Assembly structure for aircraft fuselage

Abstract

An assembly structure for an aircraft fuselage configured to attach a first aircraft fuselage element (201) to a second aircraft fuselage element (202) along a complementary cross-sectional perimeter (100) of both the first aircraft fuselage element (201) and the second aircraft fuselage element (201), where the assembly structure for an aircraft fuselage comprises: a plurality of first wedge-shaped elements (101) configured to engage the first and second aircraft fuselage elements (201, 202); the first aircraft fuselage element (201) has a first cross-sectional perimeter (100a) distributed along the first aircraft fuselage element (201); a plurality of second wedge-shaped elements (102) distributed along a second cross-sectional perimeter (100b) of the second aircraft fuselage element (202); and at least one docking band (300) configured to cover an outer side of the first aircraft fuselage element (201) and an outer side of the second aircraft fuselage element (202) corresponding to the complementary cross-sectional perimeter (100) of the first aircraft fuselage element (201) and the second aircraft fuselage element (202).

Description

Technical Field

[0001] This invention relates to an assembly structure for an aircraft fuselage, particularly for providing a robust and secure joint between two aircraft fuselage components, while allowing easy disassembly of the two components to enable access to the aircraft fuselage interior.

[0002] The assembly structure for an aircraft fuselage, which is the subject of this invention, allows easy access to components inside the aircraft fuselage that would otherwise be difficult to access in the event of maintenance or repair operations.

[0003] This invention is preferably applicable to the design, manufacture, operation and maintenance of aircraft fuselage components. Background Technology

[0004] In the design and manufacture of structural components for an aircraft fuselage, orbital joints are often considered for use in the production of joints between two different parts of the fuselage.

[0005] The orbital joint is made along the perimeter of the cross-section of the components to be connected. The structural assembly of the components thus connected is carried out using fasteners (such as rivets), an operation known as sewing orbital. To ensure the mechanical continuity of the structure assembled in this way, the components must be in close contact at the joint. This means that the two components are precisely manufactured such that at the joint interface, the shapes of the two components are identical or completely complementary, depending on whether the joint is end-to-end or interlocking.

[0006] Furthermore, in the context of developing hydrogen-powered aircraft, the fuselage needs to accommodate large fuel tanks. Access to these fuel tanks is required for maintenance, disassembly, and replacement operations.

[0007] As the hydrogen tank is currently under development, the maintenance requirements are not fixed, so it is unclear how to provide access to the hydrogen tank.

[0008] Within this scope, using rail joints (typically used to attach different parts of the fuselage) to provide access to the hydrogen tank is likely the first logical approach. However, existing solutions for rail joints are either unsuitable for industrial components used to maintain access or are heavy, complex mechanisms in cargo aircraft. Summary of the Invention

[0009] To address the aforementioned problems, the present invention relates to an assembly structure for an aircraft fuselage.

[0010] The assembly structure for an aircraft fuselage, which is the object of the present invention, is configured to attach the first aircraft fuselage element to the second aircraft fuselage element along the perimeter of the respective complementary cross-sections of the first and second aircraft fuselage elements.

[0011] In a novel manner, the assembly structure for an aircraft fuselage, which is the object of this invention, includes:

[0012] - A plurality of first wedge elements (e.g., a plurality of convex wedge elements) configured to be distributed along the perimeter of a first cross section of a first aircraft fuselage element, each first wedge element including a first portion and a second portion, the first portion being configured to be attached to the inside of the first aircraft fuselage element, the second portion being inclined relative to the first portion, and the second portion being configured to protrude outward from the first aircraft fuselage element beyond the perimeter of the first cross section.

[0013] - A plurality of second wedge-shaped elements (e.g., a plurality of concave wedge-shaped elements) configured to be distributed along the perimeter of a second cross-section of a second aircraft fuselage element, each second wedge-shaped element comprising a first portion and a second portion, the first portion being configured to be attached to the inner side of the second aircraft fuselage element, and the second portion being inclined relative to the first portion; and

[0014] - At least one mating strip configured to cover the outer sides of the first and second aircraft fuselage elements, corresponding to the complementary cross-sectional perimeters of the first and second aircraft fuselage elements (thus providing continuity of the aircraft fuselage skin corresponding to the joint between the two aircraft fuselage elements); and

[0015] - Multiple fasteners configured to attach the mating strip to the fuselage skin.

[0016] The above assembly structure provides an easy-to-install structure in which two aircraft fuselage components can be attached to each other by easily placing the first wedge element and the second wedge element in correspondence, thereby guiding the relative movement between the two aircraft fuselage components, and using the mating strip as a structural element for transmitting forces between the two aircraft fuselage components.

[0017] Furthermore, the complementary geometry of the first and second wedge elements allows for easy guidance of relative movement between the two aircraft fuselage elements, thereby allowing easy access to and / or separation of the two aircraft fuselage elements to permit entry for inspection, maintenance, and / or repair purposes.

[0018] Therefore, the assembly structure of the aircraft fuselage may include a plurality of first fasteners with floating nuts, which are arranged and / or configured to attach the mating strip to the fuselage skin.

