Method for joining skin sections of a fully enclosed torso

Abstract

Method for joining skin sections (1, 2; 1, 2, 11, 12) of a fully enclosed fuselage, in particular for an aircraft or spacecraft, comprising the following process steps: Providing at least one first skin section (1) and one second skin section (2), wherein at least one of the provided skin sections (1, 2; 1, 2, 11, 12) is equipped with components (12; 13; 14; 18; 22) intended to remain in the fuselage later; Positioning at least the first skin section (1) and the second skin section (2) relative to each other in a first thrust (3), so that the skin sections (1, 2; 1, 2, 11, 12) form a fully enclosed trunk arrangement (4); Guiding a first joining head (5) along the first butt joint (3) on an outer surface of the fuselage assembly (4); and Guiding a second joining head (6) along the first joint (3) on an inner surface of the body assembly (4), wherein the second joining head (6) is guided along longitudinal guide means (7) arranged within the fully enclosed body assembly (4), which are formed at least partially with the components (12; 13; 14; 18; 22) intended to remain in the body later.

Description

[0001] The present invention relates to a method for joining skin sections of a circumferentially closed fuselage, in particular for an aircraft or spacecraft.

[0002] Although applicable to any type of circumferentially closed fuselage, the present invention and the problem underlying it are explained in more detail with reference to the fuselage of an aircraft.

[0003] For a long time, riveting processes were predominantly used in the manufacture of aircraft fuselages to join skin sections or fuselage sections. A riveting device for producing riveted joints is described in DE 198 34 702 A1. This device features a machine guide arranged in a ring around the outside of the aircraft fuselage and movable in the longitudinal direction of the aircraft. Furthermore, an inner part of the riveting device is provided, which has a support frame movable in the longitudinal direction of the aircraft. The support frame consists of a support arm stand, a support arm guide, and a support arm movable along the support arm guide in the longitudinal direction of the aircraft.

[0004] In modern aircraft fuselages, welding processes are sometimes also used to join skin sections. Other, specially adapted processes and devices are used for this. For example, DE 10 2011 114 922 A1 describes a process in which positioning devices in the form of a frame structure are attached to the outside of a fuselage. The positioning devices serve to hold the fuselage sections to be joined and simultaneously serve as a guide for a friction stir welding head used to join the fuselage sections.

[0005] For joining skin sections, US 6 098 260 A describes a rivet fastening system for radial connections of aircraft fuselages and a method for assembling an elongated cylindrical structure.

[0006] US Pat. No. 6,073,326 A describes a mini-rivet system for lap joints for the automatic fastening of aircraft structures. The lap joint between the fuselage sections is created by a mini-rivet system mounted on a rail system.

[0007] US 4,662,556 A describes a device for mechanical riveting of sheet metal element structures, such as aircraft fuselage sections. A guide beam supports a movable work unit with drilling machines and rivet installation equipment.

[0008] Against this background, it is the object of the present invention to provide an improved method for joining skin sections of a circumferentially closed fuselage.

[0009] According to the invention, this object is achieved by a method having the features of patent claim 1 and / or a joining device having the features of patent claim 15.

[0010] Accordingly, it is provided: - A method for joining skin sections of a circumferentially closed fuselage, in particular for an aircraft or spacecraft, comprising the following method steps: providing at least a first skin section and a second skin section, wherein at least one of the provided skin sections is equipped with components intended to remain later in the fuselage; positioning at least the first skin section and the second skin section relative to one another in a first joint, such that the skin sections 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 assembly, wherein the second joining head is guided along longitudinal guide means arranged within the circumferentially closed fuselage assembly, which are formed at least partially with the components intended to remain later in the fuselage; - A joining device, in particular designed for a method according to the invention for joining skin sections of a circumferentially closed fuselage, comprising: a first joining head which can be guided along a joint on an outer surface of a circumferentially closed fuselage arrangement; a second joining head which can be guided along the joint on an inner surface of the circumferentially closed fuselage arrangement; and a substructure, wherein the substructure is coupled to the second joining head and is designed to be guided along longitudinal guide means arranged within the circumferentially closed fuselage arrangement, which are at least partially formed with components intended to remain later in the fuselage.

[0011] The idea underlying the present invention is to attach components intended to remain in a fuselage later to the skin sections before the skin sections are joined and to use these as longitudinal guide means for a joining head for joining the skin sections.

