Supporting tool applied to assembly of airplane cargo hold

Abstract

The utility model belongs to the technical field of aircraft manufacturing, and discloses a supporting tool applied to assembly of an aircraft cargo hold, which comprises a first supporting block and a second supporting block, and the first supporting block is provided with a first connecting part and a first pressing surface which are arranged up and down; the second supporting block is provided with a second connecting part and a second abutting face which are arranged up and down, the bottom face of the first supporting block and the bottom face of the second supporting block abut against the skin of the aircraft, and the first supporting block and the second supporting block are detachably connected through the second connecting part and the first connecting part. The first abutting face and the second abutting face abut against the two sides of a stringer of the aircraft respectively, and the top face of the first supporting block and the top face of the second supporting block are matched to form a supporting face used for supporting the bottom plate connecting piece. The supporting face can stably support the bottom plate connecting piece in the assembling process of cargo hold installation, butt joint and the like, bending deformation or breakage of the panel connecting piece is avoided, and supporting protection in the whole airplane assembling period is achieved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, and in particular to a support tooling used in the assembly of aircraft cargo holds. Background Technology

[0002] Traditional aircraft have cylindrical fuselages that cannot be directly used for cargo loading. Instead, flat panels are laid inside the fuselage to form a rectangular cargo hold. These cargo hold floor panels are connected using floor connectors to ensure structural stability. Floor connectors are crucial connecting parts for the aircraft floor panels; however, because they are typically made of thin aluminum sheets, their strength is generally low, and most cargo hold floor connectors are quite long. During aircraft assembly, human error and other factors can easily cause these connectors to bend, deform, or break, requiring significant rework and repair costs. Currently, cargo hold floor connectors are primarily protected by temporary cargo hold floor covers, but this method has limitations and cannot provide complete protection throughout the entire assembly cycle. Utility Model Content

[0003] The purpose of this utility model is to provide a support fixture for aircraft cargo hold assembly, which is highly portable and versatile, and can protect the product throughout the entire aircraft assembly cycle.

[0004] To achieve this objective, the present invention adopts the following technical solution: a support fixture for assembling an aircraft cargo hold, wherein the aircraft cargo hold is located above a stringer on the aircraft inner skin, the aircraft cargo hold includes multiple floor plates and floor plate connectors, the floor plate connectors are used to connect the multiple floor plates, the support fixture for assembling the aircraft cargo hold includes a first support block and a second support block, the first support block has a first connecting part and a first pressing surface arranged vertically; the second support block has a second connecting part and a second pressing surface arranged vertically, the bottom surface of the first support block and the bottom surface of the second support block can respectively abut against the skin, the first support block and the second support block are detachably connected by the cooperation of the second connecting part and the first connecting part, so that the first pressing surface and the second pressing surface respectively abut against both sides of the stringer, and the top surface of the first support block and the top surface of the second support block cooperate to form a support surface for supporting the floor plate connector.

[0005] Preferably, the first support block has a first plane, the first connecting part is disposed on the first plane, the second support block has a second plane, the second connecting part is disposed on the second plane, and the first plane can be correspondingly fitted with the second plane.

[0006] Preferably, the upper end of the stringer is provided with a support structure, the support structure and the stringer are arranged at an angle, the first support block is provided with a first groove, the first groove is located between the first plane and the first pressure surface, the first groove cooperates with the opposite second support block to form a clearance space to avoid the support structure; or the second support block is provided with a second groove, the second groove is located between the second plane and the second pressure surface, the second groove cooperates with the opposite first support block to form a clearance space to avoid the support structure; or the first support block is provided with a first groove, the first groove is located between the first plane and the first pressure surface, the second support block is provided with a second groove, the second groove is located between the second plane and the second pressure surface, the first groove and the second groove cooperate to form a clearance space to avoid the support structure.

[0007] Preferably, the support fixture used for assembling aircraft cargo holds further includes fasteners, and both the first connecting portion and the second connecting portion are configured as through holes, with the fasteners sequentially passing through the two through holes.

[0008] Preferably, the first connecting portion is provided in multiple parts, and the second connecting portion is provided in a one-to-one correspondence with the first connecting portion.

[0009] Preferably, the first pressing surface and the second pressing surface are each provided with a first buffer layer.

[0010] Preferably, the bottom end of the first support block is provided with a first support portion, which protrudes toward the skin and fits against the skin; the bottom end of the second support block is provided with a second support portion, which protrudes toward the skin and fits against the skin.

