Mounting system for suspended mounting of storage compartments, particularly in aircraft

Description

[0001] The invention relates to a fastening system for the hanging installation of storage compartments, in particular in aircraft.

[0002] In passenger areas of transportation, such as the cabins of commercial aircraft, suspended storage compartments are typically arranged. These compartments typically serve as luggage boxes for hand luggage, as well as for clothing and other passenger belongings. These compartments are referred to as overhead stowage compartments or hatracks. Fastening systems are used to attach the storage compartments to the aircraft's supporting structure, allowing them to be suspended and thus forming ceiling containers, for example, in the passenger cabin.

[0003] The storage compartments are often very large and must have a high load-bearing capacity, for example, to accommodate the hand luggage of a large number of passengers. Nevertheless, the installation and removal of the storage compartments should be carried out as quickly and as easily as possible by as few personnel as possible, and ideally without the use of tools. Furthermore, the fastening systems for the storage compartments or overhead racks must withstand high loads in order to withstand the forces and associated stresses encountered during flight operations when loaded, thus ensuring the secure attachment of the storage compartments.

[0004] The suspended attachment of the storage compartments to the support structure is usually achieved using fastening systems, each with a pair of eyebolts and a bolt that is inserted into the two eyebolts to connect them together. For example, one eyebolt is located on the side of a fastening element and another eyebolt is located on the side of the storage compartment. To insert the bolt into the eyebolts of the pair of eyebolts, the two eyebolts are aligned with each other.

[0005] EP 2265 492 A1 discloses a method for attaching an element of an aircraft interior to a supporting structure in an aircraft. The element is connected to the aircraft interior using a first locking device on a first fixing device, pivoted relative to the supporting structure, and connected to a second fixing device using a second locking device. This fixes the element of the aircraft interior relative to the supporting structure.

[0006] US 2008 / 0 136 071 A1 discloses an elastomeric tie rod end insulator and an elastomeric cartridge insulator.

[0007] FR 2 685 756 A1 discloses parts of a sound- and heat-insulating mattress that are modified so that the mattress's waterproofness and insulating properties are maintained when attached to a base. The mattress is provided with an opening and a foam insert arranged in the opening and provided with a cover. The insert is held in the opening by an adhesive strip bonded to the foam insert and the mattress.

[0008] The document EP 2563 659 B1 describes a fastening system for suspended ceiling containers, comprising a pair of support eyes that can be attached to a support structure or a ceiling container, and comprising a main bolt for detachably connecting the support eyes. The main bolt is spring-loaded in a main bolt guide toward the first support eye and, when the ceiling container is not yet mounted, assumes an end position in which the main bolt is extended from the main bolt guide. Due to the spring preload, the main bolt is extended during the upward movement of the ceiling container into its mounting position with the aid of an inclined ramp formed on the first support eye into a receptacle of the first support eye, where it can be positively locked. A stop is designed as a centrally arranged pin, and the main bolt has a complementary bore in which the pin can be received.

[0009] Fig. 2 shows a known fastening system for a ceiling container 120, which forms an overhead stowage compartment (OHSC) or a luggage rack or hat rack in the cabin of an aircraft. The known fastening system is designed, for example, as described in detail in the above-mentioned patent publication. It comprises a plate-shaped, first fastening element 101, which serves for fastening to a supporting structure or to a frame 102 of the aircraft. A second fastening element 103 is screwed to the first fastening element 101.

[0010] The second fastening element 103 is screwed to a third fastening element 106 using screws 107. The third fastening element 106 is provided with a double support eyelet 108, on each of whose sides a further support eyelet 109, 110 is arranged in alignment. A bolt is arranged in each of the support eyes 109, 110, which, when inserted into the central double support eyelet 108 from both sides, fastens the ceiling container 120 to the third fastening element 106. A click and snap system is provided for fixation.

[0011] The well-known fastening system is intended to enable advantageous assembly within a short installation time. However, one disadvantage is that its components are relatively expensive to manufacture and relatively heavy. The hatrack or OHSC must also be shaken during assembly to enable the click-and-snap function. Furthermore, an additional rig is required to prevent uncontrolled forces in the frame. In addition, very complex fine-tuning is required, which can take 15 minutes or more per fastening system used.