[0012] The joining process is performed on both sides of the fuselage skin. Thus, in addition to the joining head being guided along a joint inside the fuselage assembly, a joining head is also guided along the joint outside the fuselage assembly. This enables a highly dimensionally accurate yet simple and efficient fuselage production. In particular, this method ensures that a skin section pre-assembled with components intended to remain in the fuselage later can be joined more easily in a synergistic manner using these components.

[0013] According to a preferred embodiment, the skin sections contain a thermoplastic material, so that the joining process can include thermal joining and / or forming. Alternatively or additionally, another joining process can also be used.

[0014] As a connection between the second joining head and the longitudinal guide means, a substructure is preferably provided which is guided on the longitudinal guide means.

[0015] In order to enable a flexible alignment of the second joining head, a structure and / or a motorized actuating device, in particular a multi-axis robot, can be provided between the substructure and the joining head.

[0016] The first and second joining heads can have a wide variety of configurations, adapted to the selected joining process. They are specifically designed to exert a joining force sufficient to join the skin sections.

[0017] The circumferentially closed hull can have a wide variety of configurations. In particular, it is tubular or barrel-shaped. However, other hull shapes are also conceivable, such as oval or hulls with straight sections or corners.

[0018] In particular, the invention relates to a fuselage for an aircraft or spacecraft, for example a commercial airliner. Due to its dimensions, such a fuselage cannot be handled using conventional positioning means. Therefore, special production facilities are required. The diameter of such a fuselage is in particular several meters. Accordingly, large skin sections are provided for positioning a circumferentially closed fuselage arrangement, for which at least two skin sections are necessary. Accordingly, the fuselage arrangement is in particular at least two-part. However, fuselage assemblies divided into three, four, or multiple parts can also be provided. Accordingly, a different number of the skin sections required for positioning the circumferentially closed fuselage arrangement can then also be provided.

[0019] The fuselage arrangement can, in particular, represent only a single fuselage section or a single fuselage section. However, it is also conceivable to represent the entire length of the fuselage. It is always a circumferentially closed fuselage arrangement, in particular one representing a completely closed fuselage cross-section.

[0020] The hull arrangement can be open or closed at its longitudinal ends.

[0021] The components intended to remain in the fuselage later can have a wide variety of designs. Preferably, they are components that extend evenly along the fuselage's longitudinal direction.

[0022] The substructure of a joining device has a design corresponding to the components intended to remain later in the fuselage. In particular, the substructure is designed such that, in combination with the components intended to remain later in the fuselage, longitudinal guidance of the second joining head is possible. If, for example, a longitudinally extending edge of a component serves for longitudinal guidance, the substructure can have a carriage shaped correspondingly to the edge. However, it is also conceivable that the components intended to remain later in the fuselage represent anchoring and / or alignment points which are provided for the temporary holding or fastening of components of the substructure extending in the longitudinal direction of the fuselage for guidance.

[0023] In this way, the components intended to remain in the fuselage later enable the substructure to be guided longitudinally so that the second joining head can be guided along the first joint.

[0024] The joining device can further comprise a holding device for holding or fixing the skin sections and / or for displaceably supporting the first joining head to be guided along the first joint on the outer surface of the fuselage arrangement.

[0025] Advantageous embodiments and improvements of the invention can be found in the subclaims.

[0026] According to a preferred development, the first joining head and the second joining head are provided as a welding head. It is also conceivable to provide only one of the two joining heads as a welding head. The welding head welds the first skin section to the second skin section when guided along the first joint. Advantageously, a single guide of the welding head along the first joint is therefore sufficient to join the first skin section to the second skin section. In this way, a very fast and very simple production of a fuselage is possible compared to riveting processes. Furthermore, the production time and also the production effort are advantageously reduced. This embodiment is preferably used for skin sections that contain a metallic or thermoplastic material. In particular, this can be a fiber-reinforced plastic with a thermoplastic matrix.

[0027] According to a preferred embodiment, the first joining head and the second joining head are guided parallel to each other along the first joint to mutually support a joining force. Advantageously, this eliminates the need to support the joining force via the skin sections, so that the positioning of the skin sections is advantageously maintained with high precision. Furthermore, this way, the skin sections are joined without any tension, which would otherwise be applied, for example, by a one-sided joining force. Advantageously, the shape of the joined connection is thus not affected.