[0011] Preferably, the first support portion facing the skin, the second support portion facing the skin, and the support surface are each provided with a second buffer layer.

[0012] Preferably, along the direction of the stringer, the end faces of the two side walls of the first support block and the two side walls of the second support block are flush.

[0013] Preferably, multiple first support blocks are arranged at intervals along the direction of the stringer, and the second support blocks are arranged in a one-to-one correspondence.

[0014] The beneficial effects of this utility model are as follows: By setting a first pressing surface and a second pressing surface, the first and second support blocks can be supported on the aircraft skin while simultaneously clamping the stringer from both sides of the aircraft, thereby achieving the positioning of the first and second support blocks relative to the stringer. At this time, the top surfaces of the first and second support blocks can form a support surface, which can stably support the bottom plate connectors during cargo hold installation, docking, and other assembly processes, preventing the panel connectors from bending, deforming, or breaking, thus achieving support and protection throughout the entire aircraft assembly cycle. The support device mainly consists of a first support block and a second support block, which is convenient to manufacture, has a simple structure, and is easy to install and disassemble, effectively improving the standardization, versatility, and portability of the support device. Attached Figure Description

[0015] Figure 1 This is a front view of the support device of this utility model;

[0016] Figure 2 This is a schematic diagram of the installation of the support device of this utility model;

[0017] Figure 3 This is a schematic diagram of the structure of the first support block of this utility model;

[0018] Figure 4 This is a schematic diagram of the structure of the second support block of this utility model;

[0019] Figure 5 This is a top view of the support device of this utility model.

[0020] In the figure: 100, first support block; 110, first plane; 111, first connecting part; 120, first pressing surface; 130, first groove; 140, first support part; 150, support surface; 160, fastener; 200, second support block; 210, second plane; 211, second connecting part; 220, second pressing surface; 230, second groove; 240, second support part; 300, bottom plate connector; 310, first bottom surface; 320, second bottom surface; 400, stringer; 500, skin. Detailed Implementation

[0021] 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 present 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, not the entire structure.

[0022] In the description of this utility model, 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 utility model based on the specific circumstances.

[0023] 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.

[0024] 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 this utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0025] Reference Figures 1 to 5 This utility model embodiment provides a support fixture for aircraft cargo hold assembly. The aircraft cargo hold is located inside the aircraft and above the stringer 400 on the aircraft skin 500. The bottom wall of the aircraft cargo hold is composed of multiple bottom plates, which are connected by bottom plate connectors 300. It includes a first support block 100 and a second support block 200. The first support block 100 is provided with a first connecting part 111 and a first pressing surface 120 arranged vertically. The second support block 200 is provided with a second connecting part 211 and a second pressing surface 220 arranged vertically. The bottom surfaces of the first support block 100 and the second support block 200 respectively abut against the skin 500. The first support block 100 and the second support block 200 are detachably connected by the cooperation of the second connecting part 211 and the first connecting part 111, so that the first pressing surface 120 and the second pressing surface 220 respectively press against the two sides of the stringer 400.

[0026] The top surface of the first support block 100 matches the shape of the first bottom surface 310 of the base plate connector 300, and the top surface of the second support block 200 matches the shape of the second bottom surface 320 of the base plate connector 300. This allows the first support block 100 and the second support block 200 to be connected, forming a support surface 150 for supporting the base plate connector 300 (i.e., the component to be supported). Optionally, the second connecting part 211 and the first connecting part 111 can be configured as mutually cooperating slots, screw holes, pin holes, lock bodies, or other structural components to achieve a detachable connection; further details are omitted here.

[0027] Understandably, by setting the first pressing surface 120 and the second pressing surface 220, the first support block 100 and the second support block 200, while supporting themselves on the aircraft skin 500, can clamp the stringer 400 from both sides of the aircraft, thereby achieving the positioning of the first support block 100 and the second support block 200 relative to the stringer 400. At this time, the top surfaces of the first support block 100 and the second support block 200 can form a support surface 150. The support surface 150 matches the shape of the panel connector and can stably support the bottom plate connector 300 during cargo hold installation, docking, and other assembly processes, preventing the panel connector from bending, deforming, or breaking, thus achieving support and protection throughout the entire aircraft assembly cycle. The support tooling used in aircraft cargo hold assembly mainly consists of the first support block 100 and the second support block 200. It is easy to produce, has a simple structure, and is easy to install and disassemble, effectively improving the standardization, versatility, and portability of the cargo hold panel connector support device.

