METHOD FOR JOINING SKIN PORTIONS OF A CIRCUMFERENTIALLY CLOSED FUSELAGE

Abstract

A method for joining skin portions of a closed fuselage, in particular for an aircraft or spacecraft, has the following method steps: providing at least a first skin portion and a second skin portion, at least one of the skin portions being fitted with components to remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint such that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components to remain in the fuselage.

Claims

1. A method for joining skin portions of a circumferentially closed fuselage for an aircraft or spacecraft, the method comprising: providing at least a first skin portion and a second skin portion, at least one of the provided skin portions being fitted with components provided to subsequently remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint so that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components provided to subsequently remain in the fuselage.

2. The method of claim 1, wherein at least one of the first joining head and the second joining head are provided as a welding head and, while being guided along the first joint, weld the first skin portion to the second skin portion.

3. The method of claim 1, wherein the first joining head and the second joining head are guided parallel to one another along the first joint to mutually support a joining force.

4. The method of claim 1, wherein the second skin portion is positioned with a second joint formed between the second skin portion and at least one of the first skin portion and a third skin portion.

5. The method of claim 4, wherein a third joining head is guided along the second joint on an outer surface of the fuselage arrangement and a fourth joining head is guided along the second joint on an inner surface of the fuselage arrangement, the fourth joining head being guided along longitudinal guide means arranged inside the circumferentially closed fuselage arrangement.

6. The method of claim 5, wherein at least one of the third joining head and the fourth joining head is provided as a welding head and, while being guided along the second joint, welds the second skin portion to at least one of the first skin portion and the third skin portion.

7. The method of claim 5, wherein the third joining head and the fourth joining head are guided parallel to one another along the second joint to mutually support a joining force.

8. The method of claim 5, wherein the first and the second joint are arranged on opposite sides of the fuselage arrangement.

9. The method of claim 5, wherein the third and fourth joining head are guided simultaneously parallel to the first and second joining head on the fuselage arrangement.

10. The method of claim 5, wherein the third and fourth joining head are guided simultaneously parallel to the first and second joining head directly opposite.

11. The method of claim 5, wherein the third and fourth joining head are guided simultaneously parallel to the first and second joining head at the same height.

12. The method of claim 5, wherein the second joining head and the fourth joining head are guided along common longitudinal guide means.

13. The method of claim 1, wherein the components provided to subsequently remain in the fuselage are configured as an interior system.

14. The method of claim 13, wherein the interior system is configured as at least one seat rail anchored to a cabin floor.

15. The method of claim 13, wherein the interior system is configured as at least one cargo hold floor guidance.

16. The method of claim 15, wherein the interior system is configured as a cargo hold floor rail.

17. The method of claim 1, wherein the components provided to subsequently remain in the fuselage are formed by at least one reinforced primary structural element, which runs in the longitudinal direction of the fuselage and is at least one of reinforced and enlarged.

18. The method of claim 17, wherein the components provided to subsequently remain in the fuselage are formed by a reinforced stringer.

19. The method of claim 17, wherein the components provided to subsequently remain in the fuselage are configured to project into an interior of the fuselage with respect to the other primary structural elements running in the longitudinal direction of the fuselage.

20. A joining device, comprising: a first joining head configured to be guided along a joint on an outer surface of a circumferentially closed fuselage arrangement; a second joining head configured to be guided along the joint on an inner surface of the circumferentially closed fuselage arrangement; and a substructure, said substructure being coupled to the second joining head and being configured to be guided along longitudinal guide means arranged inside the circumferentially closed fuselage arrangement and formed at least in part by the components provided to subsequently remain in the fuselage.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The invention is described in greater detail in the following by way of the accompanying drawings, in which:

[0039] FIG. 1 schematically shows the joining procedure of two skin portions of a circumferentially closed fuselage;

[0040] FIG. 2 is an arrangement for joining two skin portions of a circumferentially closed fuselage, shown schematically;

[0041] FIG. 3 is an arrangement for joining two skin portions of a circumferentially closed fuselage according to a further embodiment, shown schematically;

[0042] FIG. 4 is an arrangement for joining two skin portions of a circumferentially closed fuselage according to a further embodiment, shown schematically;

[0043] FIG. 5 is an arrangement for joining four skin portions of a circumferentially closed fuselage, shown schematically;

[0044] FIG. 6 is an embodiment of a further arrangement for joining skin portions of a fuselage, shown schematically; and

[0045] FIG. 7 shows an aircraft or spacecraft.

