ASSEMBLY SYSTEM AND METHOD FOR ASSEMBLY OF AIRCRAFT SYSTEM COMPONENTS IN THE TRIANGLE AREA

Description

[0001] The invention relates to an assembly system and method for assembling aircraft system components in a triangular area in the lower deck of an aircraft. In particular, the invention relates to an assembly system and method for assembling aircraft system components with a support structure that can be inserted in the longitudinal direction of the triangular area.

[0002] In the lower deck of an aircraft, such as a cargo deck, i.e., in the area of ​​the fuselage below a mezzanine floor, there are usually two so-called triangular areas. In a cross-sectional view of the aircraft, these are defined by the outer structure of the fuselage (e.g., frames and stringers), the cross members of the mezzanine floor (e.g., the mezzanine beams), and so-called Z-struts, which usually run vertically between a mezzanine floor beam and a frame, and are usually located on both sides of the aircraft. The Z-struts serve primarily to support the mezzanine floor in the vertical direction and to stiffen the aircraft structure below the mezzanine floor.

[0003] The usually relatively rectangular space between the opposing Z-struts is typically used as cargo space or installation space for aircraft equipment. The triangular areas, on the other hand, are often used to route cables along the exterior structure of the fuselage or longitudinally of the aircraft. Typically, no obstructive components are located in the triangular areas, especially in the transverse direction of the aircraft, allowing cables to be routed from the nose to the tail of the aircraft, or at least from the wings to the nose or tail of the aircraft, within the triangular areas.

[0004] However, the work area is difficult for personnel to access during installation in the triangular areas. On the one hand, the Z-braces are in the way of installing cables in the triangular area. On the other hand, the intermediate floor limits the working height. Both of these factors lead to ergonomically unfavorable conditions for personnel.

[0005] An attempt was made to attach the cables to the aircraft's external structure before installing the Z-struts. However, this means that in this state, the intermediate floor either cannot be installed or cannot be loaded. Removal of the upper deck must therefore wait until the Z-struts are installed. On the other hand, due to the load transfer and the distance to the outer skin, it is desirable to attach cables to the Z-struts to avoid attaching all the brackets to the aircraft's external structure. Therefore, installing cables after the Z-struts have been installed is preferable.

[0006] A corresponding assembly system and method is known from document EP3838743A1.

[0007] The invention is therefore based on the object of providing a system and method for improved assembly of aircraft system components.

[0008] This object is achieved by an assembly system having the features of claim 1 and a method having the features of claim 12.

[0009] According to a first aspect for a better understanding of the present disclosure, a mounting system for mounting aircraft system components in a triangular area in a lower deck of an aircraft comprises the following components: an elongated support structure, a guide device which is fastened to the support structure and is configured to guide the support structure, and at least one holder which is fastened to the support structure and is configured to releasably hold an elongated aircraft system component.

[0010] The aircraft contains at least one triangular section in the lower deck. Typically, one triangular section is present on each side of the aircraft along the longitudinal axis of the aircraft. These are defined in a cross-sectional view of the aircraft by the external structure of the fuselage (e.g., the frames and / or stringers), the cross members of the mezzanine floor (e.g., the mezzanine beams) or the mezzanine floor itself, and so-called Z-braces, which support a mezzanine beam (or the mezzanine floor itself) on a frame and are usually vertical. They are usually located on both sides of the aircraft.

[0011] The triangular area extends over a certain length within the aircraft, which is why this extension is also referred to as the longitudinal direction of the triangular area. In certain aircraft configurations, for example, the so-called low-wing configuration, the triangular area is interrupted by a wing center box and / or a main landing gear well. The longitudinal direction of the triangular area is generally parallel to the longitudinal direction of the aircraft (for example, the central axis from the nose to the tail of the aircraft). Since the triangular area is also defined by the width and / or external structure of the aircraft, and these can also be curved, the longitudinal direction of the triangular area in these areas can deviate from or be oblique to a longitudinal direction (longitudinal axis) of the aircraft. The longitudinal direction of the triangular area is therefore understood to be a direction that runs along the external structure of the aircraft and / or along the Z-struts.

[0012] An elongated aircraft system component is a component that is larger / longer in one direction than in others. In particular, lines fall under such elongated aircraft system components. For example, lines for conditioned air, exhaust air, ram air, bleed air, hydraulics, electrical systems, water, wastewater, etc. can be laid in the triangular areas. These lines typically have a length that (significantly) exceeds the distance between two adjacent frames or Z-struts in the longitudinal direction of the triangular area. In particular, these elongated aircraft system components can have a length that spans a plurality of Z-struts, i.e., can be laid along the plurality of Z-struts.

[0013] Of course, even short (longitudinally) aircraft system components can be held by at least one bracket. However, components shorter than the distance between two Z-struts are also easier to install. In any case, all aircraft system components can be pre-assembled to the support structure, outside the fuselage, creating optimal ergonomic conditions.

