INSTALLATION SYSTEM AND METHOD FOR INSTALLATION OF A SELF-SUPPORTING TRUSS STRUCTURE

Description

Technical field

[0001] The invention relates to an installation system and a method for installing a self-supporting truss structure in a fuselage of an aircraft and to an aircraft with a self-supporting truss structure installed therein. Technical background

[0002] To secure furnishings in an aircraft fuselage, a large number of holders are often arranged on the inside of the fuselage, each individually tailored to the furnishings to be accommodated. Truss-type systems are also known in which triangular structures are formed to connect PSU units and overhead storage compartments. In aircraft, and particularly larger commercial aircraft with fuselage lengths well over 10 m, certain manufacturing tolerances must always be expected. These tolerances must be taken into account and, if necessary, compensated for in the arrangement of holders and the design of truss-type structures, so that the furnishings arranged on them conform to a clearly defined geometry within the fuselage. The installation of furnishings therefore requires checking and, if necessary, adjusting their alignment.

[0003] DE 10 2017 131 130 A1 discloses a fastening system for attaching components to a fuselage structure in an interior of an aircraft.

[0004] DE 10 2021 102 576 A1 proposes a joint connector for connecting several components, comprising a first at least partially spherically shaped

[0005] Bearing shell with a first radial connection section, at least one second at least partially spherically shaped bearing shell, each with a second radial connection section, wherein the at least one second bearing shell is shaped complementarily to the first bearing shell and is designed to at least partially surround the first bearing shell, so that the first bearing shell and the at least one second bearing shell are movable relative to one another on a spherical surface section about a common center, and wherein the first radial connection section and the second radial connection section are designed to receive a component running in the radial direction.

[0006] DE 10 2019 134 746 A1 proposes a component system for the interior fittings of an aircraft, comprising at least one equipment component, a plurality of component rails, a plurality of guide elements engageable with the component rails and movable relative to the component rails, a plurality of holding elements connected to the guide elements and configured to be coupled to a fuselage structure of the aircraft or the at least one equipment component, and a plurality of locking units arranged on the component rails and / or on the guide elements and configured to lock the guide elements to a respective component rail, wherein at least two of the component rails are arranged on the at least one equipment component or the fuselage structure at a distance and parallel to one another,so that the equipment component can be inserted by means of the component rails onto guide elements or component rails spatially defined in the aircraft and can be locked in an inserted position by the locking units. Summary of the invention

[0007] It is an object of the invention to propose an installation system or a method for installing a truss structure in a fuselage of an aircraft, in which the installation can be carried out as simply as possible with the least possible manual effort and, at the same time, very easily compensated for tolerances.

[0008] This object is achieved by the features of independent claim 1. Advantageous embodiments and further developments can be found in the subclaims and the following description.

[0009] An installation system for installing a self-supporting truss structure with a plurality of interconnected truss elements on a fuselage structure of an aircraft is proposed, wherein the truss structure comprises radially outer closed truss nodes and radially inner detachable connection nodes, the installation system comprising said self-supporting truss structure and a mobile support device movable on a floor of the fuselage with an upper receptacle, a frame for temporarily holding the truss elements in predetermined relative positions to one another, and a movement device arranged on the upper receptacle and holding the frame in a position adjustable relative to the upper receptacle, wherein the movement device is designed to hold the frame in a transport position and any installation position,wherein the frame is further spaced from the upper receptacle in the installation positions than in the transport position, wherein the installation system is designed to move the mobile support device on the floor into a predetermined position within the fuselage and to lock it there, to move the frame into a suitable installation position by means of the movement device, and to lock the at least one lockable connection node by means of a drive arranged on the frame.

[0010] The installation system is to be understood as a system for installing multiple truss elements in a hull structure. The hull structure could comprise hull frames and / or other components designed to give the hull its required shape and strength. The system comprises technical aids for moving, holding, and installing the truss elements. The installation system also comprises the truss structure, but can also comprise all devices arranged on the truss elements that are necessary for the permanent installation of the truss elements. The installation system is suitable for forming a self-supporting truss structure in the hull. According to the invention, this is significantly simplified compared to known installation systems and methods by the devices explained below.

[0011] The self-supporting truss structure is formed by truss elements that extend in various spatial directions and form nodes where they are connected to each other. When installed, the truss structure is arranged on the hull, particularly on the hull frames, and forms a spatial, fixed structure for attaching furnishings and equipment.