[0028] It should be noted that the height of the first support block 100 and the height of the second support block 200 are precisely calculated so that after the first support block 100 and the second support block 200 are connected, there is a small gap between the support surface 150 and the panel connector to be supported. The user can press the panel connector and observe whether the first support block 100 and the second support block 200 shake or shift to determine whether the first support block 100 and the second support block 200 can stably support the panel connector on the 150 surface.

[0029] Since panel connectors typically only bend and deform under accidental factors such as human error, and conventional assembly and docking procedures do not cause panel connectors to bend and deform, a small gap is placed between the support surface 150 and the panel connector. This ensures that the support surface 150 can stabilize the panel connector and prevent panel deformation, while allowing the panel connector to make slight displacements when subjected to external pressure or vibration. This reduces the impact and damage to the base plate connector 300 and also reduces the friction and wear on the panel connector during conventional assembly and docking procedures.

[0030] Furthermore, the first pressing surface 120 and the second pressing surface 220 are respectively provided with a first buffer layer. Optionally, the first buffer layer may include flexible parts such as nylon parts and rubber parts. The first buffer layer and the first pressing surface 120, as well as the first buffer layer and the second pressing surface 220, are bonded and fixed together.

[0031] By setting the first buffer layer, on the one hand, the first buffer layer can transform the rigid contact between the first pressure surface 120 and the stringer 400 and between the second pressure surface 220 and the stringer 400 into a flexible contact, dispersing the stress exerted on the surface of the stringer 400 by the first pressure surface 120 and the second pressure surface 220, and preventing the first pressure surface 120 and the second pressure surface 220 from damaging the stringer 400; on the other hand, when the panel connector is subjected to external impact during the assembly and docking process, the first buffer layer can absorb the stress transmitted from the panel connector to the stringer 400 through the first support block 100 and the second support block 200, weaken the impact on the stringer 400, and ensure that the stringer 400 is difficult to be damaged by external impact during the entire aircraft assembly cycle.

[0032] Reference Figure 3 and Figure 4 As shown, it can be understood that the first support block 100 is provided with a first plane 110 and a first connecting part 111 is provided on the first plane 110, the second support block 200 is provided with a second plane 210 and a second connecting part 211 is provided on the second plane 210, and the first plane 110 can be correspondingly fitted with the second plane 210.

[0033] By setting the first plane 110 and the second plane 210, the structure of the first support block 100 and the second support block 200 is simplified, and the setting of the first connecting part 111 and the second connecting part 211 is convenient. At the same time, the contact area between the first support block 100 and the second support block 200 is uniform and consistent, which can provide high stability and reliability when subjected to external pressure or vibration.

[0034] Reference Figure 1 and Figure 2 As shown, it can be understood that a support structure is provided at the upper end of the stringer 400. The support structure and the stringer 400 are arranged at an angle, and the support structure abuts against the protruding structure on the aircraft skin 500 to avoid problems such as lateral tilting and torsion when the stringer 400 is subjected to lateral forces. Optionally, the support structure can be an inclined flange structure, rolled edge structure, diagonal brace structure, or flange structure perpendicular to the stringer 400, etc., set on the skin 500. The shape of the support structure is determined by stress analysis and optimization, and will not be elaborated here.

[0035] The first support block 100 is provided with a first groove 130, which is located between the first plane 110 and the first pressing surface 120. The first groove 130 cooperates with the opposite second support block 200 to form a clearance space to avoid the support structure; or the second support block 200 is provided with a second groove 230, which is located between the second plane 210 and the second pressing surface 220. The second groove 230 cooperates with the opposite first support block 100 to form a clearance space to avoid the support structure; or the first support block 100 is provided with a first groove 130, which is located between the first plane 110 and the first pressing surface 120, and the second support block 200 is provided with a second groove 230, which is located between the second plane 210 and the second pressing surface 220. The first groove 130 and the second groove 230 cooperate to form a clearance space to avoid the support structure.

[0036] Since the supporting structure needs to abut against the protruding structure on the skin 500, the supporting structure must protrude from at least one end face of the stringer 400. Therefore, at least one of the first supporting block 100 and the second supporting block 200 needs to be provided with a groove that can avoid the supporting structure. Specifically, if the supporting structure protrudes from the stringer 400 towards the first supporting block 100, a clearance space is formed between the first groove 130 of the first supporting block 100 and the side wall of the second supporting block 200 to avoid the supporting structure. If the supporting structure protrudes from the stringer 400 towards the second supporting block 200, a clearance space is formed between the second groove 230 of the second supporting block 200 and the side wall of the first supporting block 100 to avoid the supporting structure. If the supporting structure protrudes from both sides of the stringer 400, the first groove 130 and the second groove 230 cooperate to form a clearance space to avoid the supporting structure.