[0014] The mounting system further comprises a guide rail configured to be inserted into a section of the triangular region and in the longitudinal direction of the triangular region. The section of the triangular region is defined by the frames and / or the Z-struts and / or a cross member or support of the intermediate floor. It can, for example, be a lower region of the triangular region. The section can therefore, for example, be an area on the frames or an area in which the Z-struts are attached to the respective frame, are integrated therein, or otherwise cross / touch the area of ​​the frames. Of course, it can alternatively or additionally be an upper and / or lateral area of ​​the triangular region.

[0015] The guide device is designed to be moved along the guide rail. For example, the guide device can be moved within the guide rail, with movement occurring in particular in the longitudinal direction of the triangular area. Guidance by the guide rail therefore primarily involves support transverse to the longitudinal direction of the guide rail and thus transverse to the longitudinal direction of the triangular area.

[0016] Furthermore, the support structure is dimensioned such that the support structure can be inserted into the triangular area in the longitudinal direction of the triangular area by means of the guide device and the guide rail. In other words, the support structure has a cross-section that is smaller than the cross-section of the triangular area, so that the support structure can move through the cross-section of the triangular area while being guided by the guide rail and guide device.

[0017] Finally, at least one section of the support structure is configured to be moved in a direction perpendicular to the longitudinal direction of the support structure. This can be a linear movement, a circular movement, or a movement along any desired path. The section of the support structure that can be moved transversely enables the at least one mount (or at least one mount if there are multiple mounts) to be moved, thereby also moving the aircraft system component attached thereto. This allows the aircraft system component to be aligned within the triangular region, while having a compact cross-section when inserted into the triangular region with the support structure.

[0018] In order to enable assembly of the aircraft system component in the triangular region, the guide rail and guide device serve to align the aircraft system component in the longitudinal direction of the triangular region and the movement of at least one section of the support structure serves to align the aircraft system component in the transverse direction of the triangular region.

[0019] The movement of at least one section of the support structure can be designed such that the aircraft system component is brought into its final position within the cross-section of the triangular region. For example, the movement of the at least one section can comprise a horizontal and / or vertical movement component, so that the aircraft system component can be moved into (almost) any desired position within the cross-section of the triangular region.

[0020] Finally, the aircraft system component can be attached within the triangular area. For example, the aircraft system component can be attached to the exterior structure of the aircraft fuselage, e.g., a bulkhead and / or stringer, to a transverse spar of the intermediate floor, e.g., a beam of the intermediate floor or the intermediate floor itself, and / or to a Z-brace.

[0021] In one embodiment, the support structure can comprise at least one longitudinal beam and a plurality of vertical beams. The at least one longitudinal beam extends in the longitudinal direction of the triangular region, while the plurality of vertical beams are each arranged perpendicular to it and essentially vertically. The at least one longitudinal beam distributes the loads of the mounting system in the longitudinal direction and onto the guide device.

[0022] In another embodiment, the at least one mount can be attached to the plurality of vertical supports. The plurality of vertical supports therefore primarily serves to enable the at least one mount to be arranged at any (arbitrary) vertical position within the cross-section of the triangular region, so that the aircraft system component held thereby is in or near its end position within the cross-section of the triangular region. Furthermore, a vertical support also enables the arrangement of multiple aircraft system components one above the other.

[0023] In a further embodiment, the at least one section of the support structure can be a vertical support of the plurality of vertical supports, which is movable in the direction perpendicular to the longitudinal direction of the support structure. In other words, a vertical support is moved in a plane parallel to a cross-section of the triangular region. This enables movement of an aircraft system component within the triangular region. The movement of the vertical support can be any desired movement, such as a linear movement, a circular movement, an elliptical movement, or a movement along any desired path.

[0024] In yet another embodiment, one vertical support can be connected to another vertical support of the plurality of vertical supports via a joint and a spreading device, and can be rotated relative to the other vertical support. The joint forms a pivot point for the rotational movement of the vertical support. The spreading device can be any device whose length is variable and arranged such that its length determines a distance between the vertical support and the other vertical support. This distance determines an arc length by which the one vertical support is rotated relative to the other vertical support around the joint.

[0025] Alternatively or additionally, one vertical support can be connected to a longitudinal support via a joint and rotated relative to the longitudinal support. The same conditions apply as above for the rotational movement of one vertical support relative to another vertical support, with the longitudinal support forming the fixed element instead of the other vertical support.

[0026] Alternatively or additionally, the additional vertical beam and / or the longitudinal beam can also be rotated about the joint. In other words, the movement of the support structure is not limited to the rotational movement of the single vertical beam, but rather several elements of the support structure can be rotated (in a cross-sectional view of the triangular area). This enables a compact arrangement of the support structure with the attached aircraft system components and flexible movement and alignment of the aircraft system component(s) within the triangular area.

