Modular system for installing modules on a fuselage structure of a vehicle

专利摘要:
Modular system for installing modules on a fuselage structure of a vehicle Modular system (2) for installing modules (6) on a fuselage structure (40) of a vehicle, comprising a plurality of modules (6) on which retaining elements (22, 24) for attachment to a fuselage structure (40) are arranged, a plurality of mounting frames (4) movable on a floor plane (10) and at least one connecting element ( 70, 72, 74) at least in certain areas, which extends over all the modules (6) and couples these to each other in a state installed on the fuselage structure (40). Each mounting frame (4) comprises a base (8) for supporting the mounting frame (4) on the floor plane (10) and at least one holding device (16) spaced from the base (8) which is adapted to support one of the modules (6). The mounting frames (4), the modules (6) and the at least one connecting element (70, 72, 74) are designed to form a mounting frame chain (4) with modules (6) arranged on them and connected to each other in a ready-to-use manner so that at least two successive groups (54, 56, 66, 68) of the mounting frame (4) form a pivot point to which the modules (6) facing each other have a greater distance from one another than the modules (6) within the respective groups (54, 56, 66, 68). The at least one connecting element (70, 72, 74) is adapted to enable the mounting frame groups (54, 56, 66, 68) to pivot relative to one another at the pivot point on the mounting frame (4). an angle of at least 90 ° on the floor plane (10). Figure 1
公开号:FR3077058A1
申请号:FR1873320
申请日:2018-12-19
公开日:2019-07-26
发明作者:Hermann Dipl.-Ing.BENTHIEN；Martin Dr. METTEN；Florian Müller；Michael Telkamp；Marcus Hinrichs；Tancredi TINCANI；Ralph Schmitt
申请人:Airbus Operations GmbH；
IPC主号:

专利说明:

Description
Title of the invention: Modular system for installing modules on a fuselage structure of a vehicle Technical field [0001] The invention relates to a modular system for installing modules on a fuselage structure of a vehicle and a method for installing modules on a fuselage structure of a vehicle.
Background of the invention [0003] In an aircraft which comprises a fuselage, a passenger cabin provided with a plurality of items of equipment is generally present. The fuselage constructed using a fuselage structure is provided for this purpose, on its inner side, with a plurality of retaining elements which are individually adapted to the items of equipment to be received and achieve their safe mounting in a predefined location. In aircraft and in particular in large airliners with a fuselage length of well over 10 m, there are always some manufacturing tolerances that must be taken into account when fitting restraints. While equipment objects must have a clearly predefined geometry in the fuselage, it is therefore necessary to adapt the individual retaining elements to compensate for the manufacturing tolerances of the fuselage structure. For example, a corrugation of a line or surface formed from several upper storage compartments is much more limited than, for example, dimensional tolerances of the fuselage structure.
The installation of individual modules and the compensation of tolerances, in particular for the adaptation of the visible contours in the interior of an aircraft cabin, are difficult and include, in addition to the mechanical connection, also the connection by electric or other lines or conduits. This obstructs the cabin and may prevent further work in the cabin.
Summary of the invention [0005] It can be very advantageous to obtain a simplified mounting inside a vehicle, without cluttering, for a long period, the interior space of the vehicle and consequently without slowing down other works.
The objective of the invention is therefore to provide an installation system for components in a vehicle, which system can be implemented as quickly, precisely and conveniently as possible.
The invention relates to a modular system for installing modules on a fuselage structure of a vehicle. The modular system comprises several modules on which are arranged retaining elements intended to be fixed to a fuselage structure, several mounting frames movable on a floor plane and at least one flexible connection element at least in certain zones, which s 'extends over all modules and couples them to each other in a state installed on the fuselage structure. Each mounting frame includes a base for supporting the mounting frame on the floor plan as well as at least one retainer spaced from the base, which is designed to support one of the modules. The mounting frames, the modules as well as the at least one connecting element are designed to form a chain of mounting frames provided with modules arranged on these and connected to each other in a ready-to-use manner. so that at least two successive groups of mounting frames form a pivot point at which the modules facing each other have a greater distance from each other than the modules inside the respective groups, and l at least one connecting element being designed to allow the pivoting of the mounting frame groups with respect to each other at the pivot point by an angle of at least 90 ° on the floor plane.
The modular system according to the invention is therefore an advantageous combination of several modules to be installed as well as several mounting frames, which can be equipped with the modules to be installed. Thanks to the interaction of mounting frames and modules, special advantages can be obtained. These reside in particular in the fact that several mounting frames, which are juxtaposed, can be equipped with modules to be installed. These modules can be chained to each other in a ready-to-use manner on the mounting frames by means of at least one connecting element. The equipment of the mounting frames can be compared to equipment of the fuselage structure, since the modules can be subjected to a functional test directly on the mounting frames before all of the mounting frames are chained together. to others is introduced into the vehicle, to effectively carry out the installation of the modules on the fuselage structure. The arrangement and the sequence of the individual modules therefore do not require a presence inside the vehicle, so that complex working phases for the assembly of the modules, their sequence and the functional test, which require a certain time, can be performed outside the vehicle.
In this context, it should be noted that modules can be produced in different ways, to then perform an installation on the fuselage structure. Modules which are coupled to one another by means of electric and / or pneumatic lines or lines are particularly suitable. In particular the modules which must be arranged at the level of an upper region in a passenger cabin.
In addition to the transfer of preparation work to the outside of the vehicle, the modular system according to the invention also has the advantage that, thanks to a mounting chassis chain which supports modules connected to each other from ready to use, it can also be used in tight spaces. This takes into account the fact that often only a limited space is available for moving or operating an assembly frame chain in an assembly hall, while at the same time, the space available for making re-entering a mounting chassis chain into the vehicle is limited. The ability to pivot at least two groups of mounting frames through at least 90 ° allows movement of the mounting frames in a relatively small space, regardless of the total length of the mounting frame chain.