[0037] By setting up clearance space, while the first pressing surface 120 and the second pressing surface 220 press against both sides of the long string 400 and the first plane 110 and the second plane 210 are in corresponding contact, the upper support structure of the long string 400 is avoided, preventing the support structure from being squeezed and impacted by external forces, which would affect the structural stability of the long string 400 and effectively improve the structural rationality of the support device.

[0038] Reference Figures 2 to 5 As shown, it can be understood that the supporting fixtures for aircraft cargo hold assembly also include fasteners 160. The first connecting part 111 and the second connecting part 211 are configured with through holes of the same size, and the fasteners 160 are sequentially inserted into the two through holes. Optionally, the fasteners 160 include bolts, nuts, pins, snap rings, etc., which will not be described in detail here.

[0039] The first support block 100 and the second support block 200 are connected by fastener 160. The user only needs to open through holes on the first plane 110 and the second plane 210 to ensure the stable connection between the first support block 100 and the second support block 200, while effectively simplifying the structure of the first support block 100 and the second support block 200.

[0040] Furthermore, multiple first connecting portions 111 are provided. Optionally, the multiple first connecting portions 111 can be spaced apart along the direction of the stringer, spaced apart along the vertical direction, or arranged diagonally or in a matrix pattern, which will not be elaborated here. The second connecting portions 211 are provided in a one-to-one correspondence with the first connecting portions 111.

[0041] By providing multiple first connecting parts 111, the first support block 100 and the second support block 200 can be fixedly connected from multiple points, effectively improving the connection stability of the first support block 100 and the second support block 200.

[0042] Reference Figures 1 to 4 As shown, it can be understood that the bottom end of the first support block 100 is provided with a first support portion 140, which protrudes toward the skin 500 and the bottom surface of the first support portion 140 is in contact with the skin 500. The bottom end of the second support block 200 is provided with a second support portion 240, which protrudes toward the skin 500 and the bottom surface of the second support portion 240 is in contact with the skin 500.

[0043] The skin on both sides of the stringer 400 is typically recessed downwards and has a certain curvature. By providing the first support portion 140 and the second support portion 240, it can be ensured that the bottom surfaces of the first support block 100 and the second support block 200 can contact the skin 500, thereby fitting snugly against the skin 500 and ensuring the support stability of the first support block 100 and the second support block 200. In addition, some strings 400 also have a support structure at the bottom. The gap between the first support portion 140 and the second support portion 240 can avoid the support structure of the stringer 400, further improving the structural rationality of the first support block 100 and the second support block 200.

[0044] Furthermore, the first support portion 140 facing the skin 500, the second support portion 240 facing the skin 500, and the support surface 150 are each provided with a second buffer layer. In other words, the bottom and top surfaces of the first support block 100 and the bottom and top surfaces of the second support block 200 are each provided with a second buffer layer. The structure of the second buffer layer is the same as described above regarding the first buffer layer, and will not be repeated here.

[0045] By providing a second buffer layer on the first support portion 140 and the second support portion 240, the rigid contact between the first support portion 140 and the skin 500, and between the second support portion 240 and the skin 500, can be transformed into a flexible contact. This also adapts to the non-planar shape of the skin 500, ensuring a good fit between the first support portion 140 and the skin 500, and between the second support portion 240 and the skin 500, thus enhancing the support effect of the first support portion 140 and the second support portion 240. By providing a second buffer layer on the support surface 150, the support surface 150 makes flexible contact with the panel connector. The second buffer layer can absorb external impacts and vibrations experienced by the panel connector during assembly and docking, enhancing the support and protection effect of the support device throughout the entire aircraft assembly cycle.

[0046] Reference Figure 5 As shown, it can be understood that, along the direction of the stringer, the two side walls of the first support block 100 and the two side wall end faces of the second support block 200 are flush.

[0047] The side walls of the first support block 100 and the second support block 200 are aligned and flush, which makes it easy for the user to quickly align the first connecting part 111 and the second connecting part 211 when assembling the support device, thus improving the ease of assembly of the support device. At the same time, the support device composed of the first support block 100 and the second support block 200 has a flat and simple appearance, which improves the aesthetics of the support device.