[0012] Another problem is condensation, which forms in large quantities on the supporting structure, especially when an aircraft traverses various altitudes. Condensation can then seep into the storage compartment and the cabin interior from the mounting system.

[0013] The invention aims to overcome the aforementioned disadvantages. Specifically, it is intended to create a fastening system for the suspended installation of storage compartments or overhead stowage compartments that effectively prevents condensation forming on the supporting structure from penetrating the interior. Furthermore, the fastening system should enable weight reduction. Furthermore, the fastening system should enable time and cost savings, particularly during installation.

[0014] The object is achieved by the fastening system according to patent claim 1. Advantageous embodiments are the subject of the subclaims.

[0015] The invention provides a fastening system for the suspended installation of storage compartments, in particular in aircraft, comprising: a first fastening element designed for fastening to a support structure; a second fastening element designed for fastening to a storage compartment for receiving objects; and a connecting arrangement designed for flat fastening on the first fastening element, wherein the connecting arrangement and the second fastening element each comprise a support eye for receiving a fastening bolt in order to fasten the connecting arrangement to the second fastening element;and the first fastening element and the connecting arrangement each have a fastening surface for mutual fastening, so that a continuous insulation layer for insulating the supporting structure can be positioned between the fastening surfaces and / or between the supporting structure and the first fastening element in order to continuously insulate the supporting structure from the connecting arrangement.;

[0016] This makes it possible to install a layer of insulation on a primary structure without having to cut or recess the insulation layer. This prevents condensation from entering the cabin.

[0017] The invention allows the support structure, for example, together with the first fastening element, to be continuously insulated from the connecting arrangement. For this purpose, the first fastening element and the connecting arrangement are designed such that their mutual connection can be screwed. For example, the first fastening element is permanently connected to the support structure, in particular by riveting.

[0018] The first fastening element can also advantageously be designed so that it can be screwed to the supporting structure. This allows the insulation to be clamped between the supporting structure or primary structure and the first fastening element.

[0019] In this way, the invention offers increased flexibility in the installation of the insulation layer, since it can be positioned and installed according to the respective requirements in such a way that no moisture can reach the storage compartment from the supporting structure in the area of ​​the fastening system.

[0020] The connecting arrangement comprises a first connecting element and at least one second connecting element, which are adjustable and fixable in their position relative to one another.

[0021] This allows the position of the first lifting eye to be quickly adjusted in relation to the position of the second lifting eye.

[0022] The connecting elements each have a connecting surface with a toothing for mutual fixation.

[0023] This allows the connecting surfaces to interlock when the connecting elements are fastened together, which ensures quick and reliable

[0024] Adjusting the position of the connecting elements relative to each other allows for quick adjustment of the position of the connecting assembly's lifting eye. This creates a particularly resilient, adjustable connection.

[0025] The connecting arrangement is preferably made of plastic.

[0026] This significantly reduces the weight of the fastenings of an aircraft's storage compartments.

[0027] Advantageously, the fastening system comprises a toothed plate made of plastic.

[0028] In particular, the toothed plate can be fastened to a toothed side surface of one of the connecting elements in order to fix the connecting element between the toothed plate and the other connecting element in a desired position by mutual toothing.

[0029] The plastic is preferably a carbon fiber reinforced plastic and / or a glass fiber reinforced plastic.

[0030] In particular, the first fastening element is made of aluminum.

[0031] Advantageously, the fastening system comprises a vibration damper arranged in at least one of the support eyes.

[0032] Preferably, the connecting arrangement is produced by injection molding and / or overmolding.

[0033] Advantageously, the gear plate is manufactured by injection molding and / or overmolding.

[0034] Preferably, the connecting surfaces of the connecting elements in the assembled state of the fastening system are parallel to a

[0035] Mounting surface aligned for attaching the first fastener to the support structure.

[0036] Advantageously, the connecting surfaces of the connecting elements are aligned parallel to a fastening surface between the first fastening element and the first connecting element in the assembled state of the fastening system.

[0037] The connecting surfaces of the connecting elements in the assembled state of the fastening system can advantageously also be aligned perpendicular to a fastening surface between the first fastening element and the first connecting element.

[0038] Preferably, the second connecting element is plate-shaped at least in a partial area.

