Aircraft wing wallboard forming equipment with reinforcing rib structure

Abstract

The utility model belongs to the technical field of aircraft structure components, and relates to aircraft wing wallboard forming equipment with a reinforcing rib structure. The wing wall plate comprises a wing wall plate main body, the wing wall plate main body is provided with a buckle connecting piece and a screw joint fixing piece, a wall plate positioning part and an installation alignment part are arranged in the wing wall plate main body, the wall plate positioning part and the installation alignment part are arranged in a staggered mode, and a splayed reinforcing rib assembly is arranged at the bottom of the wing wall plate main body. And the wall plate positioning part and the mounting alignment part are respectively staggered with the splayed reinforcing rib assembly. By means of the splayed reinforcing rib assembly at the bottom of the wing wall plate body, especially the T-shaped reinforcing structure, bending loads can be effectively resisted, the overall bending rigidity of the wall plate is remarkably improved, deformation caused by bearing complex aerodynamic loads in the flying process is reduced, and the aerodynamic performance of an aircraft wing is guaranteed.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structural component technology, and relates to an equipment for forming aircraft wing panels with reinforcing ribs. Background Technology

[0002] In the design and manufacturing of aircraft wings, wing panels, as crucial structural components, must withstand complex aerodynamic loads and their own structural stresses. Traditional aircraft wing panels have limitations in strength and stiffness, making it difficult to meet the high-performance and long-life requirements of modern aircraft. For example, during flight, wing panels are prone to deformation due to bending loads, and localized stress concentration is a significant issue. This not only affects the aircraft's aerodynamic performance but also reduces the wing's service life and safety. Furthermore, crack propagation within the panels and insufficient fatigue life remain persistent challenges in aircraft wing design and manufacturing. Therefore, there is an urgent need to design a wing panel forming equipment with a reinforced rib structure that can overcome these shortcomings. Utility Model Content

[0003] The purpose of this invention is to address the above-mentioned problems by providing an aircraft wing panel forming equipment with a reinforcing rib structure.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] A wing panel forming equipment with a reinforcing rib structure includes a wing panel body, on which snap-fit ​​connectors and screw fasteners are provided. The wing panel body has a panel positioning part and an installation alignment part, which are staggered. The bottom of the wing panel body is provided with a figure-eight reinforcing rib assembly, and the panel positioning part and the installation alignment part are staggered with the figure-eight reinforcing rib assembly.

[0006] In the above-mentioned aircraft wing panel forming equipment with a reinforcing rib structure, the figure-eight reinforcing rib assembly includes a first reinforcing rib plate and a second reinforcing rib plate disposed at the bottom of the wing panel body, and the first reinforcing rib plate and the second reinforcing rib plate are arranged in a figure-eight shape.

[0007] In the above-mentioned aircraft wing panel forming equipment with a reinforcing rib structure, the top of the first reinforcing rib plate is attached to the bottom of the wing panel body, and the bottom of the first reinforcing rib plate is provided with a first bending web plate, which is perpendicular to the first reinforcing rib plate.

[0008] In the above-mentioned aircraft wing panel forming equipment with a reinforcing rib structure, a wiring installation space is formed between the first bending web plate and the first reinforcing rib plate.

[0009] In the above-mentioned aircraft wing panel forming equipment with a reinforcing rib structure, the top of the second reinforcing rib plate is attached to the bottom of the wing panel body, and the bottom of the second reinforcing rib plate is provided with a second bending web plate, which is perpendicular to the second reinforcing rib plate.

[0010] In the aforementioned aircraft wing panel forming equipment with a reinforcing rib structure, a wiring installation space is formed between the second bending web and the second reinforcing rib plate.

[0011] In the aforementioned aircraft wing panel forming equipment with reinforcing ribs, the snap-fit ​​connector includes a snap-fit ​​plate disposed on the side of the wing panel body.

[0012] In the above-mentioned aircraft wing panel forming equipment with reinforcing rib structure, the screw fastener includes a screw plate disposed on the side of the main body of the wing panel, and the screw plate has screw holes.

[0013] In the aforementioned aircraft wing panel forming equipment with reinforcing ribs, the panel positioning part includes several positioning square holes disposed within the wing panel body.

[0014] In the above-mentioned aircraft wing panel forming equipment with a reinforcing rib structure, the mounting and alignment part includes a component mounting groove disposed in the main body of the wing panel, and the component mounting groove and the positioning square hole are staggered.

[0015] Compared with existing technologies, the advantages of this utility model are:

[0016] 1. This utility model, through the figure-eight reinforcing rib assembly at the bottom of the wing panel body, especially the T-shaped reinforcing structure, can effectively resist bending loads, significantly improve the overall bending stiffness of the panel, reduce deformation caused by complex aerodynamic loads during flight, and ensure the aerodynamic performance of the aircraft wing.

[0017] 2. The T-shaped reinforcing ribs in this utility model can evenly distribute the load to a larger area of ​​the panel, effectively reducing the problem of local stress concentration, thereby extending the service life of the wing panel structure and improving the safety of the aircraft.

[0018] Other advantages, objectives and features of this invention will be partly apparent from the following description, and partly understood by those skilled in the art through study and practice of this invention. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of this utility model.

[0020] Figure 2 This is a structural schematic diagram of another aspect of this utility model.

[0021] Figure 3 This is a structural schematic diagram of the first reinforcing rib.

[0022] Figure 4 This is a structural schematic diagram of the second reinforcing rib.