[0028] According to one embodiment, the second skin section is positioned with a second joint. The second joint is formed either between the second skin section and the first skin section or between the second skin section and a third skin section. In this way, the skin sections are joined to form a completely circumferentially closed fuselage shape. In the first case, for example, this is a fuselage arrangement with two half-shells as skin sections. In particular, each of the two half-shells describes a curvature of 180°. In the second case, the fuselage arrangement can have a plurality of three or more skin sections. For example, an advantageous embodiment of a fuselage arrangement can have four skin sections, for example in the form of four quarter shells. In this way, a symmetrical arrangement is possible.Further numbers of skin sections and other divisions to form a circumferentially closed hull shape are of course possible.

[0029] According to one embodiment, a third joining head is guided along the second joint on an outer surface of the fuselage assembly. Furthermore, a fourth joining head is guided along the second joint on an inner surface of the fuselage assembly, wherein the fourth joining head is guided along longitudinal guide means arranged within the circumferentially closed fuselage assembly. In this way, production is advantageously possible in a shorter time, since both the first joint and the second joint of the fuselage assembly can be worked on or joined simultaneously. In particular, the longitudinal guide means for guiding the fourth joining head can also be formed at least partially with the components intended to remain later in the fuselage.

[0030] According to one embodiment, the third joining head and the fourth joining head are provided as a welding head. Alternatively, only one of the two joining heads, i.e., the third or the fourth joining head, can be provided as a welding head. When guided along the second joint, the welding head welds the second skin section to the first skin section or to the third skin section, depending on the number and distribution of the skin sections in the circumferentially closed fuselage arrangement.

[0031] According to an advantageous embodiment, the third joining head and the fourth joining head are guided parallel to each other along the second joint to mutually support a joining force. As explained with regard to the first joint, this ensures that the joining force does not need to be supported via the skin sections. Joining is thus carried out in a state in which the skin sections are preferably stress-free.

[0032] According to a particularly preferred embodiment, the first and second joints are arranged on opposite sides of the fuselage assembly. In this way, if a substructure for supporting the second and fourth joining heads is connected to one another, joining forces acting on the second and fourth welding heads can be balanced via the substructure. Advantageously, the longitudinal guide means provided within the circumferentially closed fuselage assembly therefore do not need to support large joining forces. In this way, components intended to remain in the fuselage later can advantageously be used at least as part of the longitudinal guide means, since they remain undamaged due to the low acting forces.

[0033] According to a further preferred embodiment, the third and fourth joining heads are guided simultaneously parallel to the first and second joining heads. In particular, the two joining head pairs, i.e., the third and fourth joining heads and the first and second joining heads, are guided directly opposite one another on the fuselage assembly and optionally or additionally at the same height. Advantageously, the joining force is thus applied symmetrically, enabling optimal force support.

[0034] According to a particularly advantageous embodiment, the second joining head and the fourth joining head are guided along common longitudinal guide means. Advantageously, forces acting from the second and fourth joining heads can thus balance each other out, so that they do not need to be supported by the longitudinal guide means. This, in turn, enables the use of components intended to remain in the fuselage later as longitudinal guide means or as parts of the longitudinal guide means.

[0035] According to one embodiment, the components intended to remain in the fuselage later are designed as an interior system. An interior system comprises any type of installation that remains provided in the future interior of a fuselage. This is preferably an interior system that performs structural functions in the interior. Preferably, it is an interior system that extends at least partially along the fuselage's longitudinal axis, in particular an interior guide or rail system. In this way, a system that is to be provided anyway in the fuselage can particularly advantageously serve as a longitudinal guide means for the second welding head and / or the fourth welding head.In particular, the second welding head and / or the fourth welding head is provided with a substructure corresponding to the longitudinal guide means, which is adapted to the interior system, so that the longitudinal guidance of the second and / or fourth welding head is possible.

[0036] According to one embodiment, the interior system is designed as at least one seat rail anchored in a cabin floor. Advantageously, a rail system already provided in the fuselage can thus be used as a longitudinal guide for joining the skin sections.