[0027] In another design variant, the supporting structure can comprise at least one cross member whose length can be adjusted transversely to the longitudinal direction of the supporting structure. A cross member here means that it is located in a cross-sectional plane of the triangular area, with the change in the length of the cross member occurring within this plane. This does not necessarily have to be a linear extension; it can also be circular, elliptical, or any desired change between the start and end points of the cross member.

[0028] In yet another embodiment, a mount of the at least one mount can be arranged at a free end of the at least one cross member. Thus, by changing the length of the cross member, the mount, and thus an aircraft system component held thereon, can be arbitrarily changed in position within the cross section of the triangular region. For example, the aircraft system component can be brought into its final position within the triangular region.

[0029] In one embodiment, the mounting system may further comprise an additional guide rail configured to be arranged in a different section of the triangular region than the (already described) guide rail, and an additional guide device configured to be moved along the additional guide rail and to guide the support structure. For example, a movement may take place in the longitudinal direction of the triangular region.

[0030] The first guide rail described can be arranged, for example, in a lower or lateral section of the triangular area. The second guide rail can be arranged, for example, in an upper or lateral section of the triangular area.

[0031] The lower and upper guide rails are optimized for vertical support of the mounting system's load and for supporting force components transverse (horizontal) to the longitudinal direction of the respective guide rail, and thus transverse to the longitudinal direction of the triangular area. A lateral guide rail enables lateral guidance from the outset, thus providing support against transverse (horizontal) forces, while vertical load components must be introduced into the respective guide rails by other means.

[0032] In each case, the support structure is held in place transversely within the triangular area by the guide rail and the additional guide rail, while the support structure can be easily moved longitudinally within the triangular area. In other words, the support structure is secured against tipping, facilitating its insertion into the triangular area.

[0033] Of course, the assembly system can also be securely inserted into the triangular area using only one guide rail and guide device. For example, the assembly system can be designed so that its center of gravity (including the attached elongated aircraft system component(s)) is located above a guide rail in the lower section of the triangular area. This makes it more difficult for the entire assembly system to tip over and facilitates insertion into the triangular area.

[0034] The mounting system can also be equipped with only the guide rail and guide device in the upper section of the triangular area, with the supporting structure and thus the mounting system suspended from the upper guide rail. This eliminates the problem of the mounting system tipping over.

[0035] In a further embodiment, the at least one mount can have a receiving surface that corresponds to a portion of an outer surface of an aircraft system component. The receiving surface can therefore take any shape determined by the portion of the outer surface of the aircraft system component. Thus, the receiving surface and the surface of the aircraft system component can be a section of a cylinder, a sphere, a cuboid, a cube, a polygon, or any other shape.

[0036] Of course, the mounting surface can also be made of or coated with an elastic material. This makes it easier to pick up and hold the aircraft system component, while also protecting it.

[0037] In yet another embodiment, the mounting surface can be designed such that it contacts the aircraft system component at a location in the longitudinal direction of the component where the aircraft system component is not (finally) attached in the triangular area. Thus, the mounting surface, and in particular the bracket, does not hinder the final assembly of the aircraft system component.

[0038] In a further embodiment, the at least one holder can comprise a hook-and-loop fastener strip configured to hold or grip the aircraft system component. This allows the aircraft system component to be releasably attached to the holder and thus to the support structure.

[0039] Alternatively or additionally, the at least one holder can comprise a clip configured to releasably hold the aircraft system component. The clip is a holder with a clamping function and / or a snap-in function, wherein at least one section of the clip deforms elastically as the aircraft system component is pushed into the clip, and then encloses the aircraft system component at least in part.

[0040] In any case, the bracket may be attached to the aircraft system component in such a way that it does not interfere with a final assembly position of the aircraft system component. By way of example only, the bracket and / or a vertical support to which the bracket is attached may be spaced apart from a bulkhead or Z-brace in the longitudinal direction of the triangular region. Typically, the brackets for final assembly of the aircraft system component are provided on a bulkhead or Z-brace (or a cross member of the intermediate floor).

[0041] In yet another embodiment, the assembly system can further comprise a two-part assembly device, wherein a first part of the assembly device is configured to be attached to and support the aircraft system component, and a second part of the assembly device is configured to be attached to a Z-strut, a cross member (support) of the intermediate floor, or a frame of the aircraft. This allows a part of the assembly device to be attached to the aircraft system component before it is inserted into the triangular area with the support structure. This facilitates the final assembly of the aircraft system component.

[0042] In one embodiment, the two-part mounting device can comprise a plug connection, a snap-in connection, a rail connection, a screw connection and / or a clamping connection.

[0043] Here, the two-part assembly device can be designed such that the two parts of the assembly device are brought together in a direction (to reach the final assembly position) that corresponds to a direction of movement that the aircraft system component performs when moving the section of the support structure perpendicular to the longitudinal direction of the support structure. In other words, by moving the section of the support structure, the aircraft system component is not only brought into its final position, but also simultaneously brings corresponding parts of an assembly device together or into one another.

