Floor arrangement for an aircraft with customizable load-loading capability, floor system for an aircraft, aircraft and method for customizing

Abstract

The invention relates to an aircraft floor arrangement with customizable load carrying capacity, a floor system for an aircraft, an aircraft and a method for customizing the load carrying capacity of an aircraft floor arrangement. In order to provide convenient adaptation of a floor design in terms of its load carrying capacity, an aircraft floor arrangement (10) with customizable load carrying capacity is provided, the aircraft floor arrangement (10) comprising a plurality of floor panels (12) and at least one support profile (14). The at least one support profile is configured to reinforce at least one of the floor panels such that load bearing capacity is increased. The floor panel is provided with a plurality of junction points (16) arranged at least in one direction. The joint point is configured for mounting one of the support profiles to one of the floor panels via the joint point to reinforce the floor panels.

Description

Technical Field

[0001] The present invention relates to a floor structure in an aircraft and in particular to an aircraft floor arrangement with a customizable load bearing capacity, a floor system for an aircraft, an aircraft and a method for customizing the load bearing capacity of an aircraft floor arrangement. Background Art

[0002] Aircraft usually have a floor in the fuselage. One example is a cabin floor for separating the cabin area from a cargo area which is usually arranged underneath. Another example is a floor in the cargo area. Yet another example is a floor in the cockpit area. The floor may have a floor panel which is arranged on a floor support structure which is mounted to structural components of the fuselage. Due to different use scenarios, for example in the cabin area, different requirements may be placed on the floor, which leads to the use of different floor panels. However, it has been shown that changes in the floor panel may lead to cumbersome redesign and official approval procedures, in particular when modifying an aircraft. Summary of the invention

[0003] Therefore, it may be desirable to provide for convenient adaptability of the floor design in terms of its load bearing capacity.

[0004] The objects of the invention are solved by means of the main aspects; further embodiments are incorporated in the additional aspects. It should be noted that the aspects of the invention described below also apply to an aircraft floor arrangement with customizable load bearing capacity, a floor system for an aircraft, an aircraft and a method for customizing the load bearing capacity of an aircraft floor arrangement.

[0005] According to the present invention, an aircraft floor arrangement with a customizable load bearing capacity is provided. The floor arrangement comprises a plurality of floor panels and at least one supporting profile. The at least one supporting profile is configured to reinforce at least one of the floor panels so that the load bearing capacity is increased. The floor panel is provided with a plurality of joints arranged at least along one direction. The joints are configured for mounting one of the supporting profiles to one of the floor panels via the joints to reinforce the floor panel.

[0006] Thus, the floor panel can be reinforced where required, for example locally, without further redesigning, since the panel is not altered by the attachment of the supporting profiles due to the provision of a plurality of joining points.

[0007] According to an example, the engagement points are arranged in a grid pattern.

[0008] According to an example, a plurality of different support profiles forming the reinforcement kit are provided, the support profiles being provided as at least one of the group consisting of:

[0009] i) Lower reinforcements of different lengths and heights;

[0010] i) upper reinforcements of varying lengths and widths; and

[0011] iii) Lateral stiffeners of different lengths and with different upper flange and web portions.

[0012] According to an example, the supporting profile is provided as an integrable profile comprising a horizontal flange portion for mounting an adjacent floor panel and a vertical web member providing additional load support.

[0013] According to an example, the support profile comprises an upper flange section configured to provide local trolley support.

[0014] According to another example, the support profile comprises an upper section configured to provide galley wall support.

[0015] In the example, the two options of trolley and galley wall support are provided in combination.

[0016] According to an example, a floor panel consisting of a plurality of floor panels is arranged as a sandwich panel, the sandwich panel comprising a top layer and a bottom layer separated by a central layer. The central layer comprises a sheet-like structure alternately fixed to the top layer and the bottom layer by a plurality of fixing points. At least some of the fixing points are arranged as joining points.

