Mating structure for an aircraft fuselage
The combined structure of mounting plates, connecting frames, and stabilizers solves the problem of complex and inconvenient disassembly of aircraft fuselage parts, achieving efficient attachment and separation, and meeting the maintenance needs of fuel tanks in H2-powered aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- AIRBUS SPAIN SA
- Filing Date
- 2025-09-04
- Publication Date
- 2026-07-14
AI Technical Summary
In the existing technology, the connection structure of the aircraft fuselage is complex and not easy to disassemble, especially when it is necessary to regularly access the fuselage interior, making it difficult to achieve efficient connection and separation. This is particularly true for the maintenance and replacement of large fuel tanks in H2-powered aircraft.
The system employs a combination structure of mounting plates, connecting frames, and stabilizers. The mounting plates and connecting frames are attached to the complementary circumferential edges of the aircraft fuselage, and the stabilizers are correspondingly set in the transition section of the longitudinal beams. Combined with discrete single-sided fasteners, efficient attachment and separation are achieved.
It provides a safe and reliable connection method, reduces the number of connecting components, enables efficient attachment and disengagement, facilitates access to the internal components of the machine body, and meets the maintenance requirements of the H2 fuel tank.
Smart Images
Figure CN224491473U_ABST
Abstract
Description
Technical Field
[0001] This invention relates to a mating structure for an aircraft fuselage, specifically for providing a robust and secure connection between two aircraft fuselage sections, while allowing disassembly of the two fuselage sections to provide access to the aircraft fuselage interior for the preferred installation and removal of the LH2 fuel tank. Alternatively, this solution can be applied to other situations requiring periodic access.
[0002] The purpose of this invention is to provide access to internal components of an aircraft fuselage that are otherwise inaccessible, during maintenance or repair operations.
[0003] This invention is preferably applicable to the design, manufacture, operation and maintenance of aircraft fuselage components, particularly in H2-powered aircraft. Background Technology
[0004] In the context of the development of hydrogen-powered (H2-powered) aircraft, large fuel tanks need to be housed within the fuselage. Access to these tanks is required for maintenance, removal, and replacement operations.
[0005] In the design and manufacture of structural components for aircraft fuselages, rail connections are typically envisioned for creating permanent connections between two different parts of the fuselage. This new solution is envisioned to be applicable to both permanent and removable connections between different parts of the fuselage.
[0006] Track connections are made along the circumference of the parts to be connected. The structural assembly of these connected components is done using fasteners such as rivets, used for permanent solutions; this operation is called track stitching. To ensure the mechanical continuity of the assembled structure, the components must be in close contact at the joint. This means that the two components are precisely manufactured such that their shapes are identical or completely complementary at the joint interface, depending on whether the joint is end-to-end or achieved through interlocking.
[0007] In cargo aircraft, the conventional rail connections used to attach different fuselage sections to each other are usually heavy and complex mechanisms, and typically do not allow access to two different fuel tanks located on the forward and aft fuselage sections respectively. Summary of the Invention
[0008] In order to provide a solution to the above problems, the present invention relates to a mating structure for an aircraft fuselage.
[0009] According to the invention, the mating structure for the aircraft fuselage is configured to attach a first aircraft fuselage portion (e.g., a forward aircraft fuselage element) to a second aircraft fuselage portion (e.g., a rear aircraft fuselage element) along complementary circumferential edges of two aircraft fuselage portions.
[0010] The mating structures used for aircraft fuselages include:
[0011] - A ramp, wherein the ramp is configured to be attached to the inside of the aircraft fuselage skin, wherein the ramp includes an annular geometry, wherein the ramp is configured to protrude (or project) toward the second aircraft fuselage portion beyond the first circumferential edge of the first aircraft fuselage portion;
[0012] - A connecting frame, comprising a ring geometry and configured to be attached to the fuselage skin of the first aircraft fuselage via a siding at a first circumferential edge near the first aircraft fuselage portion;
[0013] - Multiple stabilizers, each including a body with two flaps, each stabilizer configured to connect a fuselage skin and a mounting plate to a connecting frame, wherein the stabilizers are configured to correspond to the end portions (transition sections) of the longitudinal beams of the aircraft fuselage, wherein the body includes a first side with a first side flap and a second side with a second side flap; wherein each stabilizer is configured to be attached to the connecting frame corresponding to the first side flap, and wherein each stabilizer is configured to be attached to the mounting plate corresponding to the second side flap. The stabilizers can be pre-installed in the connecting frame. In this case, for assembly / disassembly operations, the mounting plate can be first installed on the "fixed fuselage side," and then the stabilizer can be installed on the web of the connecting frame via the first side flap.