The following example makes it possible to explain this in other words. The vehicle to be equipped can be an airliner. When fitting out, part of the fuselage may be open on one side or at least one door opening may be available. Assuming that a fuselage open from one side is present, it can usually be entered by means of a sort of bridge, which extends transversely from the opening of the fuselage. Transversally means in this context that the bridge can be arranged substantially perpendicular to the longitudinal axis of the fuselage. In the case of mounting of equipment usual in the state of the art, individual elements of limited size are moved, manually or by means of individual auxiliary devices, in the fuselage of aircraft passing through the bridge. Then, the respective component is manually connected to the fuselage structure and oriented appropriately. According to the invention, an entire assembly chassis chain can however be provided, which is transported along the bridge in the direction of the aircraft fuselage. Since the bridge has a finished width of about 5 m, it makes sense to introduce several mounting frame groups one after the other into the aircraft fuselage. Thanks to the ability to pivot at least 90 °, a group of mounting frames can therefore still be on deck while another group is already positioned inside the aircraft fuselage or inserted into it. .
The pivot point which is formed by the at least two successive groups is located at a greater distance between two successive mounting frames which belong to two successive groups of mounting frames. Depending on the type of vehicle which is equipped with the modular system according to the invention, such a location, that is to say an interval in which the pivot point is arranged, cannot be chosen arbitrarily. It is obvious, in the context of the description above, that the ready-to-use link of the modules with each other must also remain within this interval. This interval can therefore for example be associated with a door zone of the vehicle fuselage, in which none of the said modules must be arranged but a connection by means of at least one connection element must remain. The spacing of the door areas of a vehicle for the transport of persons is however not arbitrarily determined in a variable manner but determined by relevant directives for evacuation in the event of an unforeseen event. A determined configuration of the mounting frames, modules and spacings of the abovementioned intervals can therefore be defined in relation to the usual length of a module intended to be installed in an aircraft.
The connection of the individual mounting frames with each other can be carried out by means of mechanical couplings. These must be suitable to also allow small swivel movements to cover turns. A connection between two groups of mounting frames which form the pivot point can be effected by means of particularly suitable elongated coupling devices. These can also protect the at least one connecting element extending over the interval, by the fact that it is surrounded by a sort of cage or grid. The elongated coupling device preferably does not define the pivot radius at the pivot point.
In conclusion, a particularly advantageous manufacturing of equipment components for a vehicle cabin is made possible by the modular system according to the invention, which manufacturing allows a transfer of adaptation work outside a fuselage vehicle and therefore allows more efficient mounting. In addition, an all-in-one group of modules can be prepared outside the fuselage by adapting the modules and the mounting frames supporting them, even when space is limited.
In an advantageous embodiment of the invention, the at least one flexible connecting element is an electrical and / or pneumatic pipe or line of connection between two modules. With a view to producing the modules and the modular system according to the invention, the modules can generally have a suitable configuration. For this, we can in particular ensure that the desired radii of curvature or pivoting radii are easier to achieve thanks to suitable positioning of the corresponding pipes or connecting lines. In the case of several pipes or connecting lines, these should be deformable if possible easily around the same pivot axis. Where possible, these should also have the same distance from the pivot axis when the modules are on the retainers.
In an advantageous embodiment, each mounting frame comprises at least one pivoting device, which can pivot around a horizontal pivot axis around a vertical frame of the mounting frame. The pivoting device can for example comprise a pivoting arm which can be pivoted from a substantially vertical position to a substantially horizontal position. By means of the pivoting device, a module attached to the mounting frame can be, after the positioning of the mounting frame on the fuselage structure, pivoted in a planned position and then mounted. The pivoting device can in particular be blocked, so that after the displacement of the pivoting device, the position then provided for the module allows its simple fixing.