[0044] This significantly simplifies and accelerates the assembly of the aircraft system component, as the aircraft system component is moved into its final assembly position in a single step. Especially when multiple aircraft system components are held on the support structure, all of which are moved into their final assembly position at once by moving the section of the support structure, the assembly of the aircraft system components is significantly simplified and accelerated.

[0045] According to a second aspect for better understanding of the present disclosure, a method for mounting an aircraft system component in a triangular area in a lower deck of an aircraft comprises the following steps: Inserting a guide rail into a section of the triangular region and in the longitudinal direction of the triangular region; Providing a support structure comprising a guide device and at least one holder; Attaching an elongated aircraft system component to the at least one holder; Pushing the support structure into the triangular region in the longitudinal direction of the triangular region by moving the support structure along the guide rail by means of the guide device; Moving at least one section of the support structure in a direction perpendicular to the longitudinal direction of the support structure such that the elongated aircraft system component is brought into a final assembly position within the triangular region; Fastening the aircraft system component to at least one primary structural component of the aircraft forming the triangular region; Detaching the aircraft system component from the at least one holder;and moving the supporting structure out of the triangular area. ;

[0046] The method can be carried out using a mounting system according to the first aspect or one of its design variants, or a combination of these variants. Thus, the statements made for the first aspect apply equally to the method according to the second aspect.

[0047] In one embodiment, the method may further comprise attaching a first part of a mounting device to the aircraft system component and attaching a second part of the mounting device to a Z-strut, a cross member (beam), or a frame of the aircraft. Attaching the aircraft system component may comprise connecting the first and second parts of the mounting device.

[0048] This connection can also take place simultaneously with the movement of at least one section of the support structure or by the movement of at least one section of the support structure.

[0049] In a further embodiment, the method may further comprise removing the guide rail from the triangular area.

[0050] The aspects, embodiments, variants, and examples described above can, of course, be combined without this being explicitly described. Each of the described embodiment variants and each example is thus to be considered optional to each of the aspects, embodiments, variants, and examples, or even combinations thereof. The present disclosure is therefore not limited to the individual embodiments and embodiment variants in the described order or to a specific combination of the aspects and embodiment variants.

[0051] Preferred embodiments of the invention will now be explained in more detail with reference to the accompanying schematic drawings, in which: Figure 1 schematically shows a section of a lower deck of an aircraft with two triangular areas; Figure 2 schematically shows a side view of an assembly system; Figure 3 schematically shows a cross-sectional view of an assembly system in a triangular area; Figure 4 schematically shows a cross-sectional view of an aircraft system component with assembly device; Figure 5 schematically shows a cross-sectional view of a further assembly system in a triangular area; Figure 6 schematically shows a cross-sectional view of yet another assembly system; and Figure 7 schematically shows a flow diagram of a method for assembling an aircraft system component.

[0052] Figure 1shows schematically a section of a lower deck 8 of an aircraft 1 with two triangular areas 3. The lower deck 8 of the aircraft 1 refers to a section of the aircraft 1 which is arranged at the bottom in the cross-section of the aircraft 1, such as the cargo deck, as shown in Figure 1with a cargo floor 6. The cargo deck 8 is limited at the top by an intermediate floor 11, which is, for example, a cabin floor of a passenger cabin arranged above. While cross members or beams 10 of the intermediate floor 11 span the cross-section of the aircraft 1, supporting the beams 10 via Z-struts 12 is static and also useful to prevent vibrations. These Z-struts 12 are attached to the bottom of the cross members or beams 10. For easy attachment, the cross members or beams 10 have the same grid as the frames or frames 5 of the aircraft 1, with the cross members or beams 10 also being attached at their ends to a frame or frame 5 of the aircraft 1. The Z-struts 12 are thus arranged at their lower end above a frame or frame 5, so that they can also be attached to the frame or frame 5.

[0053] These three components (cross member 10, frame 5, and Z-strut 12) surround (define) a triangular region 3 in the cross-section of the aircraft 1. This region has an essentially triangular shape, with a curve in the fuselage usually present on the side of frame 5. Such a triangular region 3 is usually present on both sides of the aircraft 1 or at both ends of the cross member or support 10.

[0054] Aircraft system components 21, 22 (collectively designated 20) are accommodated in at least one of these triangular regions 3. These elongated aircraft system components 20 extend substantially along the longitudinal direction of the triangular region 3. This longitudinal direction of the triangular region 3 is determined by the alignment of the Z-struts 12 or the frames 5. Typically, this longitudinal direction corresponds to the longitudinal direction X of the aircraft 1. However, the cross-section of the aircraft 1 can also change (e.g., taper), whereby the longitudinal direction of the triangular region 3 can extend obliquely to the longitudinal axis X of the aircraft 1.