[0012] A closed truss node is defined as the node in which the truss elements involved are always connected to each other. Therefore, the closed node cannot be opened or loosened, or at least not without causing damage.

[0013] A detachable connecting node within the meaning of the invention is understood to be a device that can be connected to several truss elements that converge at a node. For example, the detachable connecting node can be connected to three, four, or more truss elements that form an intersection point in the node connector. The connecting node is designed to establish or break a connection with the relevant truss elements. As will be explained in more detail below, the truss structure can be fastened in fuselage-side receptacles or the like, after which the spatial positions of individual truss elements of the truss structure result from tolerance-related fuselage dimensions. Their orientations to one another, which are expressed by angles between individual truss elements, are predetermined to ensure the structural design.The detachable connecting node is designed to compensate for tolerance-related dimensional deviations by locking the truss elements in their orientation.

[0014] A truss element could be a truss bar or another element forming the truss. A truss bar could preferably be a rod-shaped element that can absorb tensile and compressive forces. A truss bar is preferably hollow. It can be made of a metallic material, such as a suitable aluminum alloy. Alternatively, fiber-reinforced plastics are conceivable. Alternatively, plate-like truss elements could be used, or a combination of truss bars and plate-like truss elements, or others. For example, it is conceivable to construct a truss in such a way that a PSU unit or the like forms part of the truss.

[0015] The floor of the fuselage is preferably understood as the floor of the cabin that is formed in the fuselage. The mobile support device can be moved on the floor, preferably in the axial direction within the fuselage, in order to be brought into a predetermined position there. The support device could be actively moved on the floor by an integrated drive or by pulling or pushing. Locking the support device could involve blocking wheels, positively connecting it to a rail, or other measures. The support device could also be designed as a plurality of support devices, in particular a chain of support devices that are coupled to one another. The coupled support devices can be retracted into the fuselage along a common movement path in order to fill a specific part of the axial length of the fuselage and to install a truss structure there.It is also conceivable to provide two such arrangements of support devices, which are simultaneously retracted into the fuselage on the floor in order to install a truss structure on each of two sides of the cabin at the same time.

[0016] The frame for temporarily supporting the truss structure is adapted to the shape and orientation of the truss elements. Preferably, the pre-assembled truss structure can be placed, placed on, or inserted into the frame from above, allowing the frame to hold the truss structure in a desired spatial orientation and to be moved by the movement device.

[0017] The movement device allows the frame to be held in a transport position and any desired installation position. The transport position could be understood as a compacted state of the assembly consisting of the support device, movement device, and frame. The pre-assembled truss structure can therefore be pre-assembled outside the fuselage and placed on the frame, before being moved into the fuselage. At the position determined for installation, the movement device can then, in particular, lift the frame and move it radially outward toward the fuselage.

[0018] The movement device further comprises a drive that can be connected or coupled to a corresponding means of the connecting node in order to selectively lock the connecting node. As explained further below, the truss structure and receptacles on the fuselage structure could be adapted to one another in such a way that the movement device allows the truss structure to engage into receptacles on the fuselage structure on the outside of the cabin, in order to subsequently lock the connecting node with the drive, whereby the truss elements then have a locked position resulting from tolerance-related dimensional deviations.

[0019] Overall, the installation system according to the invention results in a particularly simple, largely fully automated installation of a truss structure in a fuselage, while at the same time tolerance-related dimensional deviations can be compensated.

[0020] In an advantageous embodiment, the connecting node has a plurality of node elements arranged at an angle to one another, each of which can be positively connected to a truss element. Each node element can be connected to one end of a truss element. If the truss elements are hollow, one of the node elements could be inserted into a truss element in order to be positively connected to the truss element. A connecting node could, for example, accommodate two truss elements running in the axial direction, one radial truss element, one vertical truss element, and at least one diagonal truss element. The resulting node elements are arranged at corresponding angles to one another and thus determine the orientation of the truss elements.

[0021] In an advantageous embodiment, the connecting node is rigid. Consequently, the angles of the individual node elements are fixed, thus ensuring a desired alignment of the connected truss elements. This prevents undesired tilting of truss elements running in the axial, radial, and vertical directions.

