Integrated connection joint structure and method of connecting same

Abstract

The application belongs to the technical field of aircraft structure connecting joint, and discloses an integrated connecting joint structure and a connecting method thereof. The integrated connecting joint structure is used for connecting a cargo compartment cross beam and a fuselage bulkhead of an aircraft, and comprises a joint body made of a metal material and located between the cargo compartment cross beam and the fuselage bulkhead. The joint body comprises a main plate body, a first plate body and a second plate body. One side of the main plate body in a first direction is provided with a first site and a second site, and the first site and the second site are arranged at intervals along a second direction. The fuselage bulkhead can be detachably connected to one side of the main plate body along a third direction. The first plate body is located at the first site, and the cargo compartment cross beam can be detachably connected to the first plate body. The second plate body is located at the second site, and a lateral guide rail can be detachably connected to the second plate body and extends along the third direction. The integrated connecting joint structure has high installation efficiency and high space utilization rate, and the lateral guide rail is convenient to disassemble and assemble. The integrated connecting joint structure has high force transmission efficiency and strong bearing capacity.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural connection joint technology, and in particular to an integrated connection joint structure and its connection method. Background Technology

[0002] The cargo hold floor beam assemblies of civil aircraft need to be connected to the bulkhead via connectors. Typically, the connectors for the cargo hold beams are C-type composite joints. To meet fall protection requirements, a titanium alloy fall protection reinforcement plate is added between the joint and the cargo hold beam to strengthen the fuselage bulkhead. Simultaneously, the cargo system requires side rails for cargo containers to be installed at the ends of the cargo hold beams. The fuselage structure must be designed with side rail mounting brackets and provide space for bracket installation, while also meeting the requirements for rapid assembly and disassembly of the cargo system's side rails.

[0003] Existing aircraft structures require an additional connecting joint to install the lateral guide rails to the fuselage bulkhead. This involves connecting the cargo hold beam and the lateral guide rails to the bulkhead via the connecting joints of the cargo hold beam and the lateral guide rails. This results in numerous parts, multiple assembly and positioning steps, and low assembly efficiency. Furthermore, there is insufficient installation space at the connecting joint of the cargo hold beam, making the installation of the lateral guide rails difficult.

[0004] Therefore, there is an urgent need to propose an integrated connection joint structure and its connection method to solve the above problems. Summary of the Invention

[0005] The first objective of this invention is to provide an integrated connection joint structure that can not only connect the cargo hold beams to the fuselage bulkhead, but also provide installation positions for the side guide rails. This reduces the number of joints or brackets used for structural connection and installation, improves the efficiency of structural installation, and increases the utilization rate of the internal space of the fuselage. Furthermore, the side guide rails are easy to install and remove, have high force transmission efficiency, and strong load-bearing capacity.

[0006] To achieve this objective, the present invention adopts the following technical solution:

[0007] An integrated connecting joint structure is used to connect the cargo hold beam and the fuselage bulkhead of an aircraft. The integrated connecting joint structure includes a joint body made of metal. The joint body is located between the cargo hold beam and the fuselage bulkhead. The joint body includes:

[0008] The motherboard body has a first point and a second point on one side in a first direction, and the first point and the second point are spaced apart along the second direction. The chassis frame can be detachably connected to one side of the motherboard body along a third direction. The first direction is the width direction of the motherboard body, the second direction is the length direction of the motherboard body, and the third direction is the thickness direction of the motherboard body.

[0009] A first plate, located at the first position, wherein the cargo hold beam is detachably connected to the first plate;

[0010] A second plate is located at the second position, and a lateral guide rail is detachably connected to the second plate and extends along the third direction.

[0011] As an optional technical solution for the integrated connection joint structure, the cargo hold crossbeam and the fuselage bulkhead are located on the same side of the main body along the third direction, and the web of the cargo hold crossbeam is connected to the first plate; the second plate is provided with a mounting surface, which is located in the plane containing the second direction and the third direction.

[0012] As an optional technical solution for the integrated connection joint structure, the end of the first plate away from the second plate is inclined in the direction away from the body frame along the first direction; along the first direction, the mounting surface protrudes from the end of the first plate facing the second plate.

[0013] As an optional technical solution for the integrated connection joint structure, the first plate body is provided with a first reinforcing plate on the side away from the main plate body along the first direction. The first reinforcing plate extends along the third direction toward the side away from the web plate of the cargo hold beam, so that the first reinforcing plate can abut against the inner side of the wing plate of the cargo hold beam.

[0014] As an optional technical solution for an integrated connection joint structure, the first reinforcing plate has an arc transition surface between the side surface of the first reinforcing plate away from the main body and the mounting surface.