[0014] The above-described mating structure provides an efficient and feasible mounting configuration in which two aircraft fuselage sections can be attached to each other by attaching each stabilizer to the fuselage skin of the second aircraft fuselage section. The attachment / disengagement operation can be accomplished using discrete single-sided fasteners, discrete bolts and anchor nuts, or any combination or alternative attachment elements pre-installed on the mounting plate and / or stabilizers.
[0015] Furthermore, the aforementioned mating structure enables efficient attachment of the two aircraft fuselage sections.
[0016] The stabilizer enhances the transfer of loads to the web of the connecting frame, loads that arise from the moments generated during the transition of the longitudinal beams.
[0017] According to one possible aspect of the invention, the mating structure for an aircraft fuselage includes a plurality of connecting shovels, wherein a connecting frame is configured to be attached to a longitudinal beam of a first aircraft fuselage section via the connecting shovels, such that each connecting shovel is configured to be attached to the connecting frame (preferably to the bottom of the connecting frame) and a corresponding longitudinal beam.
[0018] According to the present invention, the mating structure for an aircraft fuselage may include a plurality of gaskets (or gasket components), wherein each connecting shovel is configured to be attached to a corresponding longitudinal beam via a gasket. These gasket components are designed to ensure the same thickness on both sides where they are connected to the shovel. They are typically made of PPS (polyphenylene sulfide resin), with a wide range of thicknesses selectable. They may also be protected with fiberglass on one or both sides.
[0019] According to a preferred embodiment of the mating structure (i.e., the object of the invention), the ramp includes a protruding edge having a plurality of grooves (or trimmed or shaped ramp edge areas), wherein each groove is configured to be positioned corresponding to an end portion (transition portion) of a longitudinal beam of the second aircraft fuselage section. According to this embodiment, preferably, the end portion of each longitudinal beam is inserted into a groove in the ramp.
[0020] These trimmed edge areas help prevent a single cross-section of only "fuselage skin thickness" from transferring loads between fuselage sections. By providing these trimmed edge areas, good fastening between the skin / plate or skin / longitudinal beam is ensured at the removal connection area.
[0021] According to a preferred embodiment, the mating structure includes a stabilizer on each side of each groove in the mounting plate. In other words, two stabilizers are configured to be located on each side of the ends of the longitudinal beams of the second aircraft fuselage section.
[0022] According to a possible embodiment of the mating structure, the body of each stabilizer includes a triangular wedge. Thus, the triangular wedge-shaped body of the stabilizer is positioned on a plane perpendicular to the web of the connecting frame (the middle portion of the connecting frame).
[0023] The first and second side flaps of each stabilizer can be bent at 90° relative to the main body. For the second side flap, this angle allows for adaptation to the cylindrical portion of the aircraft fuselage. Alternatively, the angles can be different to accommodate the tapered portion of the aircraft fuselage.
[0024] According to a preferred embodiment of the mating structure for an aircraft fuselage (the purpose of this invention), the connecting frame includes a "C-shaped" cross-sectional geometry, wherein the convex side of the connecting frame (the outer side of the connecting frame web) is configured to be oriented toward the second aircraft fuselage portion. However, according to an alternative embodiment, the connecting frame may include different cross-sectional geometries, such as a "J-shaped" or "T-shaped" cross-sectional geometry.
[0025] Preferably, the attachment of each stabilizer to its corresponding second side flap can be accessed from the outside of the aircraft fuselage skin.
[0026] This feature allows for more feasible assembly and disassembly operations of aircraft fuselage sections or parts.