[0022] In an advantageous embodiment, the connecting node has first form-locking means for each relevant truss element, which are designed to complement second form-locking means on the truss elements, wherein the first form-locking means can be brought into a locking position, in which they engage with the second form-locking means, and into a plug-in position, in which they can be moved towards the second form-locking means, by an actuator provided in the connecting node. The first form-locking means could, for example, comprise a first toothing, and the second form-locking means a corresponding toothing. This design allows the truss elements to be axially movable in the plug-in position and can always be connected to one another in their tolerance-dependent, individual, assumed position by the engagement of the form-locking means.The actuator could, for example, serve to move the first form-locking means on the node connector and thus allow selective engagement with the second form-locking means.

[0023] In an advantageous embodiment, the first form-locking means are displaceable relative to the second form-locking means in the plug-in position and can be locked in the respective position in the locking position. For example, the first form-locking means of the respective node element of the connecting node could be displaceable in the radial direction. For this purpose, a plurality of first form-locking means distributed over a circumference of the node element could be provided, which can be displaced radially outwards or inwards by the actuator on the node element. Second form-locking means could be arranged radially inward in the cavity of the truss element into which the node element can be inserted. By inserting the node element into the truss element and subsequently moving the actuator, the first form-locking means can engage the second form-locking means, thereby locking the respective truss element at the connecting node.

[0024] In an advantageous embodiment, the actuator is connectable to the drive. The connecting node could comprise an engagement element on an outer side that is mechanically connectable to the drive. It may be advisable to design the engagement element in such a way that it is clearly visible whether the actuator is in the locked position or in the plug-in position. For this purpose, the engagement element could be elongated or have an elongated marking and be movable only through a limited angle of, for example, 90° or less. In the locked position, the engagement element could be aligned parallel to a longitudinal axis of the fuselage, for example, and vertically or obliquely to it in a plug-in position. It is advantageous to arrange the engagement element on a side of the truss structure facing away from a fuselage wall in order to ensure good accessibility.

[0025] In an advantageous embodiment, the installation system further comprises a plurality of locking receptacles that can be fastened in the fuselage structure and are designed to receive locking elements from radially outer nodes of the truss structure and to lock them thereto by means of mechanical pressure directed from the respective node onto the respective receptacle. The locking receptacles could in particular be arranged in fuselage frames. The locking receptacles could be designed to guide a locking element that is only roughly aligned with the respective locking receptacle into a locking opening of the respective locking receptacles, such that the respective truss element or node moves into a receiving position of the locking receptacles subject to tolerances. The support device and / or the movement device could be designed to exert the necessary mechanical pressure on the pre-assembled truss structure in order to lock it into the respective locking opening.The frame should therefore be able to hold the pre-assembled truss structure sufficiently firmly so that the force can be transferred to the truss structure.

[0026] In an advantageous embodiment, the frame has several upwardly open receptacles into or onto which the truss elements can be placed. The receptacles are preferably designed to correspond to the lower truss elements of the preassembled truss structure. These can accommodate longitudinally axially and radially aligned truss elements and can be designed, for example, as slots or grooves. It is also conceivable to use a plurality of upwardly open, for example U-shaped, holders into which the preassembled truss structure can be inserted.

[0027] In an advantageous embodiment, a subset of the open receptacles is radially aligned, with the radially aligned receptacles being spring-loaded in the axial direction. The radially aligned receptacles can exert a force on radially aligned truss elements, so that radially outer ends of these truss elements, on which a locking element can be arranged, can be pressed into corresponding receptacles. The spring-loaded mounting prevents tension in the radial truss elements, since tolerance-related different end positions of the radial truss elements can be compensated for by differently compressed springs.

[0028] In an advantageous embodiment, the installation system further comprises at least one transport lock for holding the truss structure in the open receptacles. The transport lock can be, for example, a strap, a Velcro fastener, an adhesive tape, a clip, or another form-fitting, force-fitting, or material-fitting means for securing the pre-assembled truss structure to the frame. The fixation does not need to be particularly tight, allowing the movement device and / or the support device to detach the frame from the truss structure when moving it out of the fuselage.

[0029] The invention further relates to an aircraft comprising a fuselage and a self-supporting truss structure arranged therein, which is realized by means of an installation system according to the preceding description.

[0030] In an advantageous embodiment, the truss structure is arranged on radially outer regions of a passenger cabin to accommodate overhead storage compartments.