[0055] Furthermore, a vertical direction (in the cross-section of the aircraft 1) corresponds to a Z-axis (vertical axis), while a horizontal direction (in the cross-section of the aircraft 1) corresponds to a Y-axis (horizontal axis). These two axes are perpendicular to the longitudinal axis X of the aircraft 1. The Z-struts 12 can be arranged vertically, i.e. aligned parallel to the Z-axis. Alternatively, the Z-struts 12 can also be aligned obliquely to the Z-axis. Advantageously, however, the Z-struts 12 lie in the cross-sectional plane, i.e. in the YZ plane, in which a frame 5 is usually also arranged.

[0056] As in Figure 1As shown, the aircraft system components 20 are arranged behind the Z-struts 12 when viewed from the center of the aircraft 1. This makes the aircraft system components 20 difficult to access. The Z-struts 12 can be an obstruction, particularly during installation of the aircraft system components 20.

[0057] Figure 2 shows schematically a side view of an assembly system 100 which facilitates the assembly of aircraft system components 20. The assembly system 100 comprises an elongated support structure 110, a guide device 120 and at least one holder 130 which is arranged with respect to the Figures 3 to 6 will be described in more detail.

[0058] The elongated support structure 110 may, for example, comprise one or more longitudinal beams 111, 113 extending over the length of the support structure 110. Vertical beams 112, 114 may be arranged between them, forming a frame with the longitudinal beams 111, 113. This frame provides a stable structure for attaching aircraft system components 20 to it.

[0059] The guide device 120 is shown in the form of a plurality of rollers 120. Of course, other forms of guide devices 120 can be used, for example, sliders, rollers, balls, or the like.

[0060] The mounting system 100 can be moved in the longitudinal direction of the support structure 110 (for example in the longitudinal direction X) in order to be inserted into a triangular area 3, for example.

[0061] Figure 3shows a schematic cross-sectional view of a mounting system 100 in a triangular region 3, for example, while the mounting system 100 is being inserted into the triangular region 3. For this purpose, the mounting system 100 further comprises a guide rail 125, which is inserted, for example, in a lower section of the triangular region 3.

[0062] The guide device 120 can now be moved along the guide rail 125. For example, the guide rail 125 can have a U-shaped profile in which the guide device 120 can slide or roll. The vertically arranged legs of the U-shaped profile serve to provide lateral support for the guide device 120, while the support structure 110 is inserted into the triangular area 3 along the guide rail 125.

[0063] The supporting structure 110 is dimensioned in such a way that it fits into the cross-section of the triangular area 3 and can be inserted therein. In other words, and as in Figure 3 As shown, the occupied cross-section of the support structure 110 is smaller than the cross-sectional area of ​​the triangular region 3. The occupied cross-section also includes the aircraft system components 20, which are detachably attached to the support structure 110.

[0064] As from Figure 3 and also Figure 4 As can be seen, the mounting system 100, in particular the support structure 110, has at least one holder 130 (holder 134 for component 24 in Figure 4), on which (in each case) an elongated aircraft system component 20 is releasably held. For this purpose, each holder 130 has, for example, a receiving surface that corresponds to a portion of an outer surface of an aircraft system component 20. In order to hold the aircraft system component 20 in this receiving surface, the holder 130 can further comprise a releasable fastening element 135. The releasable fastening element 135 can, for example, be a hook-and-loop strip 135 that grips around the aircraft system component 20. The hook-and-loop strip 135 can be guided through a loop (not shown) and hooked onto itself in order to releasably hold the aircraft system component 20 on the holder 130.

[0065] Alternatively or additionally, the holder 130 may have a clip 136 (see Figure 6) into which the aircraft system component 20 is releasably inserted. In particular, an elastic deformation of the clip 136 is used to hold (clamp) the aircraft system component 20. The elasticity of the clip 136 enables easy insertion and removal of the aircraft system component 20 into and from the holder 130.

[0066] In Figure 3 The mounting system 100 is shown in such a way that several brackets 130 are attached to the vertical support 112, 114. This allows several aircraft system components 20 to be arranged one above the other and inserted into the triangular area 3.

[0067] Furthermore, Figure 3a mounting system 100 with two vertical supports 112, 114, wherein a vertical support 112 represents a portion of the support structure 110 that is movable in a direction perpendicular to the longitudinal direction of the support structure 110. The longitudinal direction of the support structure 110 is also the longitudinal direction of the triangular region 3 when the support structure 110 is inserted into the triangular region 3. In Figure 3 the movement of the vertical support 112 is represented by a double arrow, whereby an angle Δ between one vertical support 112 and another vertical support 114 can be changed.