[0027] Through the aforementioned mating structure, the attachment between the fixed side (in the first aircraft fuselage section) and the separable side (in the second aircraft fuselage section) of the fuselage skin of the two aircraft fuselage sections is accomplished through a single contact surface.
[0028] Furthermore, the aforementioned mating structure for the aircraft fuselage allows for a removable solution, either through an expanded maintenance solution approach or through a more typical removable solution with pre-installed bolts and anchor nuts on the detachable side. Alternatively, this concept can also be considered a permanent solution that offers the aforementioned advantages over other conventional solutions.
[0029] According to a preferred embodiment of the invention, the connecting frame consists of a single piece or component at each of its transverse portions.
[0030] The present invention also relates to an aircraft comprising the mating structure for the aircraft fuselage as described above.
[0031] Furthermore, the aircraft of the present invention includes longitudinal beams in the fuselage section, which may include, for example, a “Z-shaped” cross-sectional geometry, a “J-shaped” cross-sectional geometry, a “T-shaped” cross-sectional geometry, or an “Ω-shaped” cross-sectional geometry. Attached Figure Description
[0032] To better understand at least one embodiment of the present invention, the following set of figures is presented schematically and in a non-limiting manner.
[0033] Figure 1 A schematic diagram is shown of a first (front) aircraft fuselage element and a second (rear) aircraft fuselage element to be attached by means of a possible embodiment of a mating structure for an aircraft fuselage according to the present invention.
[0034] Figure 2 A schematic partial perspective view from the inside of two aircraft fuselage sections is shown, depicting a schematic diagram of a possible embodiment of a mating structure for an aircraft fuselage according to the present invention.
[0035] Figure 3 It shows Figure 2 A schematic plan view of the fitting structure used for the aircraft fuselage.
[0036] Figure 4 It shows Figure 2 A schematic cross-sectional view of the fitting structure used in the aircraft fuselage.
[0037] Figure 5 A schematic perspective view of the inside of two aircraft fuselage sections is shown, in which the second aircraft fuselage section is detached from the first aircraft fuselage. Detailed Implementation
[0038] As previously stated, the present invention relates to a mating structure for an aircraft fuselage.
[0039] The mating structure for aircraft fuselage, which is the object of this invention, allows for the safe and reliable attachment of two aircraft fuselage sections (201, 202) while reducing the number of connecting elements required to perform the attachment of the two aircraft fuselage sections (201, 202).
[0040] The mating structure for the aircraft fuselage, which is the object of this invention, also allows for efficient / feasible releasable attachment of two aircraft fuselage sections (201, 202), thereby allowing the two aircraft fuselage sections (201, 202) to separate when access is required for maintenance or inspection purposes, such as when access is required to access hydrogen deposits within one or more aircraft fuselage sections (201, 202).
[0041] Figure 1 The rear section of the aircraft fuselage is schematically depicted, in which two fuselage sections (201, 202) are attached to each other at a track connection (300), which is located at... Figure 1 The lines in the middle are marked as discontinuous.
[0042] Figure 2 The inner side of the fuselage skin (203) of two aircraft fuselage sections (201, 202) attached to each other at their respective circumferential edges (204, 205) by a possible embodiment of the mating structure of the present invention is shown.
[0043] like Figure 2 The schematic depiction of the mating structure for the aircraft fuselage includes a continuous connecting frame (100) having an annular or ring-shaped geometry and being configured to be attached to the first aircraft fuselage portion (201) at a first circumferential edge (204) near the first aircraft fuselage portion (201).
[0044] like Figure 2 As shown, the connecting frame (100) is configured to be located inside the fuselage skin (203), between the end of the longitudinal beam (206) and the first circumferential edge (204) of the first aircraft fuselage section (201).
[0045] The connection frame (100) may include (such as) Figure 2 and Figure 5(Clearly shown) The “C-shaped” cross-sectional geometry includes a head portion, a bottom portion, and a middle web portion, the concave side (the concave surface of the web portion) of which faces the inside of the first aircraft fuselage portion (201). However, although not shown in the figure, the connecting frame (100) may include different cross-sectional geometries, such as a “J-shaped” cross-sectional geometry.