[0037] According to a further embodiment, the interior system is designed as at least one cargo space floor guide. For example, this can be a cargo space floor rail. Alternatively or additionally, the cargo space floor guide can also be guide devices provided, for example, for freight containers. It is also conceivable to design the floor of the cargo space with a step running continuously in the longitudinal direction and to guide the second and / or fourth welding head along this step, in particular by means of a substructure of the second and / or fourth welding head that is designed to correspond to the step and to guide along the step. In this way, the cargo space or freight space, which is already provided with longitudinal guide means, is advantageously used to guide the welding head for joining the skin sections.

[0038] According to yet another embodiment, the components intended to remain in the fuselage later are formed with at least one reinforced primary structural element running in the longitudinal direction of the fuselage. In particular, this can be a reinforced stringer (a so-called "superstringer"). The reinforced primary structural element is reinforced and / or enlarged, in particular compared to the other primary structural elements running in the longitudinal direction of the fuselage, and / or is formed to protrude into an interior of the fuselage. This design of the primary structural element can preferably also be used in the later fuselage for additional functions, for example, for the installation of particularly heavy components, for cabin or system module installation, or the like.

[0039] The above embodiments and further developments can be combined with each other as desired, where appropriate. In particular, the features and elements described with regard to the method for joining skin sections also represent features of a corresponding joining device intended for carrying out the method and / or a corresponding arrangement for carrying out the method.

[0040] Further possible embodiments, refinements, and implementations of the invention also include combinations of features of the invention described above or below with reference to the exemplary embodiments that are not explicitly mentioned. In particular, those skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.

[0041] The invention is explained in more detail below using exemplary embodiments with reference to the accompanying figures of the drawing.

[0042] From the figures show: Fig. 1 schematically shows the joining of two skin sections of a circumferentially closed fuselage; Fig. 2 a schematically illustrated arrangement for joining two skin sections of a circumferentially closed fuselage; Fig. 3 a schematically illustrated arrangement for joining two skin sections of a circumferentially closed fuselage according to a further embodiment; Fig. 4 a schematically illustrated arrangement for joining two skin sections of a circumferentially closed fuselage according to yet another embodiment; Fig. 5 a schematically illustrated arrangement for joining four skin sections of a circumferentially closed fuselage; Fig. 6 shows a schematically illustrated embodiment of a further arrangement for joining skin sections of a fuselage; and Fig. 7 an aircraft or spacecraft.

[0043] In the figures, the same reference numerals designate identical or functionally equivalent components unless otherwise stated. The elements of the drawings are not necessarily shown to scale.

[0044] Fig. 1 shows schematically the joining of two skin sections 1, 2 of a circumferentially closed fuselage.

[0045] The hull to be produced by joining is shown here schematically in cross-section and only in sections. It is a circumferentially closed hull, which is indicated by the dashed lines.

[0046] The first and the second skin section are positioned relative to each other in a first joint 3, so that the two skin sections 1, 2 describe a circumferentially closed fuselage arrangement 4, ie a complete fuselage cross-section.

[0047] The first joint 3 here represents a lap joint purely for the sake of example. However, a butt joint would also be conceivable. In this case, an additional connecting section, such as a doubler, can be provided in the area of ​​joint 3.

[0048] The second skin section 2 is already equipped with components 22 prior to joining, intended to remain later in the fuselage to be manufactured. These components 22 form longitudinal guide means 7. There may be a single or a plurality of components 22, whereby only a single number of components 22, i.e., a single component, is shown here purely by way of example.

[0049] To join the two skin sections 1, 2, a first joining head 5 is guided along the first joint 3 on the outer surface of the fuselage assembly 4. A second joining head 6 is guided along the first joint 3 on the inner surface of the fuselage assembly 4. This second joining head 6 is guided within the circumferentially closed fuselage assembly 4 along the longitudinal guide means 7 formed by the component 22.

[0050] To guide the second joining head 6 along the components 22 designed as longitudinal guide means 7, a substructure 21 is provided which is designed to correspond to the components 22 and is coupled to the second welding head 6.

[0051] In the illustrated embodiment, the coupling comprises a motorized actuator 19, which is designed here purely as an articulated arm. Other designs of coupling the base 21 to the second welding head 6, in particular non-motorized couplings, are possible.

[0052] In the illustrated embodiment, the first joining head 5 and the second joining head 6 are guided simultaneously parallel along the first joint 3 for joining the first and second skin sections 1, 2, so that they jointly exert a joining effect on the first joint 3, as indicated by the wavy lines in the region of the joint 3.