[0039] For example, the support eye of the connecting arrangement is formed in the plate-shaped region of the second connecting element.

[0040] Advantageously, the second connecting element is flat. For example, it transitions continuously from a relatively wide portion in the region of its connecting surface, which serves to connect to the first connecting element, into a relatively narrow portion, in which the support eye of the connecting arrangement is preferably formed.

[0041] Preferably, markings such as notches or small holes are integrated into the individual components or fastening and connecting elements. This ensures pre-alignment during assembly of the components. If these markings match, the components are optimally pre-aligned, which simplifies assembly. Later, i.e., when aligning the storage compartments, which are designed as hat racks, for example, the pre-alignment can be deviated from if necessary.

[0042] Preferred embodiments of the invention are explained in more detail below with reference to the accompanying drawings. Herein: Fig. 1 shows a fastening system according to a preferred embodiment of the invention as a schematic view obliquely from the front; Fig. 2 shows a schematic representation of a known fastening system for ceiling containers, as described above; Fig. 3 shows a fastening system according to a particularly preferred embodiment of the invention as a schematic view of its front side; Fig. 4 shows the Fig. 3 shown fastening system in a schematic exploded view; Fig. 5 a schematic view of the rear of the Figures 3 and 4 shown fastening system; Fig. 6 a schematic side view of the Figures 3 to 5 shown fastening system attached to a supporting structure; Fig. 7 a schematic side view of the Figures 3 to 5shown fastening system, together with its fastening element for attachment to a storage compartment; and Fig. 8 shows a fastening system according to another preferred embodiment of the invention, which is attached to a supporting structure, in a schematic spatial view obliquely from the front.

[0043] In the figures, identical or corresponding elements are designated by the same reference numerals and will therefore not be described repeatedly unless appropriate. The disclosures contained in the entire description apply mutatis mutandis to identical parts with the same reference numerals or the same component designations. Furthermore, the positional information chosen in the description, such as top, bottom, side, etc., refers to the directly described and illustrated figure and, if the position changes, is to be applied mutatis mutandis to the new position. Furthermore, individual features or combinations of features from the different embodiments shown and described can represent independent, inventive or inventive solutions in themselves.

[0044] Figure 1shows a fastening system 10 according to a preferred embodiment of the invention in a spatial schematic view obliquely towards its front. The fastening system 10 is used for the suspended installation of storage compartments 11 in an aircraft. The storage compartments 11 can be, for example, luggage compartments, ceiling containers, storage compartments, storage containers, storage bins, or the like, which are suspended or mountable, for example, in an aircraft cabin and in particular form so-called overhead storage compartments or hatracks.

[0045] The fastening system 10 comprises a first fastening element 12, which is designed for fastening to a support structure 13. For this purpose, the first fastening element 12 has a fastening surface 25 with which it is fastened to the support structure 13. The support structure 13 is, for example, a frame of an aircraft fuselage.

[0046] Furthermore, the fastening system 10 comprises a second fastening element 14, which is designed for fastening to the storage compartment 11 to be mounted in a suspended manner, of which Figure 1 a partial area is shown. Between the first fastening element 12 and the second fastening element 14, a connecting arrangement 15 is provided, which is designed for flat fastening on the first fastening element 12.

[0047] The connecting arrangement 15 comprises a support eye 16 and the second fastening element 14 comprises a support eye 17. The support eyes 16, 17 are designed to receive a fastening bolt 18 so that, by being received in the support eyes 16 and 17, the fastening bolt fastens the connecting arrangement 15 to the second fastening element 14 when the support eyes 16, 17 are arranged in alignment with one another.

[0048] In the example shown here, a lifting eyelet 17 of a second fastening element 14 is arranged on each side of the lifting eyelet 16. However, it is also possible to arrange a lifting eyelet 17 of a second fastening element 14 on only one side.

[0049] The first fastening element 12 and the connecting arrangement 15 each comprise a fastening surface 12a and 22a, respectively, via which the connecting arrangement 15 can be fastened or is fastened to the first fastening element 12. The fastening is effected by means of screws 20.

[0050] In this way, it is possible that during assembly between the fastening surfaces 12a, 22a a continuous insulation layer 21 for insulating the supporting structure 13 can be positioned and installed, which in Figure 6As a result, the support structure 13, together with the first fastening element 12 fastened to the support structure 13, can be continuously insulated from the connecting arrangement 15 without the need to introduce slots, recesses, or the like into the insulation layer 21.