Advantageously, the base of each of the mounting frames is designed to come into contact with at least one fixed point on the floor plane and to adjust at least the vertical distance of the retaining device relative to the fixed point. In the case of an assembly frame chain, which supports the modules to be installed and are positioned on the fuselage structure, it can thus be ensured that the initial positions are sufficiently precise so that very precise positions of the modules are predefined from the installation process. Such a fixed point can be provided by specific devices already installed. As an example, we can refer here to floor slides in a cabin.
In a particularly preferred manner, the retaining elements of each module are designed to fix a variable distance of the module or of a component of the module relative to the fuselage structure. A particular advantage is that the individual modules can be fitted with tolerance compensation devices or can be fixed by means of tolerance compensating retaining elements, which particularly simplify assembly using this modular system. Since the fuselage structure has a certain manufacturing tolerance which can lead to an unsatisfactory tolerance of the mounting positions inside the fuselage structure, the modules to be installed must be brought to their intended final positions. Since the mounting frames can easily reach the intended end positions by exact positioning in the fuselage structure, these modules should only be fixed in them. Thanks to restraints compensating for tolerances or similar measures, the modules can be very easily fixed to the fuselage structure from their precise starting position on the mounting frames and respect individual distances from the structure of fuselage.
Particularly suitably, the at least one connecting element is designed to allow the pivoting of the mounting frame groups relative to each other at the pivot point by an angle of 180 ° on the floor plane. Thus, an nesting of the individual groups and their arrangement in parallel with each other can be ensured. The compacted mounting frame chain can be more easily maneuvered on a limited working surface. The ability to pivot 180 ° can also make it easier to introduce the chain into the fuselage structure because flexible and large-scale pivoting of the groups relative to each other allows successive introduction of the groups even in the event of very limited available space.
In a particularly advantageous embodiment, the modules and at least one connecting element are designed so as to be able to achieve a radius of curvature less than or equal to 1 m at the pivot point. Thus, a tight juxtaposition of second groups of mounting frames on which modules are installed is possible. In particular, the route of very tight turns to introduce a mounting chassis chain into a vehicle fuselage with limited action surface is easily possible.
In an advantageous embodiment, the individual modules have a length of 1.5 to 3 m. This necessarily results in the lengths of the associated mounting frames. Several mounting frames of this type can be linked together and an angle of 90 ° or 180 ° can be made between at least two adjacent mounting frames. The assembly chassis chain can then be introduced, via bridge structures, into a vehicle fuselage extending transversely or obliquely with respect thereto, when the bridge structure has a width of between 3 , 5 and 7 m. This has the particular advantage that even a longer chain of mounting frames including for example four or more mounting frames can be easily inserted into a vehicle fuselage via a bridge. Particularly preferably, the length of the individual modules is about 2 m.
In a particularly preferred manner, the modules and the retaining devices are designed so that the modules can be fixed on one side, so that they are suspended from the retaining devices in the direction of the floor plane for equipping the modules with at least one connecting element and to prepare for installation.
It should be noted here that the fixing of the modules to the mounting frames is carried out using the retaining elements arranged on the modules, which retaining elements are used to fix the modules to the fuselage structure. These retaining elements can be arranged in several places on the respective modules and have a distance from each other which corresponds to associated characteristics of the fuselage structure. For example, several retaining elements can be distributed such that their distances from one another correspond to the distances of the fuselage pairs from each other.
As indicated above, the greatest distance of the at least two successive groups of mounting frames corresponds substantially to a width of a door area of the fuselage structure.
The invention further relates to a method for installing modules on a fuselage structure in a vehicle, comprising the steps of supplying several movable mounting frames on a floor plan, of supplying several modules to be installed on which are arranged retaining elements, for fixing the modules on one side to the retaining devices of the mounting frames, so that the modules are suspended from the retaining devices in the direction of the floor plan, of the modules with at least one flexible connecting element, so that they are connected to one another in a ready-to-use manner, for moving, in a vehicle fuselage, mounting frames connected so as to form a chain, positioning of all mounting frames to positions provided in the fuselage structure, pivoting of the modules to their intended fixing position e and fixing modules.
The fixing of the modules can include the fixing of a first group of retaining elements, the pivoting of the modules and the fixing of a second group of retaining elements. For example, a first group of retaining elements can be formed by the first retaining elements, the second group of retaining elements can be formed by the second retaining elements. Or vice versa depending on the configuration of the modules.