[0053] The joining heads 5, 6 can have a wide variety of 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 sections 1, 2 are formed with a weldable material, at least in the area of ​​the joint 3. For example, a weldable material of a skin section can contain a thermoplastic. In particular, it can be a fiber composite material with a thermoplastic matrix.

[0054] Fig. 2 shows a schematically illustrated arrangement for joining two skin sections 1, 2 of a circumferentially closed fuselage according to a further embodiment.

[0055] According to this embodiment, the second skin section 2 is positioned with a second joint 8 between the second skin section 2 and the first skin section 1 in addition to the first joint 3. The first and second joints 3, 8 are arranged on opposite sides of the fuselage assembly 4.

[0056] The two skin sections 1, 2 are each designed as half-shells, each describing one half of a fuselage cross-section and thus forming one half of the fuselage assembly 4.

[0057] The skin sections 1, 2 are equipped or pre-assembled with components before the skin sections are joined, in particular with a cabin lining (not shown individually), a cabin floor 15 and other interior systems.

[0058] In the illustrated embodiment, the interior systems are pre-installed in the second skin section 2 and are intended to remain later in the finished fuselage.

[0059] A joining device 20 provided for joining the first and second skin sections 1, 2 has, in addition to the Fig. 1, the components shown have an outer support device 24. The outer support device serves, among other things, to position the skin sections 1, 2.

[0060] 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 outer surface of the fuselage assembly 4 along the second joint 8. The fourth joining head 10 is guided along an inner surface of the fuselage assembly 4 along the second joint 8. For this purpose, the fourth joining head 10 is guided together with the second joining head 6 along common longitudinal guide means 7 arranged within the circumferentially closed fuselage assembly 4.

[0061] The longitudinal guide means 7 are designed here in the form of the seat rails 12, which are arranged in the cabin floor 15. A substructure 21 in the form of a portal running in the seat rails is provided to guide the second and fourth joining heads 6, 10.

[0062] In the illustrated embodiment, the third and fourth joining heads 9, 10 are guided parallel to each other along the second joint 8. Furthermore, the third and fourth joining heads 9, 10 are also guided parallel and at the same height as the first and second joining heads 5, 6.

[0063] With this arrangement, the joining forces acting on the skin sections from the joining heads are mutually supported and thus balanced. Furthermore, the joining forces to be supported by the second joining head 6 and the fourth joining head 10 are mutually supported via the motorized actuator 19 and the substructure 21. Thus, no large lateral forces resulting from the joining forces act on the seat rails 12. This advantageously enables longitudinal guidance of the welding heads 6, 10 in the seat rails 12 without damaging the seat rails 12.

[0064] In the illustrated embodiment, the mounting device 24 is designed, for example, as a gantry supporting the fuselage assembly 4. In addition to the skin sections 1, 2, the mounting device 24 also supports the welding heads 5, 9, which are to be guided along the outside of the fuselage assembly 4. In this case, the first and third welding heads 5, 9 are therefore mounted displaceably along the mounting device 24 in the longitudinal direction of the fuselage, so that they can be guided along the first and second joints 3, 8 during joining.

[0065] A feed device (not shown here) may be provided to guide the first and third welding heads 5, 9 and / or to guide the substructure 21 in the seat rails 12. In particular, this may be a motorized and / or automatic feed device. Preferably, the feed of the first welding head 5, the third welding head 9, and the substructure 21 supporting the second and fourth welding heads are coordinated with one another.

[0066] Fig. 3 shows a schematically illustrated arrangement for joining two skin sections 1, 2 of a circumferentially closed fuselage according to yet another embodiment.

[0067] This embodiment differs from the embodiment according to Fig. 2 in that the longitudinal guide means 7 are designed here in the form of cargo space floor rails 13, in which the substructure 21 is guided. The cargo space floor rails 13 are, in particular, guide and / or anchoring rails arranged in a cargo space, which are provided in the subsequent cargo space for guiding and / or anchoring cargo, in particular freight containers.

[0068] A further difference in this embodiment is that the two joints 3, 8 are not located in a common horizontal plane, but rather in a plane inclined to the horizontal, yet are arranged directly opposite each other on the fuselage assembly 4. Accordingly, the motorized actuators 19, which are preferably designed as multi-axis industrial robots, are aligned at different angles to the horizontal.