[0017] According to an example, the sheet-like structure is provided as at least one of the group consisting of: a corrugated sheet, a folded sheet, a trapezoidal sheet, a grooved sheet and a profiled sheet.

[0018] According to the invention, there is also provided a floor system for an aircraft. The floor system comprises an aircraft floor device according to one of the preceding examples and a support device having a plurality of floor supports. The plurality of floor panels are carried by the floor supports.

[0019] According to an example, the floor support comprises a longitudinal support profile for resting the floor panel on the support profile.

[0020] According to an example, the longitudinal support profile is provided as a seat rail resting on the transverse crossbeam. The panel rests on the seat rail.

[0021] According to the invention, an aircraft is also provided. The aircraft comprises a fuselage, wing devices attached to the fuselage, and a propulsion device attached to at least one of the groups of the fuselage and the wing devices. A floor, for example for a cabin area or a cargo area, is provided in the fuselage. The floor comprises at least one aircraft floor device according to one of the above examples or a floor system for an aircraft cabin according to one of the above examples.

[0022] According to the present invention, there is also provided a method for customizing the load bearing capacity of an aircraft floor device. The method comprises the following steps:

[0023] - providing a plurality of floor panels provided with a plurality of joining points arranged at least along one direction;

[0024] - providing at least one supporting profile, the at least one supporting profile being configured to reinforce at least one of the floor panels such that the load bearing capacity is increased; and

[0025] - Mounting one of the supporting profiles to one of the floor panels via the joining points to reinforce the floor panel.

[0026] According to one aspect, the floor panel of the floor arrangement is provided with a plurality of joint points. These points can be used to attach support profiles to locally increase the load-bearing capacity of the panel. This allows the floor panel to be allocated to the primary structure of the aircraft. In case of modifications, such as changes in the cabin or cargo layout, and due to the increase in loads that the modification anticipates to be handled, customizable local reinforcements provide appropriate changes, but without actually changing the primary structure. Thus, reinforcement becomes possible.

[0027] According to one aspect, the floor panel is pre-configured for the possibility of attaching a support profile if reinforcement is required. For this purpose, a plurality of possible attachment points are provided as joints. The support profile can then be attached to the floor panel without any actual changes to the floor panel. This allows changes even after the floor design as part of the primary structure of the aircraft has been approved. Thus, the floor arrangement can be changed in the sense of reinforcement with regard to the load-bearing capacity.

[0028] These and other aspects of the invention will be apparent from and elucidated with reference to the embodiments described hereinafter. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Exemplary embodiments of the present invention will be described below with reference to the following drawings:

[0030] Figure 1 An example of an aircraft floor arrangement having a customizable load carrying capacity is schematically illustrated.

[0031] Figure 2 An example of a floor system for an aircraft is schematically shown.

[0032] Figure 3 A cross section of an example of an aircraft is shown.

[0033] Figure 4 The basic steps of an example of a method for customizing the load bearing capacity of an aircraft floor arrangement are shown.

[0034] Figure 5 A cross section of an example of a floor panel with attached supporting profile is shown.

[0035] Figure 6 Shown in a larger view against the background of a trolley and a kitchen wall section Figure 5 .

[0036] Figure 7 Shown with mounting to crossbeam Figure 6 .

[0037] Figure 8 The transverse cross section shows Figure 7 .

[0038] Fig. 9 An example of a workflow for installing floor panels and supporting profiles is schematically shown.

[0039] Fig.10 Another example of a workflow for installing floor panels and supporting profiles is schematically shown. DETAILED DESCRIPTION

[0040] Certain embodiments will now be described in more detail with reference to the accompanying drawings. In the following description, the same reference numerals are used for the same elements even in different drawings. The contents defined in the specification, such as detailed construction and elements, are provided to help fully understand the exemplary embodiments. In addition, well-known functions or structures are not described in detail because they would make the embodiments unclear due to unnecessary details. In addition, expressions such as "at least one of..." when preceding a list of elements modify the entire list of elements rather than modifying the individual elements of the list.