[0068] For example only, one vertical support 112 can be connected to the other vertical support 114 via a joint 118 and can rotate about the joint 118 relative to the other vertical support 114. The (arc) distance between the two vertical supports 112, 114 can be achieved via a spreading device 116 or via any element whose longitudinal extent can be varied. The spreading device 116 can, for example, be a threaded rod with a nut that can be rotated by a motor, but also an actuator (electrically, pneumatically, and / or hydraulically operated) or a linear motor.

[0069] Instead of the joint 118, one vertical support 112 can also be attached to the other vertical support 114 via two spreading devices 116. This allows the two vertical supports 112, 114 to move relative to each other, whereby tilting movements of one or both vertical supports 112, 114 (in the cross-sectional plane shown) are also possible.

[0070] The movement of the vertical support 112 or both vertical supports 112, 114 can be easily performed by appropriate personnel once the support structure 110 is fully inserted longitudinally into the triangular region 3. For example, one or more spreading devices 116 can be attached to one or both ends of the support structure 110. This allows the corresponding spreading device 116 to be operated at one or two positions on the support structure 110. This is significantly easier to accomplish than threading all aircraft system components 20 between the Z-struts 12 and attaching them to the corresponding mounting devices.

[0071] Both the vertical supports 112 and the further vertical supports 114 can be connected to each other by longitudinal supports 111, 113, forming a frame. Therefore, one or a few spreader devices 116 are sufficient to move the two frames relative to each other.

[0072] Figure 4 shows schematically a cross-sectional view of an aircraft system component 24 with mounting device 64, which for each aircraft system component 20 in Figure 3 is shown schematically, but is only described for one aircraft system component 24. The description applies equally to the other aircraft system components 21, 22, 23.

[0073] The aircraft system component 24 is attached to the bracket 134 with a hook-and-loop fastener 135. Furthermore, a first part 64a of a mounting device 64 is attached to a Z-strut 12. The mounting device 64 can be a final mounting device for the aircraft system component 24. A second part 64b of the mounting device 64 is attached to the aircraft system component 24 and is configured to support it. If possible, the second part 64b of the mounting device 64 is attached at a different position in the longitudinal direction of the aircraft system component 24 than the hook-and-loop strip 135 so that the hook-and-loop strip 135 can be released independently of the mounting device 64.

[0074] Again with reference to Figure 3By means of a relative movement between the vertical supports 112, 114, it is not only possible to move the aircraft system component 21 to the left, but also to move the aircraft system components 22, 23, 24 to the right. This movement is in Figure 4 represented by the arrow in the direction of the Y-axis. In the variant shown, the mounting device 64 for the aircraft system component 24 comprises two receptacles in the first part 64a and two corresponding pins in the second part 64b. The receptacles and pins are aligned such that the pins can be inserted into the receptacles. The direction of movement for inserting the pins into the respective receptacle is selected such that it coincides with the direction of movement of the aircraft system component 24 during the movement of the vertical support 114. As a result, the aircraft system component 24 can be mounted merely by moving the vertical support 114.

[0075] Of course, the mounting device 64 can subsequently be supplemented with a screw, locking pin, or similar connector for the final assembly of the aircraft system component 24, whereby the two parts 64a, 64b of the mounting device 64 are firmly connected to one another. Finally, the aircraft system component 24 is mounted in its final position.

[0076] The remaining aircraft system components 20 are mounted in their final position by corresponding mounting devices 61, 62, 63, whereby these mounting devices 61, 62, 63 can also consist of two parts. Due to the different arrangement of the aircraft system components 21-24 and the mounting devices 61-64, the respective second part of these mounting devices 61-64, which is fastened to the aircraft system component 21-24, can perform a different relative movement to the first part of the respective mounting devices 61-64, which is fastened to an aircraft structure 5, 10, 12, when the section of the support structure 110 is moved perpendicular to the longitudinal axis of the support structure 110 (for example, the movement of one or both vertical supports 112, 114). Therefore, the mounting devices 61-64 can be designed differently.In particular, the mounting devices 61-64 can be implemented not only in the form of a plug-in connection, but also in the form of a snap-in connection, a rail connection, a screw connection, and / or a clamping connection. The rail connection can be any plug-in connection with variously shaped rail-like elements instead of pins, wherein the rails extend in the direction in which the respective second part (e.g., part 62a) is moved. A clamping connection can comprise a clamping element, which comprises, for example, a strap, a clamping bracket, or a buckle.

[0077] The hook-and-loop fastener strip 135 can then be released, and at least one section of the support structure 110, for example, the vertical support 114, can be moved back. This allows the support structure 110 to be moved out of the triangular area 3, while the aircraft system components 20 remain in their final position.

[0078] Figure 5 shows schematically a cross-sectional view of another mounting system 100 in a triangular area 3. Most elements of the mounting system 100 shown correspond to those of the mounting system 100 from Figure 3 . Therefore, these same elements will not be described again. Figure 5 However, it shows reference symbols which, for illustration purposes, Figure 3 The following describes the differences between the two mounting systems 100 according to Figure 3 and Figure 5 described.