[0069] The alignment of the first and second joints 3, 8 shown here can be a continuous alignment along the fuselage or can be merely a local alignment in the cross-sectional plane shown or on an individual fuselage section.

[0070] Fig. 4 shows a schematically illustrated arrangement for joining two skin sections 1, 2 of a circumferentially closed fuselage according to yet another embodiment.

[0071] In contrast to the embodiment according to Fig. 2 and Fig. 3, the longitudinal guide means 7 are designed here in the form of a cargo space floor guide provided within a cargo space. In the illustrated embodiment, this is embodied, for example, in the form of lateral steps 14 extending in the longitudinal direction of the fuselage. The steps 14 can, for example, constitute a boundary of the cargo space. Furthermore, it would be conceivable for other interior components, such as a cabin floor, to be placed or mounted on the steps at a later stage of production.

[0072] The substructure 21 has a correspondingly adapted design. The substructure 21 is thus provided as a portal spanning the cargo space, which, by means of an angle bracket, contacts the steps 14 on two sides and can thus be safely guided along the steps 14.

[0073] A further difference in the embodiment shown here is that the first and second struts 3, 8 are arranged opposite one another in a vertical plane. Thus, a first motorized actuating device 19 extends downward from the substructure 21 into the area of ​​the cargo space where the first strut 3 is located. A second motorized actuating device extends upward from the substructure 21, in particular into the area of ​​a cabin ceiling where the second strut 8 is located.

[0074] Fig. 5 shows a schematic arrangement for joining four skin sections of a circumferentially closed fuselage.

[0075] In contrast to the preceding embodiments, the longitudinal guide means 7 are not formed by an interior system here, but by reinforced primary structural elements 18 extending in the longitudinal direction of the fuselage. The primary structural elements 18 are reinforced stringers, which have a significantly stronger design than the other stringers 27 arranged on the fuselage.

[0076] In the illustrated embodiment, the substructure 21 is suspended from the reinforced primary structural elements 18 extending in the longitudinal direction of the fuselage.

[0077] Furthermore, in contrast to the preceding embodiments, a total of four skin sections 1, 2, 11, 23 are positioned here such that they form a circumferentially closed fuselage arrangement 4. For example, these are skin sections 1, 2, 11, 23 each designed as quarter shells.

[0078] The first joint 3 is provided between a first skin section 1 and a second skin section 2. A second joint 8 is provided between the second skin section and a third skin section 11. Furthermore, a third joint 25 is provided between the third skin section 11 and a fourth skin section 23, and a fourth joint 26 is provided between the fourth skin section 23 and the first skin section 1, completing the circumferentially closed fuselage arrangement 4. The areas of the four joints 3, 8, 25, 26 are shown here with dotted lines merely for better differentiation.

[0079] A further difference from the preceding embodiments is that only one pair of joining heads 5, 6 is provided here, i.e., a first joining head 5 for guidance along the outer surface of the fuselage assembly 4 and a second joining head 6 for guidance along the inner surface of the fuselage assembly 4. The second joining head 6 is coupled to the substructure 21 via a motorized actuator that can be pivoted in all directions, for example in the form of a multi-axis, in particular six-axis, industrial robot.

[0080] The two welding heads 5, 6 are 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 the other. Thus, a total of four work steps are required to join the four joints. Alternatively, the joining can also be performed in a longitudinal position, always circumferentially at each of the joints, so that the substructure is sequentially moved longitudinally when each of the joints 3, 8, 25, 26 has been joined locally in a longitudinal position.

[0081] With this arrangement, which has only one motorized adjustment device 19 and only one second welding head 6 on the substructure 21, the weight and size of the parts of the joining device 20 running within the circumferentially closed fuselage assembly 4 are advantageously reduced. This makes the suspended design of the substructure 21 easier.

[0082] The first skin section 1, on which the reinforced primary structural elements 18 extending in the longitudinal direction of the fuselage or the reinforced stringers are provided, is preferably coupled in a particularly stable manner to the holding device 24 for holding the skin section and the fuselage-inner part of the joining device 20.

[0083] After joining, the reinforced stringers can be used as so-called “superstringers”, i.e. as multifunctional structural elements, for example for cabin or system module installation.