[0041] Figure 1 An example of an aircraft floor installation 10 with a customizable load bearing capacity is schematically shown. The aircraft floor installation 10 comprises a plurality of floor panels 12 and at least one supporting profile 14. The at least one supporting profile 14 is configured to reinforce at least one of the floor panels 12 such that the load bearing capacity is increased. The floor panel 12 is provided with a plurality of joint points 16 arranged at least along one direction. The joint points 16 are configured for mounting one of the supporting profiles 14 to one of the floor panels 12 via the joint points 16 to reinforce the floor panel 12.

[0042] The at least one support profile 14 is shown having a plurality of joint connection points 18, such as a plurality of joint connection points 18 that are complementary to the joint points 16. The joint connection points 18 are arranged to match the pattern or spacing of the joint points 16 of the floor panel 12, with at least some of them being located at matching positions to allow the support profile 14 to be mounted to the floor panel 12.

[0043] In an example, the plurality of joint connection points 18 are provided with a pattern identical to that provided for the joint points 16. In another example, the plurality of joint connection points 18 are provided with a plurality of patterns identical to that provided for the joint points 16, or vice versa. For example, the pitch of the joint connection points 18, i.e., the repeating distance between the points, is twice the pitch of the joint points 16 or three or more times the pitch.

[0044] Arrow 20 indicates the option of mounting the supporting profile 14 to the floor panel 12 .

[0045] The joint 16 may also be referred to as a joint location, a joint, a connection point, a connection location, a connector, a mounting point, or a connection joint.

[0046] The joint point 16 is provided as a connection joint for additional mounting to a floor panel.

[0047] In one option, the aircraft floor installation 10 is a cabin floor installation for a cabin area of ​​an aircraft. In another option, the aircraft floor installation 10 is a cargo floor installation for a cargo area of ​​an aircraft.

[0048] The term “along a direction” relates to the linear direction of the joint connection point 18 .

[0049] In an example, the junctions are provided in a linear pattern, ie a one-dimensional pattern.

[0050] In another example, the junction points are provided in a planar pattern, ie a two-dimensional pattern. For example, a grid-like pattern is provided, for example with different or equal spacing in two or more different directions.

[0051] Thanks to customization, the load carrying capacity can be adjusted.

[0052] The support profile 14 can be arranged to be aligned with the longitudinal direction of the aircraft, ie the X direction. The support profile 14 can also be arranged to be aligned with a direction transverse to the longitudinal direction of the aircraft, ie the Y direction.

[0053] As an option, it is provided that the joining points 16 are provided in a grid pattern.

[0054] In an example, the junction point 16 is provided as a hole. In another example, the junction point 16 is provided as a blind bushing or a blind socket.

[0055] As a further option, it is provided that the supporting profile 14 is configured for reinforcing the floor panel 12 in at least one of the following groups: i) below, ii) above; and iii) laterally.

[0056] As a further option, it is provided that a plurality of different support profiles 14 forming the reinforcement kit are provided, the support profiles 14 being provided as at least one of the group consisting of:

[0057] i) Lower reinforcements of different lengths and heights;

[0058] ii) upper reinforcements of varying lengths and widths; and

[0059] iii) Lateral stiffeners of different lengths and with different upper flange and web portions.

[0060] Figure 2 An example of a floor system 100 for an aircraft is schematically shown. The floor system 100 comprises an example of an aircraft floor installation 10 according to one of the examples described above. The floor system 100 further comprises a support device 102 having a plurality of floor supports 104. A plurality of floor panels 12 of the aircraft floor installation 10 are carried by the floor supports 104.

[0061] The floor panels 12 and the floor supports 104 are arranged as part of the primary structure of the aircraft, i.e. a structure which is considered essential to the aircraft and which must not be changed or modified during the use of the aircraft. The support profiles 14 are not part of the primary structure and can be changed, e.g. installed, removed, etc.

[0062] As an example, the support device 102 includes a triangular cantilevered center console 106 attached to a vertical floor support 107 facing the center field and another triangular cantilevered side console 108 facing the lateral sides. The center console 106 provides floor support 104 and the side consoles 108 provide additional support 110 for lateral floor panels 112.