[0051] During assembly, only the screws 20 are inserted through the insulation layer 21, so that they are surrounded by the insulation layer 21 in the area between the first fastening element 12 and the connecting arrangement 15, flush and sealed against moisture. In this way, no condensation, which forms in large quantities on the support structure 13, for example, at different flight altitudes, can penetrate through interruptions in the insulation layer 21 or through openings made therein in the fastening area of ​​the storage compartments and enter the cabin area.

[0052] The connecting arrangement 15 comprises a first connecting element 22 and a second connecting element 23, the position of which relative to one another is adjustable and fixable. The fastening system 10 thus comprises the first fastening element 12, the second fastening element 14, and the connecting arrangement 15 with its first connecting element 22 and its second connecting element 23.

[0053] The first fastening element 12 is designed as a so-called A-bracket, i.e. as a Class A bracket that can be fastened to a supporting structure of an aircraft and is designed to fasten a so-called B-bracket, i.e. a Class B bracket.

[0054] The connecting arrangement 15 or its first connecting element 22 is designed as a B-bracket, which can be fastened to the A-bracket or the first fastening element 12 by means of the screws 20.

[0055] The second connecting element 23 of the connecting arrangement 15 is also designed as a B-bracket. During assembly, it is connected to the first connecting element 22 by means of screws 24. The second connecting element 23 is attached to the first connecting element 22 so that it can move in two directions, with the directions of movement being aligned perpendicular to each other and indicated by double arrows in the figure.

[0056] In this way, the position of the support eye 16 relative to the first connecting element 22, and thus also relative to the support structure 13, can be adjusted or adjusted in two degrees of freedom before being fixed in the appropriate position using the fastening means 24. This allows the storage compartments 11 to be adjusted accordingly, which, in addition to the resulting mechanical improvement, also leads to uniform, evenly running optical lines of the storage compartments mounted in this way.

[0057] In the area of ​​the connection between the first connecting element 22 and the second connecting element 23, these each have a connecting surface 22b and 23a, respectively, which face each other during assembly and are each provided with a toothing. This allows the position of the second connecting element 23 relative to the first connecting element 22 to be adjusted. Subsequently, by tightening the screws 24, the toothing of the connecting surfaces 22b, 23a engages with each other, thereby creating a force-locking and form-locking connection between the connecting elements 22, 23. This makes the connection particularly stable, so that the adjusted position is maintained even under particularly heavy loads.

[0058] The first fastening element 12 is made of aluminum and is attached to the supporting structure 13 or the frame of the aircraft fuselage, for example, by riveting. The connecting arrangement 15 with its connecting elements 22, 23 is made of plastic, preferably fiber-reinforced or carbon-fiber-reinforced and / or glass-fiber-reinforced plastic. In particular, the connecting elements 22, 23 or the connecting arrangement 15 can be manufactured by an injection molding process.

[0059] In the embodiment shown here, the connecting surfaces 22b, 23a of the connecting elements 22 and 23 are aligned perpendicular to the fastening surfaces 12a, 22a, with which the connecting arrangement 15 is fastened or can be fastened to the first fastening element 12 by means of its first connecting element 22.

[0060] Based on the Figures 3 to 5A fastening system 10 according to another preferred embodiment of the invention is described in detail below. Figure 3 the fastening system 10 as a schematic view from the front, while the Figures 4 and 5 The fastening system 10 is shown in a schematic exploded view and as a schematic view of its rear side. For simplicity, the second fastening element 14 is not shown in these figures. Except for a few differences, the fastening system is the same or similar to that of Fig. 1 designed.

[0061] As mentioned above with reference to Figure 1 As described, the plate-like first fastening element 12 serves for the flat fastening to the supporting structure 13. It is fastened with its rear side 25, which is Figure 5 is visible and forms a fastening surface, attached to the support structure 12, that is to say for example to a side surface of the frame.

[0062] On the front side 26 of the first fastening element 12, which Fig. 3 As can be seen, the first connecting element 22 of the connecting arrangement 15 is screwed using the screws 20. For this purpose, the front side 26 of the first fastening element 12 forms the fastening surface 12a for fastening the first connecting element 22. Accordingly, the fastening surface 22a is provided on the rear side 27 of the first connecting element 22 (see Fig. 5 ), which is arranged opposite the fastening surface 12a of the first fastening element 12.