[0084] Fig. 6 shows a schematically illustrated embodiment of a further arrangement for joining skin sections of a fuselage.

[0085] For better clarity, the individual skin sections 1, 2 and joining heads 5, 6 or 5, 6, 9 and 10 are not shown in this schematic representation.

[0086] Optionally or in addition to the components 22 intended to remain in the fuselage later, an externally inserted guide device 17 is inserted into the circumferentially closed fuselage assembly 4 as part of the longitudinal guide means 7. After joining, this can be removed, for example, through an open end 16 of the fuselage assembly 4.

[0087] It is conceivable here to mount the guidance device 17 on the components 22 intended to remain in the fuselage later. Alternatively or additionally, an external mounting for the guidance device 17 can be provided.

[0088] The arrangement shown here is intended for a method for joining skin sections 1, 2; 1, 2, 11, 12 of a circumferentially closed fuselage, in particular for an aircraft or spacecraft, with the following method steps: Providing at least a first skin section 1 and a second skin section 2; Positioning at least the first skin section 1 and the second skin section 2 relative to one another in a first joint 3 such that the skin sections 1, 2; 1, 2, 11, 12 form a circumferentially closed fuselage arrangement 4; Inserting a guide device 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, wherein the second joining head 6 is guided along longitudinal guide means 7 arranged within the circumferentially closed fuselage arrangement 4, which are formed at least partially with the guide device 17;

[0089] To join the final joints, for example orbital joints on the nose of the fuselage, another joining head with a small flexible robot or a caterpillar can then be guided inside the fuselage.

[0090] Alternatively or additionally, other joints, for example the joint for integrating a structure surrounding a door of the fuselage, can be joined, in particular welded, to one or more skin sections.

[0091] According to a further embodiment, the guide device 17 can be assembled within the circumferentially closed fuselage assembly 4 and disassembled again after assembly. In this case, the guide device 17 is designed to be dismantled and / or modular. For example, it can be a dismantled framework formed by struts and couplings.

[0092] Such an arrangement is then provided in particular for a method for joining skin sections 1, 2; 1, 2, 11, 12 of a circumferentially closed fuselage, in particular for an aircraft or spacecraft, with the following method steps: Providing at least a first skin section 1 and a second skin section 2; Positioning at least the first skin section 1 and the second skin section 2 relative to one another in a first joint 3 such that the skin sections 1, 2; 1, 2, 11, 12 form a circumferentially closed fuselage arrangement 4; Building a guide device 17 within 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 assembly 4, wherein the second joining head 6 is guided along longitudinal guide means 7 arranged within the circumferentially closed fuselage assembly 4, which are formed at least partially with the guide device 17; and dismantling the guide device.

[0093] Of course, apart from the design of the longitudinal guide means 7, all features of the preceding embodiments are compatible with this arrangement according to Fig. 6 and the arrangements and methods described in this context.

[0094] Fig.Figure 7 shows an aircraft or spacecraft 28. This is, for example, a commercial aircraft. The aircraft or spacecraft 28 has a fuselage 29, which is manufactured according to one of the methods described above for joining skin sections 1, 2 of a fuselage and with a corresponding joining device 20.

[0095] Although the present invention has been described using preferred embodiments, it is not limited thereto but can be modified in many ways.

[0096] For example, it is also conceivable to guide the welding heads, especially those guided along the inner surface of the fuselage assembly, not parallel to each other along the joints. This way, collision between the welding heads can be avoided, for example, in the case of a reduced working space.

[0097] Furthermore, the longitudinal guide means 7 do not necessarily have to have symmetrically arranged guides. A single guide, for example, a single guide rail or guide structure, may also suffice.