[0019] Furthermore, the assembly structure of the aircraft fuselage may therefore include multiple self-aligning fasteners arranged and / or configured to attach the mating strip to the fuselage skin.

[0020] Self-aligning fasteners facilitate fine adjustments when installing and attaching the mating strip to the fuselage skin.

[0021] According to one possible aspect of the invention, each second wedge element is configured such that its second portion is correspondingly attached to a corresponding second portion of the first wedge element.

[0022] Furthermore, the second portion of each wedge element preferably includes a three-sided opening volume with sidewalls forming a pyramid shape. Thus, the pyramid shape of the first wedge element (convex wedge element) complements the pyramid shape of the second wedge element (concave wedge element), thereby acting as a guiding element in the approach and separation maneuvers between the two aircraft fuselage elements.

[0023] The second portion of the first wedge element can be configured to be attached to the second portion of the second wedge element by a plurality of self-aligning fasteners distributed along the surface of the second portion of each wedge element.

[0024] The wedge-shaped elements are preferably configured to be located between the struts of the aircraft fuselage.

[0025] Specifically, in a preferred embodiment of the invention, each wedge-shaped element of the assembly structure for the aircraft fuselage is configured to be located between every two stringers of the aircraft fuselage. Attached Figure Description

[0026] To better understand at least one embodiment of the present invention, the following figures are provided in a schematic and non-limiting manner.

[0027] Figure 1 A schematic diagram is shown of a rear fuselage element and a forward fuselage element attached by a possible embodiment of an assembly structure for an aircraft fuselage according to the present invention.

[0028] Figure 2 It shows that according to Figure 1 A schematic diagram of section AA in the diagram.

[0029] Figure 3 A possible embodiment of an assembly structure for an aircraft fuselage according to the present invention is shown, in which a schematic diagram of a second wedge element and a first wedge element can be seen.

[0030] Figure 4a A schematic side view of a first wedge-shaped element is shown, representing a possible embodiment of an assembly structure for an aircraft fuselage according to the present invention.

[0031] Figure 4b A schematic front view of a first wedge-shaped element is shown, representing a possible embodiment of an assembly structure for an aircraft fuselage according to the present invention. Detailed Implementation

[0032] As previously stated, the present invention relates to an assembly structure for an aircraft fuselage.

[0033] The assembly structure for an aircraft fuselage, which is the subject of this invention, allows for the safe and reliable attachment of two aircraft fuselage components 201, 202.

[0034] The assembly structure for an aircraft fuselage, which is the subject of this invention, also allows for easy release of the attachments of the two aircraft fuselage components 201, 202, thereby allowing the two aircraft fuselage components 201, 202 to be separated when access is required for maintenance or inspection purposes (e.g., when access to hydrogen storage inside one or more aircraft fuselage components 201, 202 is required).

[0035] According to a preferred embodiment of the present invention, such as Figure 1 As shown, the assembly structure for the aircraft fuselage includes a plurality of wedge-shaped elements 101, 102, which are orbitally distributed along the cross-sectional perimeter 100 of at least two aircraft fuselage elements 201, 202 to be attached to each other.

[0036] Therefore, when the first aircraft fuselage element 201 is attached to the second aircraft fuselage element 202, the first aircraft fuselage element 201 may include a plurality of first wedge-shaped elements 101 (which may be formed as convex wedge-shaped elements) distributed along its cross-sectional perimeter 100, the plurality of first wedge-shaped elements 101 being configured to be attached to a plurality of second wedge-shaped elements 102 (which may be formed as concave wedge-shaped elements) uniformly distributed along the cross-sectional perimeter 100 of the second aircraft fuselage element 202.

[0037] Each first wedge element 101 includes a first portion 101a attached to the inside of the first aircraft fuselage element 201 and a second portion 101b inclined relative to the first portion 101a, the second portion protruding outward from the first aircraft fuselage element 201 beyond the first cross-sectional perimeter 100a.

[0038] In addition, each second wedge element 102 includes a first portion 102a attached to the inside of the second aircraft fuselage element 202 and a second portion 102b inclined relative to the first portion 102a.

[0039] The first wedge element 101 and the second wedge element 102 serve as guiding elements for the relative movement of the first aircraft fuselage element 201 and the second aircraft fuselage element 202.

[0040] According to one possible embodiment of the invention, each second wedge element 102 is configured to be attached to a corresponding second portion 101b of the first wedge element 101 via its second portion 102b.

[0041] The assembly structure includes at least one mating strip 300, which is configured as a structural element to transmit forces and provide continuity between two aircraft fuselage components 201, 202. The mating strip 300 is configured to be attached to the aircraft fuselage skin 400 by fasteners 601, 602 in the portion corresponding to the engagement of the two aircraft fuselage components 201, 202.

[0042] Therefore, the docking strip 300 is configured to attach two aircraft fuselage components 201, 202 to each other.

[0043] Figure 2 It shows that according to Figure 1 A schematic diagram of the AA section, wherein multiple first fasteners 601 with floating nuts are arranged to attach the mating strip 300 to the fuselage skin 400.