Preferably, the vehicle fuselage is an aircraft fuselage, the positioning of the mounting frames comprising the locking in floor rails in the floor plane of the aircraft fuselage. This can be followed by an adjustment of the height of the individual mounting frames in order to exactly position their retaining devices.
BRIEF DESCRIPTION OF THE FIGURES [0028] Other characteristics, advantages and possibilities of application of the present invention follow from the description below of the exemplary embodiments and the figures. In this case, all the characteristics described and / or illustrated form in themselves and in any combinations the subject of the invention also independently of their composition in the individual claims or their dependencies. In the figures, identical reference signs designate identical or similar objects.
[Fig-1] illustrates a side view of part of a modular system according to the invention.
[Fig.2] illustrates a mounting frame of Figure 1 comprising a pivoting device pivoted upwards.
[Fig.3a] [0032] [fig.3b] [0033] [fig.3c] illustrate the operation of inserting and orienting mounting frames and modules.
[Fig.4a] [fig.4b] [0036] [fig.4c] to [0037] [fig.4d] illustrate a fuselage structure on which are arranged receiving devices for receiving module retainers.
[Fig.5a] [0039] [fig.5b] [0040] [fig.5c] [0041] [fig.5d] [0042] [fig.5e] to [0043] [fig.5f] as well that [fig.6a] [0045] [fig.6b] [0046] [fig.6c] [0047] [fig.6d] [0048] [fig.6e] to [0049] [fig-6f] illustrate the movement of an assembly chassis chain in an aircraft fuselage.
[Fig.7] illustrates a view of a module on which are arranged connecting elements.
Detailed representation of examples of embodiments [0052] Figure 1 illustrates a side view of a part of a modular system 2. Here are illustrated a mounting frame 4 and a module 6 to be installed. The mounting frame 4 comprises a base 8 serving to support the mounting frame 4 on a floor plane 10. The base 8 comprises for this purpose a base frame 12 on which are arranged wheels 14. The mounting frame 4 can therefore be moved on the floor plane 10 using the wheels 14.
On one side, opposite the base 8, of the mounting frame 4 is arranged a retaining device 16 in which the module 6 can be suspended. In this context, it can be noted that the module 6 comprises a retaining frame 18, retaining bars 20, first retaining elements 22 and second retaining elements 24. The first retaining elements 22 are connected to each other using a base body 26. The base body can be made in the form of an elongated element, for example a tube. This can extend along the longitudinal axis of a fuselage to be fitted with modules 6. In the same way, the second retaining elements 24 can be connected to each other, in this case by means of a second base body 28. The base bodies 26 and 28 can better distribute the load along the longitudinal direction of the fuselage in the installed state of the modules 6 and other components which can be mounted on these.
Components 30 are arranged on the retaining frame 18, which must be mounted by way of example between an upper storage compartment and a fuselage structure of an aircraft. In the illustration illustrated in FIG. 1, the retaining frame 18 on which the system 30 is arranged is suspended, by means of the retaining bars 20, from the retaining device 16 in the direction of the floor plane 10.
The mounting frame 4 further comprises a pivoting device 32, which can pivot, by means of a pivot axis 34, between the substantially vertical orientation illustrated in FIG. 1 and a substantially horizontal orientation. A support device 36 is in contact with the retaining frame 18 at one end of the pivoting device 32, so that the retaining frame 18 can rest on the support device 36. Thanks to the pivoting of the pivoting device 32 around the pivot axis 34, the retaining frame 18 is therefore pivoted from the vertical position to the horizontal position that the retaining frame 18 must adopt after installation.
FIG. 2 illustrates the mounting frame 4 with the pivoting device 32 pivoted upwards, which can be locked in a horizontal position, for example using a locking device 38. In this, the first retaining elements 22 can be connected to a fuselage structure 40. Then or simultaneously, the second retaining elements 24 can be connected to the fuselage structure 40. In the illustrated illustration, the retaining frame 18 forms, jointly with the retaining bars 20 and corresponding links to the fuselage structure 40, a triangular structure. The fixing of the retaining elements 22 and 24 can be interpreted as a preparation step serving to compensate for tolerances of the fuselage structure. The exact position of the retaining frame 18 relative to the fuselage structure 40 can be adjusted by means of tolerance compensation devices (not shown).
This is shown schematically once again in the figures FIG. 3a to 3c. Here, two mounting frames 4 are introduced into a vehicle fuselage 42 comprising a fuselage structure 40. The two rest, by the wheels 14, on the floor plane 10. The second retaining elements 24 are brought into position respectively, by the fact that the mounting frames 4 are in their intended positions and adjust a height determined at the level of the retaining devices 16 by means of an adjustment device (not illustrated). By way of example, the adjustment of the mounting frames 4 can be carried out in particular by means of floor slides 44 into which the mounting frames 4 can be snapped.