[0098] With each of the methods according to the invention, other types of joints of the skin sections can also be joined, in particular welded, for example for the integration of a structure surrounding a door of the fuselage. List of reference symbols 1 first skin section 2 second skin section 3 first push 4 Fuselage arrangement 5 first joining head 6 second joining head 7 longitudinal guides 8 second push 9 third joining head 10 fourth joining head 11 third skin section 12 seat rail 13 Cargo floor rail 14th level 15 Cabin floor 16 open ending 17 Guide device 18 reinforced primary structural element 19 motorized actuator 20 Joining device 21 Substructure 22 Component 23 fourth skin section 24 Mounting device 25 third push 26 fourth push 27 stringers 28 aircraft or spacecraft 29 Hull

Claims

[1] Method for joining skin sections (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 section (1) and a second skin section (2), wherein at least one of the provided skin sections (1, 2; 1, 2, 11, 12) is equipped with components (12; 13; 14; 18; 22) intended to remain later in the fuselage; Positioning at least the first skin section (1) and the second skin section (2) relative to one another in a first joint (3) so that the skin sections (1, 2; 1, 2, 11, 12) form a circumferentially closed fuselage arrangement (4); guiding a first joining head (5) along the first joint (3) on an outer surface of the fuselage assembly (4); and Guiding a second joining head (6) along the first joint (3) on an inner surface of the fuselage arrangement (4), wherein the second joining head (6) is guided along longitudinal guide means (7) arranged within the circumferentially closed fuselage arrangement (4), which are formed at least partially with the components (12; 13; 14; 18; 22) intended to remain later in the fuselage. [2] Method according to claim 1, characterized by that the first joining head (5) and / or the second joining head (6) is provided as a welding head and welds the first skin section (1) to the second skin section (2) when guided along the first joint (3). [3] Method according to claim 1 or 2, characterized by that the first joining head (5) and the second joining head (6) are guided parallel to each other along the first joint (3) for mutual support of a joining force. [4] Method according to one of the preceding claims, characterized bythat the positioning of the second skin section (2) is carried out with a second joint (8) which is formed between the second skin section (2) and the first skin section (1) or between the second skin section (2) and a third skin section (11). [5] Method according to claim 4, characterized by that a third joining head (9) is guided along the second joint (8) on an outer surface of the fuselage arrangement (4) and a fourth joining head (10) is guided along the second joint (8) on an inner surface of the fuselage arrangement (4), wherein the fourth joining head (10) is guided along longitudinal guide means (7) which are arranged within the circumferentially closed fuselage arrangement (4). [6] Method according to claim 5, characterized bythat the third joining head (9) and / or the fourth joining head (10) is provided as a welding head and, when guided along the second joint (8), welds the second skin section (2) to the first skin section (1) or the third skin section (11). [7] Method according to claim 5 or 6, characterized by that the third joining head (9) and the fourth joining head (10) are guided parallel to each other along the second joint (8) for mutual support of a joining force. [8] Method according to one of claims 5 to 7, characterized by that the first and second joints (3, 8) are arranged on opposite sides of the fuselage assembly (4). [9] Method according to one of claims 5 to 8, characterized by that the third and fourth joining heads (9, 10) are guided simultaneously parallel to the first and second joining heads (5, 6). [10] Method according to one of claims 5 to 9, characterized bythat the second joining head (6) and the fourth joining head (10) are guided along common longitudinal guide means (7). [11] Method according to one of the preceding claims, characterized by that the components (12; 13; 14; 18; 22) intended to remain later in the fuselage are designed as an interior system (12; 13; 14). [12] Method according to claim 11, characterized by that the interior system (12; 13; 14) is designed as at least one seat rail (12) anchored in a cabin floor (15). [13] Method according to claim 11, characterized by that the interior system (12; 13; 14) is designed as at least one loading space floor guide (13; 14). [14] Method according to one of claims 1 to 10, characterized bythat the components (12; 13; 14; 18; 22) intended to remain later in the fuselage are formed with at least one reinforced primary structural element (18) running in the longitudinal direction of the fuselage, which is reinforced and / or enlarged compared to the other primary structural elements running in the longitudinal direction of the fuselage and / or is formed so as to protrude into an interior of the fuselage. [15] Joining device (20) designed for a method for joining skin sections (1, 2; 1, 2, 11, 12) of a circumferentially closed fuselage according to one of claims 1 to 14, comprising: a first joining head (5) which can be guided along a joint (3) on an outer surface of a circumferentially closed fuselage arrangement (4); a second joining head (6) which can be guided along the joint (3) on an inner surface of the circumferentially closed fuselage arrangement (4); and a substructure (21), wherein the substructure (21) is coupled to the second joining head (6) and is designed to be guided along longitudinal guide means (7) arranged within the circumferentially closed fuselage arrangement (4), which are at least partially formed with components (12; 13; 14; 18) intended to remain later in the fuselage.

Images