[0063] The coordinate system is Figure 2 As shown in the following figures, the X-axis indicates the longitudinal direction of the aircraft, the Y-axis indicates the horizontal direction transverse to the longitudinal direction of the aircraft, and the Z-axis indicates the vertical direction transverse to the longitudinal direction of the aircraft and transverse to the horizontal transverse direction of the aircraft.

[0064] Figure 3An example of an aircraft 200 is shown in cross section. The aircraft 200 comprises a fuselage 202, a wing device 204 attached to the fuselage 202, and a propulsion device 206 attached to at least one of the groups of the fuselage 202 and the wing device 204. A floor 208 for a cabin area or a cargo area is provided in the fuselage 202. The floor 208 comprises at least one example of an aircraft floor device 10 according to one of the above and following examples and an example of a floor system 100 for an aircraft cabin according to one of the above examples.

[0065] It should be noted that the support profile 14 is shown schematically.

[0066] Figure 4 The basic steps of an example of a method 300 for customizing the load bearing capacity of an aircraft floor installation are shown. The method 300 comprises the following steps:

[0067] - In a first step 302, a plurality of floor panels are provided, the plurality of floor panels having a plurality of joining points arranged at least along one direction.

[0068] - In a second step 304, at least one supporting profile is provided, said at least one supporting profile being configured to reinforce at least one of the floor panels such that the load bearing capacity is increased.

[0069] - In a third step 306, one of the supporting profiles is mounted to one of the floor panels via the joining points to reinforce the floor panel.

[0070] Figure 5 A cross section of an example of a floor panel 12 with an attached supporting profile 14 is shown.

[0071] As an option, the floor panel 12 composed of the plurality of floor panels 12 is provided as a sandwich panel 22 comprising a top layer 24 and a bottom layer 26 separated by a central layer 28. The central layer 28 comprises a sheet-like structure 30 alternately fixed to the top layer 24 and the bottom layer 26 by a plurality of fixing points 32. At least a part of the fixing points 32 are provided as joining points.

[0072] As an example, the fixing points 32 are provided for connecting the sheet-like structure 30 to the top layer 24 and the bottom layer 26. As an option, the fixing points 32 are provided at the same point for the top case and the bottom case. As another option, the fixing points 32 are provided at different points for the top case and the bottom case, such as Figure 5 As an example, the lower fixing point 32 is provided as a connector 36 for connection to the support profile 14 .

[0073] As an option, the supporting profile 14 is provided as a profile extending vertically at the level of the floor panel 12. For better illustration, the first bracket indicates the floor panel 12 and the second bracket 40 indicates the supporting profile 14.

[0074] The top layer 24 is the side of the floor panel 12 that faces the cabin area or the cargo area in the installed state. The bottom layer 26 is the side of the floor panel 12 that faces away from the cabin area or the cargo area in the installed state.

[0075] In the example, a floor surface layer 38 is arranged on the top layer. In the case of a cabin floor, the floor surface layer 38 can be provided as a carpet. In the case of a cargo floor, the floor surface layer 38 can be provided as a wear-resistant surface.

[0076] As an example, the sheet-like structure 30 is provided as a folded sheet. Figure 5 Indicated as an option.

[0077] In another option, the sheet-like structure 30 is provided as at least one of the group consisting of: a corrugated sheet, a trapezoidal sheet, a grooved sheet, and a profiled sheet.

[0078] Thus, the floor panel is arranged as at least one of the group of:

[0079] -Corrugated floor panels;

[0080] - Trapezoidal floor panels; and

[0081] -Special shaped panels.

[0082] In the example, corrugated floor panels oriented in the Y direction replace the cross beams and floor panels.

[0083] As combined Figure 8 It can also be seen that the support profile 14 is provided as an integrable profile 41 comprising a horizontal flange portion for mounting an adjacent floor panel and a vertical web member providing additional load support.