[0046] The connecting frame (100) extends along the first perimeter toward the edge (204) and corresponds thereto, and is attached to the longitudinal beams (206) of the first aircraft fuselage section (201) by connecting shovels (101), which are attached to the connecting frame (100) (the bottom of the connecting frame) and each longitudinal beam (206).
[0047] The connecting frame (100) can be made as a single piece along its entire length (circumferential length) or as several parts (e.g., 4 parts) along its entire length (circumferential length).
[0048] The connecting frame (100) is preferably a continuous frame (made into a single part) at each cross section (transverse section) of the connecting frame (100).
[0049] Each connecting shovel (101) can be attached to the corresponding longitudinal beam (206) via a shim (102). This can help offset any differences in thickness that may exist at the bottom of the longitudinal beam / frame.
[0050] The attachment of each connecting shovel (101) to the connecting frame (100) (attached to the bottom of the frame (100)) can further serve as the attachment of the connecting frame (100) to the fuselage skin (203) of the first aircraft fuselage section (201).
[0051] In addition, the connecting frame (100) is attached to the fuselage skin (203) of the first aircraft fuselage section (201) through the intermediary of the mounting plate (103).
[0052] The ramp (103) includes an annular or ring-shaped geometry and is configured to protrude toward the second aircraft fuselage section (202) beyond the first circumferential edge (204) of the first aircraft fuselage section (201) and beyond the connecting frame (100).
[0053] The ramp (103) includes a protruding edge (104) with a plurality of grooves (105) or trims, wherein each groove (105) or trim is configured to be positioned corresponding to the end of the longitudinal beam (206) of the second aircraft fuselage section (202) (to the longitudinal beam transition).
[0054] Furthermore, the cooperating structure of the present invention includes a plurality of stabilizers (106).
[0055] like Figure 4and Figure 5 As shown, each stabilizer (106) includes a body having a generally triangular shape (triangular wedge). A first side flap (107) (or first side flange) (bent relative to the body, forming approximately 90° relative to the body of the stabilizer (106)) is provided on a first side of the body of the stabilizer (106); a second side flap (108) (or second side flange) (bent relative to the body, forming approximately 90° relative to the body of the stabilizer (106)) is provided on a second side of the body of the stabilizer (106). One of the side flanges is connected to the body (stabilizer web) at 90° and to the fuselage skin. In this case, the flange preferably includes a curved surface with a "hinge line" associated with the stabilizer web to match the geometry of the bent side flap.
[0056] Each stabilizer (106) is configured to be attached to the connecting frame (100) corresponding to the first side flap (107) (the convex side of the “C-shaped” geometry of the connecting frame (100).
[0057] In addition, such as Figure 3 and Figure 4 As illustrated, each stabilizer (106) is configured to be attached to the fuselage skin (203) of the second aircraft fuselage section (202) via a connecting plate (103) in relation to the second side flap (108).
[0058] The attachment of each stabilizer (106) to its corresponding second side flap (108) is preferably accessible from the outside of the aircraft fuselage skin (203), such that by operating the corresponding nuts and / or bolts through appropriate assembly or disassembly, the attachment of the stabilizer (106) to the aircraft fuselage skin (203) can be released, thereby allowing (e.g.) Figure 5 (Schematic illustration) Separation control of the second aircraft fuselage section (202) relative to the first aircraft fuselage section (201).
[0059] The stabilizer (106) is configured to be located on each side of each groove (105) of the mounting plate (103) (on each trimmed side) such that when the mating structure is used to connect the aircraft fuselage sections (201, 202) to each other, the stabilizer (106) is located on each side of the longitudinal beam (206) of the second aircraft fuselage section (202).
[0060] When using a mating structure (connecting the aircraft fuselage sections (201, 202) to each other), the second circumferential edge (205) of the second aircraft fuselage section (202) is positioned close to the first circumferential edge (204) of the first aircraft fuselage section (201).