[0046] In the drawings, the same reference numerals denote identical or functionally identical components, unless indicated otherwise. The elements of the drawings are not necessarily shown true to scale relative to one another.

DETAILED DESCRIPTION

[0047] FIG. 1 schematically shows the joining procedure of two skin portions 1, 2 of a circumferentially closed fuselage.

[0048] Here, the fuselage to be produced by the joining procedure is shown schematically in cross section and only in portions. It is a circumferentially closed fuselage which is indicated by the lines continued in dashes.

[0049] The first and the second skin portions are positioned relative to one another in a first joint 3, so that the two skin portions 1, 2 describe a circumferentially closed fuselage arrangement 4, i.e. a complete fuselage cross section.

[0050] Here, purely by way of example, the first joint 3 forms a lap joint. However, a butt joint for example would also be conceivable. In this case, an additional connecting portion, for example a doubler, can be provided in the region of the joint 3.

[0051] Before the joining procedure, the second skin portion 2 has already been fitted with components 22 provided to subsequently remain in the fuselage to be produced. These components 22 form longitudinal guide means 7. A singular component or a plurality of components 22 can be provided and here, purely by way of example, a singular component 22, i.e. one component, is shown.

[0052] To join the two skin portions 1, 2, a first joining head 5 is guided along the first joint 3 on the outer surface of the fuselage arrangement 4. A second joining head 6 is guided along the first joint 3 on the inner surface of the fuselage arrangement 4. In this respect, this second joining head 6 is guided along the longitudinal guide means 7 formed by the components 22 inside the circumferentially closed fuselage arrangement 4.

[0053] To guide the second joining head 6 along the components 22 formed as longitudinal guide means 7, a substructure 21 is provided which is formed such that it corresponds to the components 22 and is coupled to the second welding head 6.

[0054] In the embodiment shown, the coupling comprises a motor-driven adjusting means 19 which is configured here purely by way of example as an articulated arm. Other configurations of a coupling of the substructure 21 to the second welding head 6, particularly also non-motor-driven couplings, are possible.

[0055] In the embodiment shown, the first joining head 5 and the second joining head 6 are guided simultaneously in parallel along the first joint 3 in order to join the first and second skin portions 1, 2, so that together they exert a joining action on the first joint 3, as indicated by the wavy lines in the region of the joint 3.

[0056] The joining heads 5, 6 can have very different configurations. For example, one of the joining heads 5, 6 or both joining heads 5, 6 can be a welding head. In this case, the skin portions 1, 2 are formed with a weldable material at least in the region of the joint 3. For example, a weldable material of one skin portion can contain thermoplastics. In particular, it can be a fibre composite material with a thermoplastic matrix.

[0057] FIG. 2 schematically shows an arrangement for joining two skin portions 1, 2 of a circumferentially closed fuselage according to a further embodiment.

[0058] According to this embodiment, the second skin portion 2 is positioned with a second joint 8 between the second skin portion 2 and the first skin portion 1, in addition to the first joint 3. In this respect, the first and the second joint 3, 8 are arranged on opposite sides of the fuselage arrangement 4.

[0059] Here, the two skin portions 1, 2 are each configured as half-shells which each describe one half of a fuselage cross section and thereby form one half of the fuselage arrangement 4.

[0060] Before the skin portions 1, 2 are joined, they are fitted or preassembled with components, in particular with a cabin facing (not shown separately), a cabin floor 15 and also with other interior systems.

[0061] In the embodiment shown, the interior systems are pre-installed in the second skin portion 2 and are provided to subsequently remain in the finished fuselage.