[0079] The mounting system 100 according to Figure 5comprises a further guide rail 126, which is designed to be arranged in an upper section of the triangular area 3. For example, the (upper) further guide rail 126 can be fastened to a cross member 10. Furthermore, the mounting system 100 comprises a further guide device 121, which is designed to move along the further guide rail 126 and to guide the support structure 110. For example, the further guide rail 126 can be a rail which is only exemplary in Figure 5 shown as an inverted U-profile.

[0080] For example, the additional guide device 121 can be supported by the additional guide rail 126 in the transverse direction of the triangular region 3. Thus, the support structure 110 is protected against tipping by the lower and upper guide rails 125, 126.

[0081] Alternatively, the support structure 110 can also be suspended only on an upper guide rail 126, which also prevents tipping.

[0082] Alternatively or in addition to the arrangements of the Figures 3 or 5 The support structure 110 can be guided on / in one or more lateral guide rails (not shown). This is particularly helpful when there are 3 elements in the lower and / or upper section of the triangular area, such as the Figure 1 shown component 25.

[0083] However, this component 25 can also be an aircraft system component which is inserted with the support structure 110 into its final assembly position within the triangular area 3.

[0084] Figure 6 Finally, shows schematically a cross-sectional view of yet another mounting system 100. The same elements as in the examples according to Figures 3 and5 are again provided with the same reference numerals, and their description is omitted here to avoid repetition. This mounting system 100 has at least one cross member 170 whose length can be varied transversely to the longitudinal direction of the support structure 110. This change in length is represented by a respective double arrow. For example, the support structure 110 can comprise one or more vertical members 114, each of the cross members 170 projecting in one direction from the vertical member 114. However, one or all of the cross members 170 can also be attached to a longitudinal member 111, 113.

[0085] One of the mounts 130 can be arranged at each free end of such a cross member 170. Thus, an aircraft system component 20 can be releasably held at each free end of a cross member 170. By appropriately changing the length of the cross member 170 (for example, by means of a threaded rod and nut, (linear) motor, (electric, pneumatic and / or hydraulic) actuator, etc.), the respective aircraft system component 20 can be removed from the vertical support 114. In doing so, the aircraft system component 20 is brought into its final assembly position. The movement of the cross member 170 can be not only linear, but also circular, elliptical, or any desired movement along a path. For this purpose, the cross member can have corresponding linear and / or round elements that can be displaced / moved relative to one another.

[0086] As already mentioned in relation to Figure 3As described above, the aircraft system components 20 can also be attached to the aircraft structure 5, 10, 12 via a mounting device 61-64. The respective mounting device 61-64 can also consist of at least two parts, which can be pushed into one another and / or can engage with one another according to the movement of the aircraft system component 20 by the movement of the cross member 170.

[0087] Finally, Figure 6 A schematic representation of a holder in the form of a clip 136 is shown. This can be attached in the form of an elastic element to a cross member 170 or to a vertical member 112, 114 or to a longitudinal member 111, 113 and can be dimensioned such that an aircraft system component 20 can be inserted into the clip 136. Due to the elastic properties of the clip 136, the respective aircraft system component 20 can be releasably held on the support structure 110.

[0088] Figure 7shows a schematic flow diagram of a method for assembling an aircraft system component 20 in a triangular area 3 in a lower deck 8 of an aircraft 1. In step 510, a guide rail 125 is first introduced into the triangular area 3.

[0089] Furthermore, in step 520, a support structure 110 with a guide device 120 and at least one holder 130 is provided. An aircraft system component 20 is attached to the at least one holder 130 in a step 530. Optionally, a mounting device 61-64 can also be attached in step 535. For example, one part of the mounting device 64 can be attached to the aircraft system component 20 and another part to an aircraft structure 5, 10, 12. All of this work can be performed while the assembly system 100 is located outside the aircraft fuselage. This enables a simple, fast, and ergonomically balanced assembly of the aircraft system components 20.

[0090] The thus prefabricated assembly system 100 (in particular the support structure 110 with attached aircraft system component 20) is inserted into the triangular region 3 in step 540. The support structure 110 is moved along the guide rail 125 by means of the guide device 120.

[0091] For example, after reaching the correct position in the longitudinal direction of the triangular region 3, at least a portion of the support structure 110 can be moved in step 550. This movement occurs transversely to the longitudinal direction of the support structure 110 until the aircraft system component 20 has assumed a final assembly position within the triangular region 3.

[0092] There, the aircraft system component 20 can be fastened in step 560 to at least one primary structural component 5, 10, 12 of the aircraft 1 forming the triangular region 3, and the aircraft system component 20 can be detached from the holder 130 in step 570.

[0093] Finally, in step 580, the support structure 110 can be moved out of the triangular area 3, and in step 590 the guide rail 125, 126 can be removed from the triangular area 3.