[0048] Furthermore, multiple first support blocks 100 are arranged at intervals along the direction of the stringer, and second support blocks 200 are set in a one-to-one correspondence with the second support blocks 200.

[0049] Multiple first support blocks 100 are arranged along the long stringer to ensure that different positions of the panel connector can be supported by the support device. Even if the panel connector is long, there will be no bending or deformation at any position, thus ensuring the structural stability of the long panel connector.

[0050] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. 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 this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A support fixture for assembling an aircraft cargo hold, the cargo hold being located above a stringer (400) on an aircraft inner skin (500), the cargo hold comprising a plurality of floor plates and floor plate connectors (300), the floor plate connectors (300) being used to connect the plurality of floor plates, characterized in that, include: The first support block (100) is provided with a first connecting part (111) and a first pressing surface (120) arranged vertically. The second support block (200) is provided with a second connecting part (211) and a second pressing surface (220) arranged vertically. The bottom surface of the first support block (100) and the bottom surface of the second support block (200) can respectively abut against the skin (500). The first support block (100) and the second support block (200) are detachably connected by the cooperation of the second connecting part (211) and the first connecting part (111), so that the first pressing surface (120) and the second pressing surface (220) respectively abut against the two sides of the stringer (400), and the top surface of the first support block (100) and the top surface of the second support block (200) cooperate to form a support surface (150) for supporting the bottom plate connector (300).

2. The support fixture for aircraft cargo hold assembly according to claim 1, characterized in that, The first support block (100) has a first plane (110), and the first connecting part (111) is disposed on the first plane (110). The second support block (200) has a second plane (210), and the second connecting part (211) is disposed on the second plane (210). The first plane (110) can be correspondingly fitted with the second plane (210).

3. The support fixture for aircraft cargo hold assembly according to claim 2, characterized in that, The upper end of the stringer (400) is provided with a support structure, which is arranged at an angle to the stringer (400). The first support block (100) is provided with a first groove (130), which is located between the first plane (110) and the first pressing surface (120). The first groove (130) cooperates with the opposite second support block (200) to form a clearance space to avoid the support structure; or The second support block (200) is provided with a second groove (230), which is located between the second plane (210) and the second pressing surface (220). The second groove (230) cooperates with the opposite first support block (100) to form a clearance space to avoid the support structure; or The first support block (100) is provided with a first groove (130) located between the first plane (110) and the first pressing surface (120). The second support block (200) is provided with a second groove (230) located between the second plane (210) and the second pressing surface (220). The first groove (130) and the second groove (230) cooperate to form a clearance space to avoid the support structure.

4. The support fixture for aircraft cargo hold assembly according to any one of claims 1-3, characterized in that, The support fixture used for aircraft cargo hold assembly also includes fasteners (160), and the first connecting part (111) and the second connecting part (211) are both configured as through holes, with the fasteners (160) passing through the two through holes in sequence.

5. The support fixture for aircraft cargo hold assembly according to any one of claims 1-3, characterized in that, The first connecting part (111) is provided in multiple ways, and the second connecting part (211) is provided in a one-to-one correspondence with the first connecting part (111).

6. The support fixture for aircraft cargo hold assembly according to any one of claims 1-3, characterized in that, The first pressure surface (120) and the second pressure surface (220) are respectively provided with a first buffer layer.

7. The support tooling for aircraft cargo hold assembly according to any one of claims 1-3, characterized in that, The bottom end of the first support block (100) is provided with a first support part (140), which protrudes toward the skin (500) and fits against the skin (500). The bottom end of the second support block (200) is provided with a second support part (240), which protrudes toward the skin (500) and fits against the skin (500).

8. The support fixture for aircraft cargo hold assembly according to claim 7, characterized in that, The first support portion (140) facing the skin (500), the second support portion (240) facing the skin (500), and the support surface (150) are respectively provided with a second buffer layer.

9. The support tooling for aircraft cargo hold assembly according to any one of claims 1-3, characterized in that, Along the direction of the stringer, the two side walls of the first support block (100) and the two side wall end faces of the second support block (200) are flush.

10. The support tooling for aircraft cargo hold assembly according to any one of claims 1-3, characterized in that, Multiple first support blocks (100) are arranged at intervals along the direction of the stringer, and the second support blocks (200) are arranged in a one-to-one correspondence.

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