[0015] As an optional technical solution for an integrated connection joint structure, the mounting surface is adapted to the connecting plate surface of the side guide rail, the connecting plate surface is provided with a connecting hole, the mounting surface is provided with a first mounting hole, the connecting hole corresponds to the first mounting hole, and fasteners are sequentially passed through the connecting hole and the first mounting hole to connect the side guide rail and the second plate.

[0016] As an optional technical solution for an integrated connection joint structure, the first mounting hole is provided with an internal thread, the outer wall of the fastener is provided with an external thread, the internal thread is adapted to the external thread, and the fastener connects the side guide rail and the second plate through the external thread and the internal thread.

[0017] As an optional technical solution for the integrated connector structure, the integrated connector structure further includes a mounting component, which is located inside the second plate and is directly opposite to the first mounting hole. The fastener passes through the connection hole and the first mounting hole in sequence and is connected to the mounting component.

[0018] As an optional technical solution for the integrated connection joint structure, the second plate has a second mounting hole on its side wall, which communicates with the first mounting hole. The mounting assembly includes a cylindrical nut and a cover. The cylindrical nut is located inside the second mounting hole, and the cover is placed on the side of the cylindrical nut facing the mounting surface. The opposite edges of the cover are provided with folded edges, which can hook onto the opposite sides of the outer edge of the opening of the second mounting hole. The cylindrical nut has an internal thread, and the outer wall of the fastener has an external thread that matches the internal thread. The fastener passes through the cover and the first mounting hole and is threadedly connected to the cylindrical nut.

[0019] The second objective of this invention is to provide a connection method for an integrated connector structure that can improve the efficiency of structure installation.

[0020] To achieve this objective, the present invention adopts the following technical solution:

[0021] The method for connecting the integrated connector structure, using the aforementioned integrated connector structure to connect the cargo hold beam, the fuselage bulkhead, and the side guide rail, includes the following steps:

[0022] S1: Connect the first plate of the connector body to the cargo hold crossbeam to form an assembly of the cargo hold crossbeam and the connector body;

[0023] S2: The assembly is installed into the machine body as a component using a positioning fixture, and the main board is connected to the machine body frame along one side of the third direction.

[0024] S3: Connect the side guide rail to the second plate.

[0025] The beneficial effects of this invention are:

[0026] The integrated connection joint structure provided by this invention is used to connect the cargo hold beam and the fuselage bulkhead of an aircraft, and includes a joint body made of metal. The joint body includes a main plate, a first plate, and a second plate. The main plate is used to connect to the fuselage bulkhead. The first and second plates are spaced apart on one side of the main plate and are used to connect the cargo hold beam and the side guide rail, respectively, so that both the cargo hold beam and the side guide rail can be installed onto the fuselage bulkhead, thereby transferring the cargo load and the load on the side guide rail to the fuselage bulkhead in the form of shear force. Therefore, this integrated connection joint structure can not only undertake the connection function between the cargo hold beam and the fuselage bulkhead, but also provide an installation position for the side guide rail (second plate), reducing the number of joints or brackets used for structural connection and installation, improving the efficiency of structural installation, and improving the utilization rate of the internal space of the fuselage.

[0027] Secondly, the end of the cargo hold beam is usually connected to the fuselage bulkhead, so the end of the cargo hold beam is connected to the first plate. The second plate is spaced apart from the first plate to reserve operating space for the side guide rails, which facilitates the disassembly, assembly and maintenance of the side guide rails.

[0028] Furthermore, the joint body, as an integrated structure made of metal, has high force transmission efficiency and strong load-bearing capacity, eliminating the need for components such as anti-fall reinforcement. Attached Figure Description

[0029] Figure 1 This is an exploded view of the integrated connection joint structure provided in an embodiment of the present invention;

[0030] Figure 2 This is an assembly drawing of the integrated connecting joint structure provided in this embodiment of the invention, which connects the cargo hold crossbeam, fuselage bulkhead, and side guide rails.

[0031] Figure 3 This is a schematic diagram of the assembly side guide rail of the integrated connection joint structure provided in the embodiment of the present invention;

[0032] Figure 4 This is an exploded view of the installation component provided in an embodiment of the present invention.