[0063] The second connecting element 23 of the connecting arrangement 15 is fastened to the first connecting element 22 by means of the screws 24. For this purpose, a connecting surface 22b for connecting to the second connecting element 23 is formed on the rear side 27 of the first connecting element 22 (see Fig. 5 ).

[0064] The connection between the first connecting element 22 and the second connecting element 23 is designed such that the two connecting elements 22, 23 are movable relative to each other in two directions which are aligned orthogonally to each other, as shown in Figure 4 is marked by double arrows. This allows the position of the second connecting element 23 to be adjusted relative to the first connecting element 22, and the appropriate position can be firmly and securely fixed by subsequently tightening the screws 24.

[0065] For adjusting and fixing the desired position of the second connecting element 23, which is movable with respect to the first connecting element 22, a toothing is additionally provided on the rear side 27 of the first connecting element 22. Correspondingly, on the oppositely arranged connecting surface 23a of the second connecting element 23, which is in Fig. 4visible, a toothing is also formed.

[0066] By tightening the fastening screws 20 or their associated nuts, the second connecting element 23 is fixed in the appropriate or desired position on the first connecting element 22 by the teeth of their corresponding or complementary connecting surfaces 22b, 23a interlocking and thereby ensuring high stability.

[0067] In addition, on the other side of the first connecting element 22, ie on its front side 28, which forms a further connecting surface and in the Figures 3 and 4visible, a toothed plate 29 is arranged. The toothed plate 29 also has a toothing on its side facing the first connecting element 22 and therefore not visible here, in order to mesh with a corresponding or complementary toothing on the front side 28 of the first connecting element 22.

[0068] Thus, the first connecting element 22 is fixed flatly and on both sides via toothings between the second connecting element 23 and the toothing plate 29, wherein after adjusting the second connecting element 23, the fixing is carried out by tightening the fastening screws 24, which extend through the second connecting element 23, the first connecting element 22 and the toothing plate 29 and engage in the associated nuts (see Fig. 4 ).

[0069] A vibration damper 30 is arranged in the support eye 16 of the second connecting element 23 and secured by a locking ring 31. This isolates the storage compartment 11 and other interior components of the aircraft from noise and vibrations.

[0070] The first fastening element 12 is as in the Fig. 1 The embodiment shown is an A-bracket or A-holder made of aluminum. The first connecting element 22 and the second connecting element 23 are designed as B-bracket or B-holder, as described above, and are made of plastic, preferably carbon fiber-reinforced or glass fiber-reinforced plastic. These measures and the construction shown here achieve a particularly low weight of the fastening system 10 with a very high load-bearing capacity.

[0071] The Figures 6 and 7show the fastening system 10 in a side view, together with the support structure 13 to which it is attached. In addition, Figure 7 also the attachment of the lifting eye 16 of the connecting arrangement 15 between two lifting eyes 17 of second fastening elements 14, to which an arrangement of storage compartments 11 is attached. The fastening system 10 is as described above with reference to the Figures 3 to 5 described.

[0072] As in Fig. 6As shown, the supporting structure 13 or the frame of the aircraft fuselage, together with the first fastening element 12 attached thereto, is enclosed by the insulating layer 21. In the area of ​​the fastening surfaces 12a, 22a and also outside of them, the insulating layer 21 extends continuously between the first fastening element 12 and the first connecting element 22 of the connecting arrangement 15. In this way, the supporting structure 13 with the first fastening element 12 attached thereto is completely or without interruptions insulated from the connecting arrangement 15 and the storage compartment held thereon. The insulating layer 21 is designed for heat and moisture insulation.

[0073] In the Figures 3 to 7In the embodiment of the fastening system 10 shown, the connecting surfaces 22b, 23a for mutual fastening of the connecting elements 22, 23 in the assembled state of the fastening system 10 are aligned parallel to the fastening surface 12a, 22a between the first fastening element 12 and the first connecting element 22.