Figures 3b and 3c respectively illustrate the oriented retaining device 16 with the second retaining elements 24 brought into position, the retaining frame 18 being pivoted in position.
Figures 4a to 4d illustrate a fuselage structure 40 comprising a pair 44 as well as beams 46. A receiving device 48 which is designed to receive the second retaining element 24 is illustrated on a pair. This is, in Figures 4a to 4d successive, connected to the receiving device 48 by means of a bolt 50. In addition, the second base body 28 is also shown here, which projects through an opening in the first retaining element 24. The second retaining element 24 and the second base body 28 are designed to adjustably provide, at a variable position of the second base body 28, a solid mechanical connection to the second retaining element 24. By Consequently, the relative position of several second retaining elements 24 relative to each other can be adjusted.
FIG. 4a illustrates the second retaining element 24 having a slightly too low height on the receiving device 48. After adjusting the mounting height, the second retaining element 24 is inserted in the receiving device 48, after which the position of the second base body 28 is adjusted. Then, as can be seen in Figure 4d, the bolt 50 is inserted. It can be seen that the retaining bar 20 protrudes out of an opening of the first retaining element 24. This can also be equipped with a tolerance compensation device, so that the insertion depth or screwing the retaining bar 20 into the first retaining element 24 can be adapted.
Figures 5a to f illustrate the movement of a whole chain 52 of mounting chassis 4 on which are arranged modules 6 to equip an aircraft fuselage 42 with modules 6. Here, four mounting chassis 4 directly coupled to each other are illustrated by way of example, which form a first group 54 of mounting frames 4. A second group is formed by four other mounting frames 4 and is designated by the reference sign 56. The two groups 54 and 56 are pivoted 180 ° relative to each other at a pivot point 58. The successive mounting frames 4 concerned are here connected to each other by means of a pivoting link 60. This makes so that the two groups 54 and 56 are movable close to one another and are not damaged, so that an assembly of the modules 6 on the mounting frames 4 and their connection can be carried out. Another function test after transport may be superfluous, if correct transport can be guaranteed.
A dotted line indicates an illustrative action area 62, along which the two groups 54 and 56 are movable. As can be seen in FIG. 5b, the second group of mounting frames 56 can for example be pivoted upwards around the pivot point 60, the first group 54 can also be pivoted slightly to the side. After pivoting upwards substantially over 90 ° (FIG. 5c), the first group 54 may already have entered the aircraft fuselage 42. This is indicated in FIGS. 5d and 5e. In FIG. 5f, the second group of mounting frames 56 is finally introduced into the aircraft fuselage 42.
Figures 6a to 6f illustrate another example in which a different action area 64 is present and two groups 66 and 68 of mounting frame 4 can be used. While in FIG. 6a, two other groups 66 and 68 of mounting frames 4 are arranged parallel to each other, the second group 68 is pivoted upwards from the first group 66 and introduced into the fuselage aircraft 42 in Figure 6b. The pivoting and insertion movement continues in Figure 6c, until an angle of approximately 90 ° between the two groups 66 and 68 is present in Figure 6d. Then, the first group 66 is spaced further from the second group 68 until the two groups 66 and 68 extend substantially along a direction in Figure 6f and can thus be fully introduced into the aircraft fuselage 42.
FIG. 7 illustrates a view of a module 6 which is equipped with several retaining bars 20, a second base body 28 and a plurality of pipes or lines 70, 72 and 74 as connecting elements. If, as shown for example in FIGS. 3a to 3c, the module 6 is then fixed to a mounting frame 4 by means of the second retaining elements 24, the retaining frame 18 is suspended from the retaining bars 20. Then, the second base body 28, the pipes or lines 70, 72 and 74 are all in a plane which is located directly below the retaining device 28. The position of the retaining device 28 as well as that of the couplings between the mounting frames 4 individual can be adapted to each other so as to obtain as little bending of the pipes or lines 70, 72 and 74 as well as the second base body 28 when a chain consisting of several mounting frames is moved to the interior of a manufacturing workshop. The flexibility of the connecting elements 70, 72 and 74 allows the slight pivoting of the mounting frames 4 relative to one another in the case of mounting frames 4 directly adjacent. If there is a large gap between mounting frame groups 4, for example in the pivot point 58 in Figures 5a to 5f, pivoting up to 180 ° may be allowed. The pipes or lines or connecting elements 70, 72 and 74 must be adapted to it.
In addition, it should be noted that "comprising" does not exclude any other element or any other step. In addition, it should be noted that characteristics which have been described with reference to one of the examples of embodiments mentioned above can also be used in combination with other characteristics of other examples of embodiments described above. The reference signs in the claims should not be considered to be limiting.