[0033] In the picture:

[0034] 10. Cargo hold beams; 20. Fuselage bulkheads; 30. Side guide rails;

[0035] 100. Connector body; 110. Main body; 111. Second reinforcing plate; 120. First plate; 121. First reinforcing plate; 130. Second plate; 131. Mounting surface; 132. First mounting hole; 133. Second mounting hole; 200. Mounting assembly; 210. Cylindrical nut; 220. Cover. Detailed Implementation

[0036] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0037] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0038] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0039] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0040] This embodiment provides an integrated connection joint structure, which can not only connect the cargo hold beam to the fuselage bulkhead, but also provide an installation position for the side guide rails. This reduces the number of joints or brackets used for structural connection and installation, improves the efficiency of structural installation, and increases the utilization rate of the internal space of the fuselage. In addition, the side guide rails are easy to install and remove, have high force transmission efficiency, and strong load-bearing capacity.

[0041] Specifically, such as Figures 1 to 3As shown, the integrated connector structure is used to connect the cargo hold beam 10 and the fuselage bulkhead 20 of an aircraft. It includes a connector body 100, which is made of metal and located between the cargo hold beam 10 and the fuselage bulkhead 20. The connector body 100 includes a main plate 110, a first plate 120, and a second plate 130. The main plate 110 has a first point and a second point on one side in a first direction, and the first point and the second point are spaced apart along a second direction. The fuselage bulkhead 20 can be detachably connected to the main plate 110 on one side in a third direction. The first plate 120 is located at the first point, and the cargo hold beam 10 can be detachably connected to the first plate 120. The second plate 130 is located at the second point, and a lateral guide rail 30 can be detachably connected to the second plate 130, extending along a third direction.

[0042] It should be noted that the first direction is the width direction of the motherboard body 110, the second direction is the length direction of the motherboard body 110, and the third direction is the thickness direction of the motherboard body 110.

[0043] Based on the above design, the connector body 100 is located between the cargo hold beam 10 and the fuselage bulkhead 20. The main body 110 is used to connect the fuselage bulkhead 20. The first plate 120 and the second plate 130 are spaced apart on one side of the main body 110 and are used to connect the cargo hold beam 10 and the side guide rail 30, respectively. This allows both the cargo hold beam 10 and the side guide rail 30 to be installed onto the fuselage bulkhead 20, thereby transferring the cargo load and the load on the side guide rail 30 to the fuselage bulkhead 20 in the form of shear force. Therefore, this integrated connector structure can not only connect the cargo hold beam 10 and the fuselage bulkhead 20, but also provide an installation position for the side guide rail 30 (second plate 130), reducing the number of joints or brackets used for structural connection and installation, improving the efficiency of structural installation, and increasing the utilization rate of the internal space of the fuselage. Secondly, the end of the cargo hold beam 10 is typically connected to the fuselage bulkhead 20, thus the end of the cargo hold beam 10 is connected to the first plate 120. The second plate 130 and the first plate 120 are spaced apart to reserve operating space for the side guide rail 30, facilitating the disassembly, assembly, and maintenance of the side guide rail 30. Furthermore, the joint body 100, as an integrated structure made of metal, has high force transmission efficiency and strong load-bearing capacity, eliminating the need for components such as anti-fall reinforcement.

[0044] Furthermore, the cargo hold beam 10 and the fuselage bulkhead 20 are located on the same side of the main body 110 along the third direction, and the web of the cargo hold beam 10 is connected to the first plate 120. That is, both the cargo hold beam 10 and the fuselage bulkhead 20 are located on the outer side of the main body 110 (more precisely, the cargo hold beam 10 is located on the outer side of the first plate 120). The web of the cargo hold beam 10 can be fitted and connected to one side surface of the first plate 120. The second plate 130 is provided with a mounting surface 131, which is located on the plane of the second direction and the third direction. The mounting surface 131, which is specially set for the side guide rail 30, is different from the plane where the cargo hold beam 10 and the fuselage bulkhead 20 are located, which facilitates the disassembly and installation of the side guide rail 30.

[0045] Optionally, the end of the first plate 120 facing away from the second plate 130 is inclined in the first direction toward the direction away from the fuselage bulkhead 20, providing more space for the installation of the cargo hold beam 10; along the first direction, the mounting surface 131 protrudes from the end of the first plate 120 facing the second plate 130, that is, there is a height difference between the mounting surface 131 and the end of the first plate 120 facing the second plate 130, further providing installation and operation space for the side guide rail 30.

[0046] Optionally, the first plate 120 is provided with a first reinforcing plate 121 on the side away from the main plate 110 along the first direction. The first reinforcing plate 121 extends along the third direction toward the side away from the web of the cargo hold beam 10, so that the first reinforcing plate 121 can abut against the inner side of the wing plate of the cargo hold beam 10, increasing the contact area between the first plate 120 and the cargo hold beam 10, and also increasing the structural strength of the first plate 120, thereby improving the installation strength of the cargo hold beam 10.