[0084] As an example, the integrable profile 41 comprises a lower profile portion 42, for example, having an I-beam cross section. An intermediate profile portion 44 is provided, for example, also having an I-beam cross section. The lower profile portion 42 and the intermediate profile portion 44 have a common first horizontal flange portion. The intermediate profile portion 44 comprises a vertical web member 48, which is followed by another flange portion 50, and the vertical web member 48 continues as an upper vertical web member 52. An upper flange section 54 is also provided. The upper flange section 54 may also be referred to as an upper flange portion.

[0085] In the options, such as Figure 8As shown in FIG, the support profile 14 comprises an upper flange section 54 configured to provide local trolley support. For this purpose, a trolley 60 with its wheels 62 is shown. The arrows illustrate the weight force resting on the wheels 62 just above the flange section 54. Due to the local reinforcement, the additional weight force can be compensated.

[0086] By way of example, the support profile 14 is configured for creating a joint in the floor plane.

[0087] In the options, also as Figure 8 As shown in , the support profile 14 comprises an upper section 54 configured to provide a kitchen wall support. For this purpose, a kitchen wall 64 of a kitchen is schematically shown. As an example, the kitchen wall 64 rests in or on a wall mounting 66, thereby fixing the wall to the floor, for example.

[0088] In an option not shown in detail, the floor support 104 comprises a longitudinal support profile for resting the floor panel 12 on the support profile.

[0089] In another option, which is likewise not shown in detail, the longitudinal support profile is provided as a seat rail which rests on the transverse cross member 68. The panel 12 rests on the seat rail.

[0090] The floor panel 12 may be reinforced by at least one supporting profile 14 to provide additional load carrying capacity where required.

[0091] In another option, the floor is a cabin floor with a cargo area below the cabin. The floor system is arranged as an airtight floor.

[0092] As an option, the floor system 100 with at least one mountable support profile 14 provides a modular truss structure.

[0093] The truss structure of the floor system is arranged as a system with modular reinforcement capabilities.

[0094] Figure 6 The larger view shows the background of a trolley 60 and a kitchen wall 64, for example, for providing additional support by means of the support profile 14. Figure 5 .

[0095] Figure 7 A mounting member having a mounting to a crossbeam 68 is shown. Figure 6 The bracket 70 provides a connection to the support profile 14. For example, an omega-shaped profile 72 is provided for further supporting the floor panel 12, thereby also carrying a seat track, for example.

[0096] Figure 8 The transverse cross section shows Figure 7 .

[0097] Fig. 9 An example of a workflow for installing a floor panel 12 and a support profile 14 is schematically shown. The floor panel is moved towards the support profile 14, as indicated by a first movement arrow 74. Brackets 75 and a plurality of joints 16 are provided for connection. The device is then lowered onto a floor grid, for example comprising beam members fixed to a crossbeam 68 by means of retaining brackets 70. The lowering is indicated by a second movement arrow 76.

[0098] Fig.10 Schematically shows the Fig. 9 Another example of a workflow for installing floor panels and supporting profiles in the viewing direction of the solution.

[0099] It must be noted that embodiments of the present invention are described with reference to different subject matters. In particular, some embodiments are described with reference to method claims, while other embodiments are described with reference to apparatus claims. However, from the above and following descriptions, it will be understood by those skilled in the art that, unless otherwise indicated, any combination of features related to different subject matters is also considered to be disclosed with the present application in addition to any combination of features belonging to one type of subject matter. However, all features can be combined to provide synergistic effects that exceed the simple superposition of features.

[0100] Although the present invention is illustrated and described in detail in the drawings and the foregoing description, such illustration and description are to be considered illustrative or exemplary rather than restrictive. The present invention is not limited to the disclosed embodiments. Other variations of the disclosed embodiments may be understood and effected by those skilled in the art in practicing the claimed invention through a study of the drawings, the disclosure, and the dependent claims.