[0044] In addition, multiple self-aligning fasteners 602 are arranged to attach the mating strip 300 to the fuselage skin 400.

[0045] like Figure 2 As shown, the fuselage skin 400 is kept flat by surface wedges 500 (thus ensuring aerodynamic shape). This solution has minimal aerodynamic penalty. Alternatively, the fuselage skin 400 may include stage sections with gradually decreasing widths to avoid compromising fuselage aerodynamics.

[0046] The number of self-aligning fasteners 602 should be determined empirically to be the minimum required. A solution with two such fasteners per line is considered a robust approach, but the actual required number may be much lower. Choosing the middle position of these joints amplifies the adaptation effect and achieves better load distribution (since a larger diameter results in a greater load transfer, a middle position helps reduce this effect, and the load distribution in the fastener line is more even).

[0047] Figure 3 A side view of wedge elements 101 and 102, namely the first wedge element 101 and the second wedge element 102, is schematically shown.

[0048] Figure 4a The first wedge-shaped element 101 is schematically depicted.

[0049] The second parts 101b and 102b of the wedge-shaped elements 101 and 102 include a pyramid shape (both the horizontal and side walls are inclined, thus accommodating displacement of the fuselage section in the radial and tangential directions), such as Figure 4b The front view of the first wedge-shaped element 101 is shown.

[0050] The first wedge element 101 can be attached to the second wedge element 102 by a plurality of self-aligning fasteners 602 distributed along the surfaces of the second portions 101b, 102b of the wedge elements 101, 102.

[0051] Wedge elements 101 and 102 are located between stringers 700. If load continuity between wedge elements 101 and 102 is relevant, or if the track joint requires an out-of-plane stabilizer, a self-aligning fastener 602 for attaching the first wedge element 101 to the second wedge element 102 can be used.

[0052] The number of wedge elements 101, 102 provided along the perimeter 100 of the cross section will be determined based on assembly and structural requirements, with at least 3-4 considered. At the other extreme of this range, one wedge element may be provided between every two stringers 700.

Claims

1. Assembly structure for an aircraft fuselage, configured to attach a first aircraft fuselage element (201) to a second aircraft fuselage element (202) along a complementary cross-sectional periphery (100) of both aircraft fuselage elements, wherein, The assembly structure for aircraft fuselages is characterized in that it comprises: - a plurality of first wedge elements (101) configured to be distributed along a first cross-sectional perimeter (100a) of the first aircraft fuselage element (201), each first wedge element (101) comprising a first portion (101a) configured to be attached to an inner side of the first aircraft fuselage element (201) and a second portion (101b) inclined with respect to the first portion (101a) and configured to project outwardly from the first aircraft fuselage element (201) beyond the first cross-sectional perimeter (100a); - a plurality of second wedge elements (102) configured to be distributed along a second cross-sectional perimeter (100b) of the second aircraft fuselage element (202), each second wedge element (102) comprising a first portion (102a) configured to be attached to an inner side of the second aircraft fuselage element (202) and a second portion (102b) inclined with respect to the first portion (102a); and - at least one interfacing band (300) configured to cover an outer side of the first aircraft fuselage element (201) and an outer side of the second aircraft fuselage element (202) corresponding to the complementary cross-sectional perimeters (100) of the first aircraft fuselage element (201) and the second aircraft fuselage element (202); and - a plurality of fasteners (601, 602) configured to attach the interfacing band (300) to a fuselage skin (400).

2. The assembly structure for an aircraft fuselage according to claim 1, characterized in that It comprises a plurality of first fasteners with floating nut (601) arranged to attach the interfacing band (300) to the fuselage skin (400).

3. The assembly structure for an aircraft fuselage according to claim 1 or 2, characterized in that It comprises a plurality of self-aligning fasteners (602) arranged to attach the interfacing band (300) to the fuselage skin (400).

4. Assembly structure for an aircraft fuselage according to any one of the preceding claims, characterized in that Each second wedge element (102) is configured so that its second portion (102b) is attached to a corresponding second portion (101b) of the first wedge element (101).

5. Assembly structure for an aircraft fuselage according to any one of the preceding claims, characterized in that, The second portions (101b, 102b) of the first wedge elements (101) and the second wedge elements (102) comprise a three-sided opening volume forming a pyramid shape.

6. Assembly structure for an aircraft fuselage according to any one of the preceding claims, characterized in that The first wedge elements (101) are configured to be attached to the second wedge elements (102) by means of a plurality of self-aligning fasteners (602) distributed along the surfaces of the second portions (101b, 102b) of the first wedge elements (101) and the second wedge elements (102).

7. Assembly structure for an aircraft fuselage according to any one of the preceding claims, characterized in that The first wedge elements (101) and the second wedge elements (102) are configured to be located between stringers (700) of the aircraft fuselage.

8. The assembly structure for an aircraft fuselage according to claim 7, characterized in that Each wedge element (101, 102) is configured to be located between every two stringers (700) of the aircraft fuselage.

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