权利要求:
Claims (1)
[1" id="c-fr-0001]
[Claim 1] [Claim 2] [Claim 3]
claims
Modular system (2) for installing modules (6) on a fuselage structure (40) of a vehicle, characterized in that it comprises several modules (6) on which are arranged retaining elements (22, 24) intended to be fixed to a fuselage structure (40), several mounting frames (4) movable on a floor plane (10) and at least one connecting element (70, 72, 74) flexible at least in certain zones, which extends over all the modules (6) and couples them to each other in a state installed on the fuselage structure (40), each mounting frame (4) comprising a base (8) serving to supporting the mounting frame (4) on the floor plane (10) as well as at least one retaining device (16) spaced from the base (8), which is designed to support one of the modules (6), the mounting frames (4), the modules (6) as well as the at least one connecting element (70, 72, 74) being designed to form a ch mounting frame (4) with modules (6) arranged thereon and connected to each other in a ready-to-use manner so that at least two successive groups (54, 56, 66, 68 ) of mounting frames (4) form a pivot point at which the modules (6) turned towards one another have a greater distance from each other than the modules (6) inside the groups (54 , 56, 66, 68) respectively and the at least one connecting element (70, 72, 74) being designed to allow the pivoting of the groups (54, 56, 66, 68) of mounting frames (4) one relative to the others at the pivot point at an angle of at least 90 ° on the floor plane (10).
Modular system according to claim 1, characterized in that the at least one flexible connection element (70, 72, 74) being an electrical and / or pneumatic connection line or line between two modules (6). Modular system (2) according to claim 1 or 2, characterized in that the base (8) of each of the mounting frames (4) being designed to come into contact with at least one fixed point on the floor plane (10) and to adjust at least the vertical distance of the retainer (16) [Claim 4] [Claim 5] [Claim 6] [Claim 7] [Claim 8] [Claim 9] relative to the fixed point.
Modular system (2) according to any one of the preceding claims, characterized in that each mounting frame (4) comprising at least one pivoting device (32), which can pivot around a horizontal pivot axis (34) around a vertical frame of the mounting frame (4). Modular system (2) according to any one of the preceding claims, characterized in that the retaining elements (22, 24) of each module (6) being designed to fix a variable distance from the module (6) or from a component of the module (6) relative to the fuselage structure (40).
Modular system (2) according to any one of the preceding claims, characterized in that the at least one connecting element (70, 72, 74) being designed to allow the groups (54, 56, 66, 68) to pivot. mounting frame (4) relative to each other at the pivot point (60) at an angle of 180 ° on the floor plane (10).
Modular system (2) according to any one of the preceding claims, characterized in that the modules (6) and the at least one connecting element (70, 72, 74) being designed so as to be able to produce a radius of curvature less than or equal to 1 m at the pivot point (60).
Modular system (2) according to any one of the preceding claims, characterized in that the individual modules (6) having a length of 1.5 to 3 m. Modular system (2) according to any one of the preceding claims, characterized in that the modules (6) and the retaining devices (16) being designed so that the modules (6) can be fixed on one side, so that they are suspended from the retaining devices (16) in the direction of the floor plane (10) for equipping the modules (6) with the at least one connecting element (70, 72, 74) and to prepare for installation.
[Claim 10] [Claim 11] [Claim 12] [Claim 13]
Modular system (2) according to any one of the preceding claims, characterized in that the greatest spacing of the at least two successive groups (54, 56, 66, 68) of the mounting frame (4) corresponding substantially to a width d a door area of the fuselage structure (40).
Method for installing modules (6) on a fuselage structure (40) in a vehicle,
Characterized in that it includes steps of:
supply of several mounting frames (4) movable on a floor plan (10), supply of several modules (6) to be installed on which are arranged retaining elements (22, 24), fixing of the modules (6) one side to the retaining devices (16) of the mounting frames (4), so that the modules (6) are suspended from the retaining devices (16) in the direction of the floor plane (10), fitting of the modules (6 ) with at least one flexible connecting element (70, 72, 74), so that they are connected to one another in a ready-to-use manner, displacement, in a vehicle fuselage, of the mounting frames ( 4) connected so as to form a chain, positioning of all the mounting frames (4) at positions provided in the fuselage structure (40), pivoting of the modules (6) to their intended fixing position and fixing of the modules (6).
Method according to claim 11, characterized in that the fixing of the modules (6) comprises the fixing of a first group of retaining elements (22, 24), the pivoting of the modules (6) and the fixing of a second group of retaining elements (22, 24).
Method according to claim 11 or 12, characterized in that the vehicle fuselage is an aircraft fuselage and the positioning of the mounting frames (4) comprises snap-fastening in floor runners in the floor plane (10) of the aircraft fuselage.