Claims
1. A mating structure for an aircraft fuselage, configured to attach a first aircraft fuselage portion (201) to a second aircraft fuselage portion (202) along complementary circumferential edges of two aircraft fuselage portions, characterized in that, The mating structure for the aircraft fuselage includes: - A flap (103), wherein the flap (103) is configured to be attached to the inside of the aircraft fuselage skin (203), wherein the flap (103) includes an annular geometry, wherein the flap (103) is configured to protrude toward the second aircraft fuselage portion (202) beyond the first circumferential edge (204) of the first aircraft fuselage portion (201). - A connecting frame (100), comprising an annular geometry and configured to be attached to the fuselage skin (203) of the first aircraft fuselage portion (201) via the intermediary of the mounting plate (103) at the first circumferential edge (204) near the first aircraft fuselage portion (201), and; - A plurality of stabilizers (106), wherein each stabilizer (106) includes a body having two side flaps, wherein each stabilizer is configured to connect the aircraft fuselage skin (203) and the ramp (103) to the connecting frame (100), wherein the stabilizer (106) is configured to correspond to the end portion of the longitudinal beam (206) of the aircraft fuselage, wherein the body includes a first side having a first side flap (107) and a second side having a second side flap (108); wherein each stabilizer (106) is configured to be attached to the connecting frame (100) corresponding to the first side flap (107), and wherein each stabilizer (106) is configured to be attached to the ramp (103) corresponding to the second side flap (108).
2. The mating structure for an aircraft fuselage according to claim 1, characterized in that, The mating structure for the aircraft fuselage includes a plurality of connecting shovels (101), wherein each connecting shovel (101) is configured to be attached to the connecting frame (100) and a corresponding longitudinal beam (206).
3. The mating structure for an aircraft fuselage according to claim 2, characterized in that, The mating structure for the aircraft fuselage includes a plurality of gaskets (102), wherein each connecting shovel (101) is configured to be attached to a corresponding longitudinal beam (206) via the intermediary of the gasket (102).
4. The mating structure for an aircraft fuselage according to any one of claims 1-3, characterized in that, The mounting plate (103) includes a protruding edge (104) having a plurality of grooves (105), wherein each groove (105) is configured to be positioned corresponding to an end portion of a longitudinal beam (206) of the second aircraft fuselage section (202).
5. The mating structure for an aircraft fuselage according to claim 4, characterized in that, The mating structure for the aircraft fuselage includes a stabilizer (106) on each side of each groove (105) of the mounting plate (103).
6. The mating structure for an aircraft fuselage according to any one of claims 1-3, characterized in that, The body of each stabilizer (106) comprises a triangular wedge.
7. The mating structure for an aircraft fuselage according to any one of claims 1-3, characterized in that, The first side flap (107) and the second side flap (108) of each stabilizer (106) are bent at 90° relative to the main body.
8. The mating structure for an aircraft fuselage according to any one of claims 1-3, characterized in that, The connecting frame (100) includes a "C-shaped" cross-sectional geometry, wherein the convex side of the connecting frame (100) is configured to be oriented toward the second aircraft fuselage portion (202).
9. The mating structure for an aircraft fuselage according to any one of claims 1-3, characterized in that... The mating structure for the aircraft fuselage is configured such that the attachment of each stabilizer (106) to its corresponding second side flap (108) is accessible from the outside of the aircraft fuselage skin (203).
10. The mating structure of the aircraft fuselage according to any one of claims 1-3, characterized in that, The connecting frame (100) consists of a single piece at each of its transverse portions.
11. An aircraft, characterized in that, The aircraft includes a mating structure for the aircraft fuselage according to any one of claims 1-10.
12. The aircraft according to claim 11, characterized in that, The longitudinal beam (206) of the aircraft fuselage section includes a "Z-shaped" cross-sectional geometry.
13. The aircraft according to claim 11, characterized in that, The longitudinal beam (206) of the aircraft fuselage section includes a "J-shaped" cross-sectional geometry.
14. The aircraft according to claim 11, characterized in that, The longitudinal beam (206) of the aircraft fuselage section includes a "T-shaped" cross-sectional geometry.
15. The aircraft according to claim 11, characterized in that, The longitudinal beam (206) of the aircraft fuselage section includes an "Ω" shaped cross-sectional geometry.