[0062] Here, a joining device 20 provided for joining the first and the second skin portion 1, 2 has an outer holding means 24 in addition to the components shown in FIG. 1. The outer holding means is used, inter alia, for positioning the skin portions 1, 2.

[0063] Furthermore, in this embodiment, the joining device 20 has a third and a fourth joining head 9, 10. The third joining head 9 is guided along the second joint 8 on the outer surface of the fuselage arrangement 4. The fourth joining head 10 is guided along the second joint 8 on an inner surface of the fuselage arrangement 4. For this purpose, the fourth joining head 10 together with the second joining head 6 is guided along common longitudinal guide means 7 which are arranged inside the circumferentially closed fuselage arrangement 4.

[0064] Here, the longitudinal guide means 7 are configured as the seat rails 12 which are arranged in the cabin floor 15. A substructure 21 in the form of a gantry which runs in the seat rails is provided for guiding the second and fourth joining head 6, 10.

[0065] In the embodiment shown, the third and the fourth joining head 9, 10 are guided parallel to one another along the second joint 8. Furthermore, the third and the fourth joining head 9, 10 are also guided in parallel with and at the same height as the first and second joining head 5, 6.

[0066] This arrangement thereby mutually supports and thus compensates joining forces which act on the skin portions by the joining heads. Furthermore, joining forces from the second joining head 6 and the fourth joining head 10 which are to be supported are mutually supported by the motor-driven adjusting means 19 and by the substructure 21. No great lateral forces resulting from the joining forces thereby act on the seat rails 12. In this way, a longitudinal guidance of the welding heads 6, 10 is possible in the seat rails 12, without the seat rails 12 being damaged thereby.

[0067] In the embodiment shown, the holding means 24 is configured by way of example as a gantry which spans the fuselage arrangement 4. Here, in addition to the skin portions 1, 2, the holding means 24 also mounts the welding heads 5, 9 to be guided on the outer side of the fuselage arrangement 4. Therefore, in this case, the first and the third welding head 5, 9 are mounted such that they can be moved along the holding means 24 in the longitudinal direction of the fuselage, so that they can be guided along the first and second joint 3, 8 during the joining process.

[0068] A feed means (not shown here) can be provided for guiding the first and third welding head 5, 9 and/or for guiding the substructure 21 in the seat rails 12. This can be in particular a motor-driven and/or an automatic feed means. The feed of the first welding head 5, of the third welding head 9 and of the substructure 21 supporting the second and fourth welding heads can be coordinated.

[0069] FIG. 3 schematically shows an arrangement for joining two skin portions 1, 2 of a circumferentially closed fuselage according to a further embodiment.

[0070] This embodiment differs from the embodiment according to FIG. 2 in that here the longitudinal guide means 7 are configured as cargo hold floor rails 13 in which the substructure 21 is guided. The cargo hold floor rails 13 are in particular guide rails and/or anchor rails which are arranged in a cargo hold and are provided in the subsequent cargo hold for guiding and/or anchoring cargo, in particular freight containers.

[0071] A further difference of this embodiment is that here the two joints 3, 8 do not lie in a common horizontal plane, but in a plane lying obliquely to the horizontal, though they are arranged directly opposite one another on the fuselage arrangement 4.

[0072] Accordingly, the motor-driven adjusting means 19, which can be configured here as a multi-axis industrial robot, are oriented at different angles to the horizontal.

[0073] The orientation, shown here, of the first and second joint 3, 8, can be an orientation which passes along the fuselage or also merely an orientation which is provided locally in the cross-sectional plane shown or is provided on an individual fuselage section.

[0074] FIG. 4 schematically shows an arrangement for joining two skin portions 1, 2 of a circumferentially closed fuselage according to a further embodiment.

[0075] Unlike the embodiment according to FIGS. 2 and 3, here the longitudinal guide means 7 are configured as a cargo hold floor guidance provided inside a hold. In the embodiment shown, this cargo hold floor guidance is configured as lateral steps 14 which extend in the longitudinal direction of the fuselage. The steps 14 can be, for example, a delimitation of the hold. Furthermore, it would be possible for other interior components, for example a cabin floor, to be placed or mounted on the steps in a subsequent production stage.