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EP2848505A1|2015-03-18|Engine spreader installation bracket and mounting assembly for corresponding motor vehicle manufacturing plant

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FR2923762A1|2009-05-22|Equipment i.e. armrest, for seat of e.g. commercial motor vehicle, has support arm with joint pivoting around axle that is placed laterally under base of seat such that bearing and support arms are placed under seat in retracted position

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EP3882082A1|2021-09-22|Vehicle with improved pivoting arm

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FR3073437B1|2019-10-11|VEHICLE ASSEMBLY STATION FOR A MOTOR VEHICLE

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FR2987338A1|2013-08-30|Mechanical preparation framework for pre-positioning of tank forming element of car, has adaptation interface arranged to adapt vertical position of tank carrying frame with respect to base plate and receiving unit

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EP2218622B1|2013-10-23|Side wall of the bodyshell of a passenger railway transport vehicle

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FR2724920A1|1996-03-29|Swingletree for handling of heavy aircraft engines

同族专利:

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公开号 | 公开日

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US20190193872A1|2019-06-27|

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CN110015426A|2019-07-16|

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DE102017131150A1|2019-06-27|

引用文献:

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公开号 | 申请日 | 公开日 | 申请人 | 专利标题

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US3419164A|1966-01-12|1968-12-31|Robert A. O'neill|Method and apparatus for handling aircraft passengers, baggage and freight|

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US5842668A|1997-02-27|1998-12-01|Hexcel Corporation|Quick fit overhead stowage compartment|

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CA2332489A1|2001-01-26|2002-07-26|Federal Steel Equipment Ltd.|Storage and transport support for airplane seat|

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DE102009023391A1|2009-05-29|2010-12-02|Airbus Deutschland Gmbh|Method and system for assembling interior components in an aircraft|

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DE102010018272A1|2010-04-26|2011-10-27|Airbus Operations Gmbh|Rail system and method for mounting a component in an aircraft|

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DE102010055962A1|2010-12-23|2012-06-28|Airbus Operations Gmbh|Aircraft system component carrier system mounted in aircraft cabin, has aircraft system component carrier module that is fastened to aircraft structural element of fuselage upper shell by structural holder|

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DE102012001797A1|2012-01-30|2013-08-01|Airbus Operations Gmbh|System and method for assembling aircraft system components in the crown area of an aircraft|

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FR3029897B1|2014-12-11|2016-12-09|Airbus|METHOD FOR INSTALLING EQUIPMENT IN A CABIN OF AN AIRCRAFT|DE102019118494A1|2019-07-09|2021-01-14|Airbus Operations Gmbh|Assembly system, method for assembling a component, component arrangement and aircraft|

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DE102020103626A1|2020-02-12|2021-08-12|Airbus Operations Gmbh|Articulated connection and method for fastening a vehicle device to a primary structure of a vehicle, truss structure with an articulated connection and aircraft with an articulated connection|

法律状态:
2019-12-19| PLFP| Fee payment|Year of fee payment: 2 |

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2021-09-10| ST| Notification of lapse|Effective date: 20210806 |

优先权:

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申请号 | 申请日 | 专利标题

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DE102017131150.5|2017-12-22|

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DE102017131150.5A|DE102017131150A1|2017-12-22|2017-12-22|Module system for installing modules on a fuselage structure of a vehicle|

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