[0101] In the claims, the word "comprising" does not exclude other elements or steps, and the indefinite article "a" or "an" does not exclude a plurality. A single processor or other unit may fulfill the functions of several items repeatedly cited in the claims. The fact that certain measures are repeatedly cited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage. Any reference signs in the claims should not be construed as limiting the scope.

Claims

1. An aircraft floor device (10) having a customizable load bearing capacity, the aircraft floor device (10) comprising: a plurality of floor panels (12); as well as at least one supporting profile (14); wherein said at least one supporting profile is configured to reinforce at least one of said floor panels such that said load bearing capacity is increased; wherein the floor panel is provided with a plurality of joint points (16) arranged at least along one direction; and Therein, the joining point is configured for mounting one of the supporting profiles to one of the floor panels via the joining point to reinforce the floor panel.

2. The device according to claim 1, wherein: The engagement points are arranged in a grid pattern.

3. The device according to claim 1 or 2, wherein: The support profile is configured for reinforcing the floor panel on at least one of the group of: i) below; ii) above; and iii) Lateral.

4. The device according to one of the preceding claims, wherein A plurality of different support profiles forming the reinforcement kit are provided, the support profiles being provided as at least one of the group consisting of: i) Lower reinforcements of different lengths and heights; ii) upper reinforcements of varying lengths and widths; and iii) Lateral stiffeners of different lengths and with different upper flange and web portions.

5. The device according to one of the preceding claims, wherein The support profile is provided as an integrable profile (41) comprising horizontal flange portions (50, 54) for mounting adjacent floor panels and vertical web members (48, 52) providing additional load support.

6. The device according to one of the preceding claims, wherein The support profile includes an upper flange section (54) configured to provide partial cart support.

7. The device according to one of the preceding claims, wherein The support profile includes an upper section (54) configured to provide galley wall support.

8. The device according to one of the preceding claims, wherein The floor panel composed of the plurality of floor panels is arranged as a sandwich panel, the sandwich panel comprising a top layer (24) and a bottom layer (26) separated by a central layer (28); and wherein the central layer comprises a sheet-like structure (30) alternately fixed to the top layer and the bottom layer via a plurality of fixing points (32); and Wherein, at least a part of the fixing points is set as the joining points.

9. The device according to claim 8, wherein: The sheet-like structure is configured as at least one of the group consisting of: i) corrugated sheets; ii) folding the sheet; iii) Trapezoidal sheets; iv) channel sheets; and v) Special-shaped sheets.

10. A floor system (100) for an aircraft, the floor system comprising: Aircraft floor device (10) according to one of the preceding claims; as well as A support device (102), the support device (102) comprising a plurality of floor supports (104); Wherein, the plurality of floor panels are carried by the floor support.

11. The system according to claim 10, wherein: The floor support comprises a longitudinal support profile for resting the floor panel on the support profile.

12. The system according to claim 10 or 11, wherein: The longitudinal support profile is arranged as a seat track resting on the transverse crossbeam; and Wherein, the panel rests on the seat track.

13. A system according to claim 10, 11 or 12, wherein: The floor system with at least one mountable support profile provides a modular truss structure.

14. An aircraft (200), comprising: Body (202); a wing assembly (204), the wing assembly (204) being attached to the fuselage; as well as a propulsion device (206) attached to at least one of the group of said fuselage and said wing devices; wherein a floor (208) for a cabin area or a cargo area is provided in the fuselage; and Thereby, the floor comprises at least one aircraft floor arrangement (10) according to one of claims 1 to 9 or a floor system (100) for an aircraft cabin according to one of claims 10 to 13.

15. A method (300) for customizing the load bearing capacity of an aircraft floor arrangement, the method (300) comprising the steps of: providing (302) a plurality of floor panels, the plurality of floor panels being provided with a plurality of joint points arranged at least along one direction; as well as providing (304) at least one supporting profile, the at least one supporting profile configured to reinforce at least one of the floor panels such that the load bearing capacity is increased; as well as One of the support profiles is mounted (306) to one of the floor panels via the joint point to reinforce the floor panel.

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