[0076] Here, the substructure 21 has a correspondingly adapted form. Thus, provided here as the substructure 21 is a gantry which spans the hold and contacts the steps 14 on two sides in each case by an angle and which can thereby be guided securely along the steps 14.

[0077] A further difference in the embodiment shown here is that the first and the second joint 3, 8 are arranged opposite one another in a vertical plane. Thus, here a first motor-driven adjusting means 19 extends downwards from the substructure 21 into the region of the hold in which the first joint 3 is arranged. A second motor-driven adjusting means extends upwards from the substructure 21, in particular into the region of a cabin ceiling where the second joint 8 is arranged.

[0078] FIG. 5 schematically shows an arrangement for joining four skin portions of a circumferentially closed fuselage.

[0079] Unlike the previous embodiments, here the longitudinal guide means 7 are not formed by an interior system, but by reinforced primary structural elements 18 which extend in the longitudinal direction of the fuselage. The primary structural elements 18 are reinforced stringers which are configured to be significantly stronger than the other stringers 27 which are arranged on the fuselage.

[0080] In the embodiment shown, the substructure 21 is guided in a suspended manner from the reinforced primary structural elements 18 which extend in the longitudinal direction of the fuselage.

[0081] Furthermore, here unlike the previous embodiments, a total of four skin portions 1, 2, 11, 23 are positioned such that they form a circumferentially closed fuselage arrangement 4. For example, they are skin portions 1, 2, 11, 23 which are each configured as quarter shells.

[0082] The first joint 3 is provided between a first skin portion 1 and a second skin portion 2. A second joint 8 is provided between the second skin portion and a third skin portion 11. Furthermore, provided between the third skin portion 11 and a fourth skin portion 23 is a third joint 25 and provided between the fourth skin portion 23 and the first skin portion 1 is a fourth joint 26 which completes the circumferentially closed fuselage arrangement 4. The regions of the four joints 3, 8, 25, 26 are shown here in dotted lines merely to provide a clearer differentiation.

[0083] Yet another difference from the previous embodiments is that here only one pair of joining heads 5, 6 is provided, i.e. a first joining head 5 to be guided on the outer surface of the fuselage arrangement 4 and a second joining head 6 to be guided on the inner surface of the fuselage arrangement 4. In this respect, the second joining head 6 is coupled to the substructure 21 by a motor-driven adjusting means which is swivellable on all sides, for example in the form of a multi-axis, in particular a six-axis industrial robot.

[0084] The two welding heads 5, 6 are thus used here to join each of the four joints 3, 8, 25, 26. For example, the individual joints 3, 8, 25, 26 can be joined one after another. In order to join the four joints, a total of four working steps is thus necessary. Alternatively, the joints can also be joined consistently circumferentially at each of the joints in a longitudinal position so that the substructure is moved sequentially lengthwise when each of the joints 3, 8, 25, 26 has been joined locally in a longitudinal position.

[0085] With this arrangement, which has only one motor-driven adjusting means 19 and only one second welding head 6 on the substructure 21, the weight and size of the parts of the joining device 20 which run inside the circumferentially closed fuselage arrangement 4 can be reduced. In this way, the suspended configuration of the substructure 21 is more easily possible.

[0086] The first skin portion 1, on which the reinforced primary structural element 18 or the reinforced stringers extending in the longitudinal direction of the fuselage are provided, can be coupled in a particularly stable manner to the holding means 24 for holding the skin portion and to the part of the joining means 20 inside the fuselage.

[0087] After the joining procedure, the reinforced stringers can be used as super stringers, i.e. as multifunctional structural elements, for example for the installation of cabin or system modules.

[0088] FIG. 6 schematically shows an embodiment of a further arrangement for joining skin portions of a fuselage.

[0089] For the sake of clarity, the individual skin portions 1, 2 and joining heads 5, 6 and 5, 6, 9 and 10 are not shown in this schematic drawing.