[0074] Figure 8 shows a further embodiment of the fastening system 10. As in the embodiments described above, the connection arrangement 15 comprises a first connecting element 22 and a second connecting element 23, which are movable relative to each other in two degrees of freedom, as in Figure 4 shown and explained above. However, in the Figure 8 In the embodiment shown, the first connecting element 22 is designed as a relatively thin plate which is arranged flatly between the second connecting element 23 and the first fastening element 12.

[0075] The first fastening element 12 forms an offset between its fastening surface 25 for fastening to the support structure 13 and its fastening surface 12a for fastening the connecting arrangement 15 or the first connecting element 22.

[0076] Here too, as mentioned above with reference to Fig. 6 described, the insulation layer 21 is positioned or installed continuously between the first fastening element 12 and the first connecting element 22 of the connecting arrangement 15 in order to bring about, in the assembled state, a continuous and complete insulation of the support structure 13 with the first fastening elements 12 fastened thereto relative to the connecting arrangement 15.

[0077] Alternatively, the Fig. 6 The insulation layer 21 shown can be clamped between the supporting structure 13 and the first fastening element 12. For this purpose, the first fastening element 12 is screwed to the supporting structure 13.

[0078] The connecting surfaces for mutually connecting the connecting elements 22, 23 are formed by one side 22b of the first connecting element 22 and by the opposite side 23a of the second connecting element 23. These connecting surfaces 22b, 23a are aligned parallel to the fastening surface 25 of the first fastening element 12 on the support structure 13. They are also formed parallel to the connecting surfaces 12a, 22a, which serve to fasten the first connecting element 22 to the first fastening element 12.

[0079] In this embodiment, the first fastening element 12 is also designed as an A-bracket, whereas the second connecting element 23 is designed as a B-bracket for securing the storage compartments 11. The connecting elements 22, 23 and the second fastening element 14, which is designed for securing the storage compartments 11, are made of plastic, preferably fiber-reinforced and in particular carbon-fiber-reinforced and / or glass-fiber-reinforced plastic.

[0080] The invention offers the following advantages in particular: By dividing the fastening system 10 into A and B brackets, it is possible to install a layer for insulating the primary structure between the two brackets while avoiding a cut in the insulation layer. This prevents condensation from entering the cabin.

[0081] The invention also offers the further advantage that the fastening system is adjustable in two preferably perpendicular directions. Opposing toothing allows adjustment of the interface to the ceiling container or the overhead storage compartment (OHSC).

[0082] Furthermore, the interior components are decoupled from noise and vibration. This is made possible by the vibration damper, which is preferably integrated into the B-bracket or connecting element and secured in the B-bracket by a simple snap-lock ring. This fixation allows for very easy replacement of the vibration damper after its service life has been reached.

[0083] Commercially available standard parts are used to assemble the fastening system 10 and its parts, i.e. no special fastening devices or specially developed bearings are necessary.

[0084] The invention is based in particular on three parts of a bracket or fastening concept, whereby each part can advantageously be manufactured from fiber-reinforced plastic, in particular by means of injection molding.

[0085] To avoid the risk of corrosion that can arise from the combination of carbon fiber-reinforced plastic and aluminum, the invention proposes two possible solutions that can also be combined with each other. Firstly, a non-conductive material layer can be placed between the carbon fiber-reinforced plastic and the aluminum to decouple the materials. Secondly, glass fiber reinforcement can be provided instead of carbon fiber reinforcement.

[0086] To further increase the load-bearing capacity and strength of the fastening system, an additional fiber insert can be created using overmolding technology, which further increases the load-bearing capacity of the brackets or fastening system elements. Overmolding is an injection molding process in which one material is molded onto a second material, typically a rigid plastic. This allows the overmolded thermoplastic material to form a strong bond with the plastic and maintain its strength in the user environment.

