered by the closing device 64. The infiltration with resin and subsequent curing can take place in this position. The method shown relates, in particular, to a vacuum infusion process.

[0033] A slightly modified variant, in which the first base scrim 60 and the first stiffening scrims 62 are arranged on top of one another, is shown in FIG. 3B. A different first closing device 66 is selected in this case, which does not run into gaps between the first stiffening scrims 62. Instead of this, first stiffening elements 68 are arranged there, which supplement the gaps in a radial direction and are covered by the first closing mechanism 66. After curing, they are removed again in a direction parallel to the first stiffening scrims 62 or the first stiffening elements which result. For this purpose, it is particularly favorable for all the stiffening scrims 62 to run in the same direction. The first stiffening elements 68 can then be drawn out in the same direction. This depiction relates, in particular, to an RTM method.

[0034] Devices formed in a similar manner to FIG. 3A or 3B are used for the manufacture of the second component 46.

[0035] FIG. 4 shows an aircraft 70 which has multiple structural components in the form of wings 72, horizontal stabilizers 74, and a vertical stabilizer 76. At least one of these structural components 72, 74 and 76 may be fitted with a torsion box manufactured as previously depicted. By way of example, a torsion box 78 is depicted using dotted lines at one end of one of the wings 72.

[0036] In addition, it should be pointed out that “comprising” does not exclude other elements or steps, and “a” or “an” does not preclude a plurality. In addition, it should be pointed out that features which have been described with reference to one of the above example embodiments can also be used in combination with other features of other example embodiments described above. Reference signs in the claims should not be regarded as a limitation.

[0037] 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” 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 SIGNS

[0038] 2 method

[0039] 4 provision of first component

[0040] 6 arrangement of first stiffening elements

[0041] 8 provision of second component

[0042] 10 arrangement of second stiffening elements

[0043] 12 superimposition

[0044] 14 connection

[0045] 16 formation of first scrim

[0046] 18 formation of second scrim

[0047] 20 covering of first scrim

[0048] 22 covering of second scrim

[0049] 24 impregnation of first scrim

[0050] 26 impregnation of second scrim

[0051] 28 curing of first scrim

[0052] 30 curing of second scrim

[0053] 32 removal of closing device

[0054] 34 removal of closing device

[0055] 36 first component

[0056] 38 first base

[0057] 40 first outer side

[0058] 42 first inner side

[0059] 44 first stiffening elements

[0060] 46 second component

[0061] 48 second base

[0062] 50 second outer side

[0063] 52 second inner side

[0064] 54 second stiffening elements

[0065] 56 interruptions

[0066] 58 forming tool

[0067] 60 first base scrim

[0068] 62 first stiffening scrims

[0069] 64 first closing device

[0070] 66 first closing device

[0071] 68 first stiffening elements

[0072] 70 aircraft

[0073] 72 wing

[0074] 74 horizontal stabilizer

[0075] 76 vertical stabilizer

[0076] 78 torsion box