[0031] The invention further relates to a method for installing a self-supporting truss structure with a plurality of interconnected truss elements on a fuselage structure of an aircraft, wherein the truss structure comprises radially outer closed truss nodes and radially inner detachable connection nodes, the method comprising the steps of providing a pre-assembled truss structure in the fuselage on a frame which is movably held by a support device via a movement device, moving the support device to a predetermined position within the fuselage, locking the support device, lifting the frame and moving it in the radial direction for alignment with a fuselage structure, locking the outer truss nodes with corresponding locking receptacles on the fuselage structure by urging the truss structure in the axial direction into the locking receptacles,wherein a predetermined alignment of the truss elements to each other is maintained, locking the radially inner connecting nodes, and removing the frame.,

[0032] In an advantageous embodiment, removing the frame comprises lowering the frame, moving the frame in a direction away from the fuselage structure and moving it out of the fuselage. Short description of the characters

[0033] The following examples are described in more detail with reference to the accompanying drawings. The illustrations are schematic and not to scale. Like reference numerals refer to like or similar elements. They show: Fig. 1: A schematic representation of a hull with an installation system arranged therein. Fig. 2: A schematic plan view of a truss structure. Fig. 3: A schematic side view of a connecting node. Fig. 4a: A schematic view of part of the installation system on a hull frame. Figs. 4b-4d: Schematic views of the frame during installation of the truss. Fig. 5a-5b: Various other variants of truss structures in schematic views. Fig. 6a: A schematic representation of the truss approaching receptacles in hull frames. Fig. 6b: A schematic representation of the truss locking into receptacles in hull frames. Fig. 7: A schematic representation according to Fig. 6a with modified open mounts with transport locks. Fig. 8an aircraft. Detailed description of implementation examples

[0034] Fig. 1 shows an installation system 2 in a fuselage 4 of an aircraft. Here, a floor 6 is shown, on which a mobile support device 8 is arranged and movable on the floor 6. For this purpose, the support device 8 has several wheels 10 that rest on the floor 6 and enable wheel-guided movement on the floor 6.

[0035] The support device 8 is designed to be moved, in particular, along a longitudinal axis of the fuselage 4. The support device 8 has an upper receptacle 12 on which a movement device 14 is arranged. This is designed to move a frame 16 in three spatial directions, i.e., in the longitudinal direction of the fuselage 4, in the radial direction, and in the vertical direction. A pre-assembled truss structure 18, which consists of several truss elements 20, is located on the frame 16. The movement device 14 is intended to place the frame 16 and thus the pre-assembled truss structure 18 on the fuselage 4 in such a way that it is or can be permanently fastened there. Overhead storage compartments, PSU units, or other devices can be attached to this.

[0036] Fig. 2 shows a plan view of the truss structure 10. Axial truss elements 20a, radial truss elements 20b, and diagonal truss elements 20c are shown here. Arranged radially outward, i.e., directed toward the fuselage structure 4, are outer nodes 22, each equipped with a locking element 24 that is axially aligned and can be locked in the axial direction. The locking element 24 is designed to be locked into corresponding receptacles (not shown here) on the fuselage frames by mechanical pressure in the axial direction.

[0037] Node connectors 26 are provided radially inward, i.e., facing away from the fuselage structure 4. Each node connector has a plurality of node elements 28 arranged at an angle to one another, which can be connected to truss elements 20. The truss elements 20 can each be displaced along their longitudinal axis on the node element 28. A drive 30 belonging to the system 2 can be coupled via an engagement element 31 to an actuator 32 inside the connecting node 26 and can positively connect or detach the node elements 28 to the truss elements 20.

[0038] If the locking elements 24 are locked into corresponding receptacles on the fuselage frames, the frame 16 is able to align in particular the radial truss elements 20b and the axial truss elements 20a in the desired manner and then to connect the connecting node 26 to the truss elements 20 by means of the drive 30.

[0039] Fig. 3 shows the connecting node 26 in a top view. Here, first positive locking means 34 can be seen, which are designed in the form of toothed elements that can be moved in a radial direction on the node elements 28. Preferably, the actuator 32 is capable of displacing the first positive locking means 34 radially outward as needed.

[0040] By way of example, a modified first form-locking means 36 is additionally arranged on one of the node elements 28, which, instead of a toothing, comprises a plurality of radial projections 38 and wide grooves 40 located therebetween. Corresponding second form-locking means can move slightly in the axial direction through the grooves 40 with sufficient axial force. It is conceivable to use such first form-locking means 36 on only a small number of node connectors 26, for example, on every fourth, fifth, or sixth connecting node 26, in order to allow for a longitudinal axial displacement of truss elements 20a in the longitudinal direction as needed, in order to prevent tensioning of the truss structure 18 during thermal expansion or contraction.