[0087] A further advantage is that the connection to the storage compartment or ceiling container can be made using a simple standard bolt. The bolt preferably attaches two storage compartments or OHSCs to a bracket or holder. List of reference symbols:

[0088] 10 Fastening system 11 Storage compartment 12 First fastening element 12a Fastening surface for the connection arrangement 13 Supporting structure 14 Second fastening element 15 Connection arrangement 16 Supporting eye 17 Supporting eye 18 Fastening bolt 20 Screws 21 Insulation layer 22 First connecting element 22a Fastening surface for fastening to the first fastening element 22b Connection surface to the second connecting element 23 Second connecting element 23a Connection surface to the first connecting element 24 Fasteners or screws 25 Back or fastening surface of the first fastening element 26 Front of the first fastening element 27 Back of the first connecting element 28 Front or connecting surface of the first connecting element 29 Toothed plate 120Ceiling container 101First fastening element 102Supporting structure or frame 103Second fastening element 106Third fastening element 107Screws 108Double lifting eye 109, 110Further lifting eye

Claims

1. Fastening system for the suspended installation of stowage compartments, in particular in aircraft, comprising: a first fastening element (12), which is designed for fastening on a supporting structure (13); a second fastening element (14), which is designed for fastening on a stowage compartment (11) for accommodating items; and a connecting arrangement (15), which is designed for surface-area fastening on the first fastening element (12), wherein the connecting arrangement (15) and the second fastening element (14) each comprise a supporting eyelet (16, 17) for accommodating a fastening bolt (18), in order for the connecting arrangement (15) to be fastened on the second fastening element (14); and the first fastening element (12) and the connecting arrangement (15) each have a fastening surface (12a, 22a) for fastening on one another, and therefore a continuous insulation layer (21) can be positioned between the fastening surfaces (12a, 22a), and / or between the supporting structure (13) and the first fastening element (12), for the purpose of insulating the supporting structure (13), in order for the supporting structure (13) to be insulated throughout in relation to the connecting arrangement (15), and the connecting arrangement (15) comprises a first connecting element (22) and at least one second connecting element (23), which can be adjusted and fixed in position relative to one another, characterized in that the connecting elements (22, 23) each have a connecting surface (22b, 23a) with a toothing formation for fixing on one another.

2. Fastening system according to one of the preceding claims, characterized in that the connecting arrangement (15) is produced from plastic.

3. Fastening system according to one of the preceding claims, characterized by a toothing plate (29) which is provided with a toothing formation, is produced from plastic and can be fastened on a toothed surface (28) of one of the connecting elements (22, 23) in order for the connecting element (22) to be fixed in a desired position between the toothing plate (29) and the other connecting element (23) by mutual toothing engagement.

4. Fastening system according to Claim 2 or 3, characterized in that the plastic is a carbon-fibre-reinforced plastic and / or a glass-fibre-reinforced plastic.

5. Fastening system according to one of the preceding claims, characterized in that the first fastening element (12) is produced from aluminium.

6. Fastening system according to one of the preceding claims, characterized by a vibration damper (30), which is arranged in at least one of the supporting eyelets (16, 17).

7. Fastening system according to one of the preceding claims, characterized in that the connecting arrangement (15) is produced by injection moulding and / or by overmoulding.

8. Fastening system according to one of Claims 3 to 7, characterized in that the toothing plate (29) is produced by injection moulding and / or by overmoulding.

9. Fastening system according to one of Claims 1 to 8, characterized in that, in the joined-together state of the fastening system (10), the connecting surfaces (22b, 23a) of the connecting elements (22, 23) are oriented parallel to the fastening surface (25) for fastening the first fastening element (12) on the supporting structure (13).

10. Fastening system according to one of preceding Claims 1 to 9, characterized in that, in the joined-together state of the fastening system (10), the connecting surfaces (22b, 23a) of the connecting elements (22, 23) are oriented parallel to the fastening surface (12a, 22a) between the first fastening element (12) and the first connecting element (22).

11. Fastening system according to one of Claims 1 to 9, characterized in that, in the joined-together state of the fastening system (10), the connecting surfaces (22b, 23a) of the connecting elements (22, 23) are oriented perpendicularly in relation to the fastening surface (12a, 22a) between the first fastening element (12) and the first connecting element (22).

12. Fastening system according to one of the preceding claims, characterized in that the second connecting element (23) is of at least partially plate-like design, and the supporting eyelet (16) of the connecting arrangement (15) is formed in the plate-like region of the second connecting element (23).

13. Fastening system according to one of the preceding claims, characterized in that the second connecting element (23) is of planar design, wherein it merges continuously from a relatively wide part in the region of its connecting surface (23a) for connection to the first connecting element (22) into a relatively narrow part, in which the supporting eyelet (16) of the connecting arrangement (15) is formed.