[0090] Optionally or in addition to the components 22 which are provided to subsequently remain in the fuselage, an externally introduced guide means 17 is introduced into the circumferentially closed fuselage arrangement 4 as part of the longitudinal guide means 7. After the joining procedure, said guide means can be removed for example though an open end 16 of the fuselage arrangement 4.

[0091] Here, it is possible to mount the guide means 17 on the components 22 provided to subsequently remain in the fuselage. Alternatively or additionally, an external mounting can be provided for the guide means 17.

[0092] The arrangement shown here is provided for a method for joining skin portions 1, 2; 1, 2, 11, 12 of a circumferentially closed fuselage, in particular for an aircraft or spacecraft, comprising the following method steps: providing at least a first skin portion 1 and a second skin portion 2; positioning at least the first skin portion 1 and the second skin portion 2 relative to one another in a first joint 3 such that the skin portions 1, 2; 1, 2, 11, 12 form a circumferentially closed fuselage arrangement 4; introducing a guide means 17 into the circumferentially closed fuselage arrangement 4; guiding a first joining head 5 along the first joint 3 on an outer surface of the fuselage arrangement 4; and guiding a second joining head 6 along the first joint 3 on an inner surface of the fuselage arrangement 4, the second joining head 6 being guided along longitudinal guide means 7 which are arranged inside the circumferentially closed fuselage arrangement 4 and are formed at least in part by the guide means 17.

[0093] In order to join the final joints, for example orbitally running joints on the nose of the fuselage, a further joining head can then be guided by a small flexible robot or a crawler inside the fuselage.

[0094] Alternatively or additionally, it is possible for other joints, for example the joint for integrating a structure surrounding a door of the fuselage, to be joined, in particular welded to one or more skin portions.

[0095] According to a further embodiment, the guide means 17 can firstly be constructed inside the circumferentially closed fuselage arrangement 4 and then dismantled again after the joining procedure. In this case, the guide means 17 is configured in a demountable and/or modular manner. For example, the guide means can be a demountable framework, formed with struts and couplings.

[0096] An arrangement of this type is then provided in particular for a method for joining skin portions 1, 2; 1, 2, 11, 12 of a circumferentially closed fuselage, in particular for an aircraft or spacecraft, comprising the following method steps: providing at least a first skin portion 1 and a second skin portion 2; positioning at least the first skin portion 1 and the second skin portion 2 relative to one another in a first joint 3 such that the skin portions 1, 2; 1, 2, 11, 12 form a circumferentially closed fuselage arrangement 4; constructing a guide means 17 inside the circumferentially closed fuselage arrangement 4; guiding a first joining head 5 along the first joint 3 on an outer surface of the fuselage arrangement 4; guiding a second joining head 6 along the first joint 3 on an inner surface of the fuselage arrangement 4, the second joining head 6 being guided along longitudinal guide means 7 which are arranged inside the circumferentially closed fuselage arrangement 4 and are formed at least in part by the guide means 17; and dismantling the guide means.

[0097] Of course, apart from the configuration of the longitudinal guide means 7, all the features of the previous embodiments can be combined with this arrangement according to FIG. 6 and with the arrangements and methods described in this connection.

[0098] FIG. 7 shows an aircraft or spacecraft 28. In this case, it is for example an airliner. The aircraft or spacecraft 28 has a fuselage 29 which is produced according to any of the above-described methods for joining skin portions 1, 2 of a fuselage and with a corresponding joining device 20.

[0099] Although the present invention has been described here on the basis of several embodiments, it is not restricted thereto, but can be modified in many different ways.

[0100] For example, it is also conceivable that the welding heads, in particular the welding heads which are guided on the inner surface of the fuselage arrangement, are not guided parallel to one another along the joints. In this way, for example in the case of a limited amount of working space, it is possible to avoid a collision between the welding heads.

[0101] Furthermore, the longitudinal guide means 7 do not necessarily have to have symmetrically arranged guides. An individual guide, for example only one guide rail or guide structure can also be sufficient.

[0102] With each of the methods according to the invention, other types of joints of the skin portions can also be joined, in particular welded, for example in order to integrate a structure surrounding a door of the fuselage.

[0103] 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.