[0047] Furthermore, a second reinforcing plate 111 is provided on the side of the main body 110 facing away from the cargo hold crossbeam 10 (i.e., the inner side of the main body 110). The second reinforcing plate 111, the first reinforcing plate 121, and the second plate 130 divide the inner sides of the main body 110 and the first plate 120 into multiple frames, thereby strengthening the structural strength of the main body 110 and the first plate 120. Among them, multiple reinforcing ribs are provided in the frames of the first plate 120 to prevent the first plate 120 from deforming when it is connected to the cargo hold crossbeam 10.

[0048] Furthermore, the surface of the first reinforcing plate 121 facing away from the main body 110 is provided with an arc transition surface between it and the mounting surface 131, which improves the drop resistance of the connector body 100.

[0049] Optionally, the mounting surface 131 is adapted to the connecting plate surface of the side guide rail 30. The connecting plate surface is provided with a connecting hole, and the mounting surface 131 is provided with a first mounting hole 132. The connecting hole and the first mounting hole 132 correspond to each other. Fasteners are sequentially passed through the connecting hole and the first mounting hole 132 to connect the side guide rail 30 and the second plate 130, which can realize quick disassembly and assembly of the side guide rail 30 on one side.

[0050] Furthermore, each of the four corners of the mounting surface 131 is provided with a first mounting hole 132, and the connecting holes and fasteners correspond one-to-one with the first mounting holes 132, increasing the connection strength between the side guide rail 30 and the second plate 130. Of course, the number of first mounting holes 132 can also be two, three, or five, etc., with multiple first mounting holes 132 evenly spaced along the four edges of the mounting surface 131.

[0051] In one specific implementation, the first mounting hole 132 is provided with an internal thread, and the outer wall of the fastener is provided with an external thread. The internal thread and the external thread are compatible, and the fastener is connected to the side guide rail 30 and the second plate 130 through the external thread and the internal thread. The structural processing can be completed by drilling holes in the connecting plate surface of the side guide rail 30 and the threaded holes in the second plate 130, which is convenient.

[0052] In this implementation plan, such as Figure 1 and Figure 4 As shown, the integrated connector structure also includes a mounting component 200, which is located inside the second plate 130 and directly opposite the first mounting hole 132. Fasteners pass through the connection hole and the first mounting hole 132 in sequence and are connected to the mounting component 200. Compared to the fasteners directly mating with the first mounting hole 132, the mounting component 200 avoids the need to replace the entire connector body 100 if the first mounting is damaged.

[0053] Specifically, the second plate 130 has a second mounting hole 133 on its side wall, which communicates with the first mounting hole 132. The mounting assembly 200 includes a cylindrical nut 210 and a cover 220. The cylindrical nut 210 is located inside the second mounting hole 133, and the cover 220 covers the side of the cylindrical nut 210 facing the mounting surface 131. The opposite sides of the cover 220 are provided with folded edges, which can hook onto the opposite sides of the outer edge of the opening of the second mounting hole 133, preventing the cover 220 and the cylindrical nut 210 from misaligning. In particular, in this embodiment, two second mounting holes 133 are provided on one side of the second plate 130, and the mounting assembly 200 is installed into the second mounting holes 133 along a third direction.

[0054] The cylindrical nut 210 has an internal thread, and the outer wall of the fastener has an external thread. The external thread is compatible with the internal thread. The fastener passes through the cover 220 and the first mounting hole 132 and is threadedly connected to the cylindrical nut 210. The fastener and the cylindrical nut 210 cooperate to connect the side guide rail 30 and the second plate 130, which is simple to connect and can increase the contact area between the fastener and the second plate 130, thereby improving the installation strength.

[0055] In this embodiment, the mounting component 200 can be rotated and adjusted within the second mounting hole 133 so that the axis of the internal thread coincides with the axis of the first mounting hole 132, which facilitates the fastener to pass through the first mounting hole 132 and the internal thread connection of the cylindrical nut 210.

[0056] This embodiment also provides a connection method for an integrated connector structure, which can improve the efficiency of structure installation.

[0057] Specifically, the connection method of this integrated connection joint structure uses the aforementioned integrated connection joint structure to connect the cargo hold beam 10, the fuselage bulkhead 20, and the side guide rail 30. The method includes the following steps:

[0058] S1: Connect the first plate 120 of the connector body 100 to the cargo hold crossbeam 10 to form an assembly of the cargo hold crossbeam 10 and the connector body 100, so as to avoid the parts from being scattered.

[0059] S2: The assembly is installed into the machine body as a component using a positioning fixture. After positioning, the main body 110 is connected to the machine body frame 20 along one side of the third direction.