[0041] In Fig. 4a The support device 8 is shown, on which the frame 16 is in a transport position. The pre-assembled truss structure 18 is thus located vertically and radically at a sufficient distance from a fuselage frame 42 and can therefore be moved in the longitudinal axial direction in the fuselage 4. In Fig. 4b This direction of movement, which extends into the plane of the drawing, is shown. The frame 16 has upwardly open receptacles 44 for supporting the truss structure 18, into which the formatted truss structure 18 is inserted.

[0042] In Figur 4c the frame 16 is moved upwards and radially outwards towards the fuselage frame 42, so that outer nodes 22 of the truss structure 18 are guided directly to the fuselage frame 42. After locking, as in Fig. 6b As shown, the truss structure 18 is attached to the fuselage frame 42 and remains there. The drive 30 can then lock the connecting nodes 26 of the truss structure 18. The frame 16 is then moved vertically toward the floor 6 and radially inward to release it from the truss structure 18. The support device 8 can then be moved out of the fuselage 4.

[0043] In Fig. 5a a truss structure 18 with a PSU element 46 integrated therein is shown. In Fig. 5b a different shape of a truss structure 18 is shown. Of course, other truss structures are conceivable that can be installed in the fuselage 4 using the installation system 2.

[0044] Fig. 6a shows the frame 16 in a plan view, with the pre-assembled truss structure 18 lying in the open receptacles 44. Here, it can be seen that a radially aligned receptacle 44a is resiliently mounted on the frame 16 by means of springs 48. Preferably, the radial receptacle 44a is guided on the frame 16 in such a way that it always runs perpendicular to an axial receptacle 44b and the truss elements 20 arranged in both receptacles 44a and 44b are always aligned perpendicular to one another.

[0045] The receptacles 44a and 44b also allow for tolerance compensation in the vertical direction, since the truss elements 20 are mounted in a floating manner therein, as can be seen in the two detailed illustrations in the drawing plane at the top right. By moving the frame 16 in the longitudinal axial direction, the locking elements 24 arranged on the outer nodes 22 reach corresponding locking receptacles 50, which have a tapered inlet area 52 that moves the respective locking element 24 and thus the nodes 22 attached thereto with the respectively connected truss elements 20, so that the locking elements 24 each lock into a locking opening 54.

[0046] Fig. 6b shows the locking process. Due to the spring-loaded mounting of the radial mounts 44a, a tolerance-related dimensional deviation in the longitudinal axial direction can be compensated for by the individual springs 48 compressing more or less strongly depending on the resulting position of the radial mounts 44a while simultaneously exerting a sufficient locking force. Fig. 6b shows a resulting tolerance compensation in the radial direction (dashed lines) and by the differently compressed springs 48 in the longitudinal axial direction.

[0047] By subsequently moving the frame 16 back in the longitudinal axial direction, the springs 48 are relaxed again and by lowering the frame 16, the truss structure 18 is finally released and can be equipped with appropriate devices.

[0048] Fig. 7 depicts slightly modified open receptacles 56 that are open not only upwards but also axially toward a side facing away from the springs 48. The truss structure 18 is secured in the receptacles 56 by several transport locks 58. These could be removed manually once the truss structure 18 is arranged on the fuselage frames 42. However, the transport locks 58 could also be released by retracting the frame 16 and then manually removed from the truss structure 18.

[0049] Fig. 8 shows an aircraft 60 with a fuselage 4 in which a truss 18 is installed by means of an installation system 2.

[0050] Additionally, it should be noted that "comprising" or "having" does not exclude other elements or steps, and "a" or "an" does not exclude a plurality. Furthermore, it should be noted that features or steps described with reference to one of the above embodiments may also be used in combination with other features or steps of other embodiments described above. Reference signs in the claims are not to be considered as limitations. List of reference symbols

[0051] 2Installation system 4Fuselage 6Floor 8Support device 10Wheel 12Upper receptacle 14Movement device 16Frame 18Pre-assembled truss structure 20Truss rod 22Outer node 24Locking element 26Connecting node 28Node element 30Drive 31Engaging element 32Actuator 34First form-locking means 36Modified first form-locking means 38Radial projection 40Groove 42Fuselage bulkhead 44Open receptacle 46PSU element 48Spring 50Locking receptacle 52Inlet area 54Locking opening 56Open receptacle 58Transport lock 60Aircraft