Claims

1. Mounting system (100) for mounting aircraft system components (20) in a triangular region (3) in a lower deck of an aircraft (1), wherein the mounting system (100) comprises: - a support structure (110); - a guide mechanism (120) which is fastened to the support structure (110) and is specified to guide the support structure; - at least one bracket (130) which is fastened to the support structure (110) and is specified to releasably hold an elongate aircraft system component(20); wherein the mounting system (100) further comprises a guide rail (125); the guide mechanism (120) being set up to be moved along the guide rail (125), the support structure (110) being dimensioned such that the support structure (110) can be pushed into the triangular region (3) in the longitudinal direction of the triangular region (3) through the guide mechanism (120) and the guide rail (125), characterized in that the support structure (110) is elongate, the guide rail (125) is specified to be inserted in a portion of the triangular region (3) and in the longitudinal direction of the triangular region (3), and at least one portion of the support structure (110) is specified to be moved in a direction perpendicular to the longitudinal direction of the support structure (110).

2. Mounting system (100) according to Claim 1, wherein the support structure (110) comprises at least one longitudinal member (111, 113) and a plurality of vertical members (112, 114).

3. Mounting system (100) according to Claim 2, wherein the at least one bracket (130) is fastened to the plurality of vertical members (112, 114).

4. Mounting system (100) according to Claim 2 or 3, wherein the at least one portion of the support structure (110) is a vertical member (112) of the plurality of vertical members (112, 114), which is movable in the direction perpendicular to the longitudinal direction of the support structure (110).

5. Mounting system (100) according to Claim 4, wherein the one vertical member (112) by way of a joint (118) and an expansion device (116) is connected an additional vertical member (114) of the plurality of vertical members, and can be rotated relative to the additional vertical member (114).

6. Mounting system (100) according to one of Claims 1 to 5, wherein the support structure (110) comprises at least one cross member (170) which is adjustable in terms of length transversely to the longitudinal direction of the support structure (110); and wherein a bracket of the at least one bracket (130) is disposed on a free end of the at least one cross member (170).

7. Mounting system (100) according to one of Claims 1 to 6, furthermore comprising: - an additional guide rail (126) which is specified to be disposed in another portion of the triangular region (3); and - an additional guide mechanism (121) which is specified to be moved along the additional guide rail (126) and to guide the support structure (110).

8. Mounting system (100) according to one of Claims 1 to 7, wherein the at least one bracket (130) has a receiving surface which corresponds to a section of an outer surface of an aircraft system component (20).

9. Mounting system (100) according to any one of claims 1 to 8, wherein the at least one bracket (130) comprises a Velcro strip (135), which is designed to hold the aircraft system component (20) or to embrace, and / or wherein the at least one bracket (130) comprises a clip (136) which is specified to releasably hold the aircraft system component (20).

10. Mounting system (100) according to one of Claims 1 to 9, furthermore comprising: - a two-piece mounting device (61-64), wherein a first part (64b) of the mounting device is specified to be fastened to and support the aircraft system component (20), and a second part (64a) of the mounting device is specified to be fastened to a Z-strut (12), a crossbeam (10) or a frame (5) of the aircraft (1).

11. Mounting system (100) according to Claim 10, wherein the two-piece mounting device (64) comprises a plug connection, a latching connection, a rail connection, a screw connection and / or a clamping connection.

12. Method for mounting an aircraft system component (20) in a triangular region (3) in a lower deck of an aircraft (1), wherein the method comprises: introducing (510) a guide rail (125) into a portion of the triangular region (3) and in the longitudinal direction of the triangular region (3); providing (520) a support structure (110) comprising a guide mechanism (120) and at least one bracket (130); attaching (530) an elongate aircraft system component (20) to the at least one bracket (130); pushing (540) the support structure (110) into the triangular region (3) in the longitudinal direction of the triangular region (3) by moving the support structure (110) along the guide rail (125) by means of the guide mechanism (120); moving (550) at least one portion of the support structure (110) in a direction perpendicular to the longitudinal direction of the support structure (110) in such a manner that the elongate aircraft system component (20) is moved into a final mounting position within the triangular region (3); Fastening (560) the aircraft system component (20) to at least one primary structural component (5, 10, 12) of the aircraft (1) forming the triangular region (3); releasing (570) the aircraft system component (20) from the at least one bracket (130); and extracting (580) the support structure (110) from the triangular region (3).

13. Method according to Claim 12, further comprising: attaching (535) a first part (64a) of a mounting device (64) to the aircraft system component (20); and attaching (535) a second part (64b) of the mounting device (64) to a Z-strut (12), crossbeam (10) or frame (5) of the aircraft (1); wherein the fastening (560) of the aircraft system component (20) comprises connecting the first and second parts (64a, 64b) of the mounting device (64).

14. Method according to Claim 12 or 13, further comprising: removing (590) the guide rail (125) from the triangular region (3).