[0060] S3: Connect the side guide rail 30 to the second plate 130.

[0061] Specifically, before the cargo hold beam 10 is assembled into the fuselage, the integrated connecting joint structure is first assembled and connected to the cargo hold beam 10, and the cargo hold beam 10, the integrated connecting joint structure, and other related components form an assembly; then, the assembly is installed into the fuselage as a component, requiring only one positioning at this time, resulting in high installation efficiency; finally, the side guide rail 30 is installed onto the second plate 130 specially designed by the integrated connecting joint structure, completing the installation of the cargo hold beam 10 and the side guide rail 30.

[0062] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. An integrated connecting joint structure for connecting the cargo hold beam (10) and the fuselage bulkhead (20) of an aircraft, characterized in that, The integrated connection joint structure includes a joint body (100), which is made of metal. The joint body (100) is located between the cargo hold beam (10) and the fuselage bulkhead (20). The joint body (100) includes: The main body (110) has a first point and a second point on one side in a first direction, and the first point and the second point are spaced apart along the second direction. The fuselage frame (20) is detachably connected to one side of the main body (110) along a third direction. The cargo hold beam (10) and the fuselage frame (20) are located on the same side of the main body (110) along the third direction. The first direction is the width direction of the main body (110), the second direction is the length direction of the main body (110), and the third direction is the thickness direction of the main body (110). A first plate (120) is located at the first position. The web of the cargo hold beam (10) is detachably connected to the first plate (120). The first plate (120) is provided with a first reinforcing plate (121) on the side away from the main plate (110) along the first direction. The first reinforcing plate (121) extends along the third direction toward the side away from the web of the cargo hold beam (10), so that the first reinforcing plate (121) can abut against the inner side of the wing plate of the cargo hold beam (10). The second plate (130) is located at the second position. A side guide rail (30) is detachably connected to the second plate (130) and extends along the third direction. The second plate (130) is provided with a mounting surface (131) located in the plane containing the second direction and the third direction. The end of the first plate (120) away from the second plate (130) is inclined in the direction away from the fuselage frame (20) along the first direction. Along the first direction, the mounting surface (131) protrudes from the end of the first plate (120) facing the second plate (130). The side surface of the first reinforcing plate (121) away from the main plate (110) is provided with an arc transition surface between it and the mounting surface (131).

2. The integrated connector structure according to claim 1, characterized in that, The mounting surface (131) is adapted to the connecting plate surface of the side guide rail (30). The connecting plate surface is provided with a connecting hole, and the mounting surface (131) is provided with a first mounting hole (132). The connecting hole corresponds to the first mounting hole (132). Fasteners pass through the connecting hole and the first mounting hole (132) in sequence to connect the side guide rail (30) and the second plate (130).

3. The integrated connector structure according to claim 2, characterized in that, The first mounting hole (132) is provided with an internal thread, and the outer wall of the fastener is provided with an external thread. The internal thread is adapted to the external thread, and the fastener is connected to the side guide rail (30) and the second plate (130) through the external thread and the internal thread.

4. The integrated connector structure according to claim 2, characterized in that, The integrated connection joint structure also includes a mounting component (200), which is located inside the second plate (130) and is directly opposite to the first mounting hole (132). The fastener passes through the connection hole and the first mounting hole (132) in sequence and is connected to the mounting component (200).

5. The integrated connector structure according to claim 4, characterized in that, The second plate (130) has a second mounting hole (133) on its side wall, which communicates with the first mounting hole (132). The mounting assembly (200) includes a cylindrical nut (210) and a cover (220). The cylindrical nut (210) is located in the second mounting hole (133), and the cover (220) covers the side of the cylindrical nut (210) facing the mounting surface (131). Both sides of the cover (220) are provided with folded edges. The cylindrical nut (210) has an internal thread, and the outer wall of the fastener has an external thread. The external thread is adapted to the internal thread. The fastener passes through the cover (220) and the first mounting hole (132) and is threadedly connected to the cylindrical nut (210).

6. A connection method for an integrated connector structure, characterized in that, The method for connecting the cargo hold beam (10), the fuselage bulkhead (20), and the side guide rail (30) using the integrated connecting joint structure according to any one of claims 1-5 includes the following steps: S1: Connect the first plate (120) of the connector body (100) to the cargo hold beam (10) to form an assembly of the cargo hold beam (10) and the connector body (100); S2: The assembly is installed into the machine body as a component by positioning tooling, and the main board body (110) is connected to the machine body frame (20) along the third direction. S3: Connect the side guide rail (30) to the second plate (130).

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