Claims

1. Installation system (2) for installing a self-supporting truss structure on a fuselage structure (42) of an aircraft (60), the installation system (2) comprising: a truss structure (18) with a plurality of interconnected truss elements (20, 46), a mobile carrying device (8) movable on a floor (6) of the fuselage (4) with an upper receptacle (12), a rack (16) for temporarily holding the truss elements (20, 46) in predetermined relative positions to one another, and a movement device (14) which is arranged on the upper receptacle (12) and holds the rack (16) in a position that is adjustable relative to the upper receptacle (12), the truss structure (18) comprising radially outer closed truss nodes (22) and radially inner releasable connecting nodes (26), the movement device (14) being designed to move the rack (16) in one transport position and any installation position, the rack (16) being spaced further from the upper receptacle (12) in the installation positions than in the transport position, the installation system (2) being designed to move the mobile carrying device (8) on the floor (6) into a predetermined position within the fuselage (4) when the rack (16) is in the transport position and to lock it there, to move rack (16) by means of the movement device (14) into a suitable installation position and to lock the at least one lockable connecting node (26) by means of a drive (30) arranged on the rack (16).

2. Installation system (2) according to claim 1, wherein the connecting node (26) has a plurality of node elements (28) arranged at an angle to one another, each of which can be positively connected to a truss element (20, 46).

3. Installation system (2) according to claim 1 or 2, wherein the connecting node (26) is rigid.

4. Installation system (2) according to claim 2, wherein the connecting node (26) has first positive locking means (34) for each relevant truss element (20, 46), which are designed to complement second positive locking means on the truss elements (20, 46), and wherein the first positive locking means (34) are brought into a locking position by an actuator (32) provided in the connecting node (26), in which they are in the second positive locking means intervene, and can be brought into a plug-in position in which they can be moved to the second positive locking means.

5. Installation system (2) according to claim 4, wherein the first positive locking means (34) can be displaced in the plug-in position relative to the second positive locking means and can be locked in the respective position in the locking position.

6. Installation system (2) according to claim 4 or 5, wherein the actuator (32) can be connected to the drive (30).

7. Installation system (2) according to one of the preceding claims, further comprising a plurality of locking receptacles (50) which can be fastened in the fuselage structure (42) and are designed to receive locking elements (24) from radially outer nodes (22) of the truss structure (18) and to lock therewith by mechanical pressure directed from the relevant node (22) to the respective locking receptacle (50).

8. Installation system (2) according to one of the preceding claims, wherein the rack (16) has a plurality of upwardly open receptacles (44, 56) into or onto which the truss elements (20, 46) can be brought.

9. Installation system (2) according to claims 7 and 8, wherein a subset of the open receptacles (44, 56) are radially aligned, the radially aligned open receptacles (44, 56) being spring mounted in the axial direction.

10. Installation system (2) according to one of claims 7 to 9, further comprising at least one transport lock (58) for holding the truss structure (18) in the open receptacles (44, 56).

11. Aircraft (60), having a fuselage (4) and a self-supporting truss structure (18) arranged therein, which is realized by means of an installation system (2) according to one of the preceding claims.

12. Aircraft (60) according to claim 11, wherein the truss structure (18) is arranged on radially outer regions of a passenger cabin to accommodate overhead storage compartments.

13. Method for installing a self-supporting truss structure (18) with a plurality of interconnected truss elements (20, 46) on a fuselage structure (42) of an aircraft (60), the truss structure (18) comprising radially outer closed truss nodes (22) and radially inner detachable connecting nodes (26), the method comprising the steps: - Providing a pre-assembled truss structure (18) in the fuselage (4) on a rack (16), which is movably held by a carrying device (8) via a movement device (14), - Moving the carrying device (8) to a predetermined position within the fuselage (4), - Locking the carrying device (8), - Lifting the rack (16) and moving in the radial direction to align it with a fuselage structure (42), - Locking the outer truss nodes (22) with corresponding latching receptacles (50) on the fuselage structure (42) by urging the truss structure (18) in the axial direction into the latching receptacles (50), whereby a predetermined alignment of the truss elements (20, 46) to one another is maintained, - Locking the radially inner connecting nodes (26), and - Remove the rack (16).

14. The method of claim 13, wherein removing the rack (16) includes lowering the rack (16), moving the rack (16) in a direction away from the fuselage structure (42), and moving out of the fuselage (4).