[0023] In the diagram: 1. Wing panel body; 2. Buckle connector; 3. Screw fastener; 4. Panel positioning part; 5. Mounting alignment part; 6. Figure-eight reinforcing rib assembly; 7. First reinforcing rib plate; 8. Second reinforcing rib plate; 9. First bending web plate; 10. Second bending web plate; 11. Buckle plate; 12. Screw plate; 13. Screw hole; 14. Positioning square hole; 15. Accessory mounting slot. Detailed Implementation

[0024] The present invention will be further described below with reference to the accompanying drawings.

[0025] like Figure 1-4 As shown, an aircraft wing panel forming equipment with a reinforcing rib structure includes a wing panel body 1. The wing panel body 1 is provided with a snap-fit ​​connector 2 and a screw fastener 3. The wing panel body 1 has a panel positioning part 4 and an installation alignment part 5 inside. The panel positioning part 4 and the installation alignment part 5 are staggered. The bottom of the wing panel body 1 is provided with a figure-eight reinforcing rib assembly 6. The panel positioning part 4 and the installation alignment part 5 are staggered with the figure-eight reinforcing rib assembly 6.

[0026] In this embodiment, the snap-fit ​​connector 2 and the screw fastener 3 are distributed on the side of the wing panel body 1 for connection with other aircraft components; the panel positioning part 4 and the mounting alignment part 5 are inside the wing panel body 1, and they are staggered to ensure the orderly installation and positioning of internal components; the figure-eight reinforcing rib assembly 6 is located at the bottom of the wing panel body 1, and is also staggered with the internal panel positioning part 4 and mounting alignment part 5, without interfering with each other, while providing support and reinforcement for the wing panel body 1. The snap-fit ​​connector 2 and the screw fastener 3 provide diverse ways to connect the wing panel body 1 with other components, facilitating installation and disassembly; the staggered arrangement of the panel positioning part 4 and the mounting alignment part 5 facilitates the precise installation and positioning of internal components; the staggered arrangement of the figure-eight reinforcing rib assembly 6 and them ensures the effectiveness of the reinforcing structure and provides space for the internal structural layout, thereby improving the overall assembly efficiency and structural stability of the wing panel.

[0027] Combination Figure 1-4 As shown, the figure-eight reinforcing rib assembly 6 includes a first reinforcing rib plate 7 and a second reinforcing rib plate 8 disposed at the bottom of the wing panel body 1, and the first reinforcing rib plate 7 and the second reinforcing rib plate 8 are arranged in a figure-eight shape.

[0028] Specifically, the first reinforcing rib 7 and the second reinforcing rib 8 are closely attached to the bottom of the wing panel body 1 in a figure-eight shape. The two work together to provide support for the wing panel body 1 from different directions. The unique figure-eight layout allows the reinforcing rib assembly to distribute the load borne by the wing panel body 1 in multiple directions, effectively enhancing its bending and compressive strength, and improving the overall strength and stability of the wing panel. Compared with a single reinforcing rib structure, it can better adapt to complex aerodynamic loads.

[0029] The top of the first reinforcing rib 7 is attached to the bottom of the wing panel body 1, and the bottom of the first reinforcing rib 7 is provided with a first bending web 9, which is perpendicular to the first reinforcing rib 7.

[0030] In this embodiment, the top of the first reinforcing rib 7 is in close contact with the bottom of the wing panel body 1, transmitting and dispersing the force on the wing panel body 1; the first bending web 9 is vertically arranged at the bottom of the first reinforcing rib 7, forming a T-shaped structure together with the first reinforcing rib 7. This T-shaped structure greatly improves the bending stiffness of the wing panel body 1. The first bending web 9 can effectively resist bending deformation, evenly distribute the force to a larger area, reduce local stress concentration, and extend the service life of the wing panel.

[0031] Combination Figure 2 , Figure 3 As shown, a wiring installation space is formed between the first bending web 9 and the first reinforcing rib 7.

[0032] In this embodiment, due to the perpendicular relationship between the first bending web plate 9 and the first reinforcing rib plate 7, a space is naturally formed for wiring, saving space. This wiring installation space provides a dedicated area for the internal wiring of the aircraft, avoiding interference between the wiring and other structural components, making the internal structure of the aircraft more compact and orderly, and also facilitating the maintenance and repair of the wiring, thus improving the overall reliability and maintainability of the aircraft.

[0033] The top of the second reinforcing rib 8 is attached to the bottom of the wing panel body 1, and the bottom of the second reinforcing rib 8 is provided with a second bending web 10, which is perpendicular to the second reinforcing rib 8.

[0034] In this embodiment, in conjunction with the first reinforcing rib 7, the top of the second reinforcing rib 8 is attached to the bottom of the wing panel body 1 to transfer loads; the second bending web 10 is vertically arranged at the bottom of the second reinforcing rib 8 to form a T-shaped structure. The T-shaped structure composed of the second reinforcing rib 8 and the second bending web 10 further enhances the strength and rigidity of the wing panel body 1, and works in synergy with the first reinforcing rib 7 and the first bending web 9 to comprehensively improve the wing panel's ability to resist various loads, ensuring the safety and stability of the aircraft during flight.

[0035] Combination Figure 4 As shown, a wiring installation space is formed between the second bending web 10 and the second reinforcing rib 8.

[0036] In this embodiment, the space is formed by the vertical structure of the second bending web 10 and the second reinforcing rib 8, which provides additional space for the internal wiring of the aircraft, further optimizes the internal wiring layout, improves the utilization rate of the internal space of the aircraft, and also ensures the safety and stability of the wiring.

[0037] The snap-fit ​​connector 2 includes a snap-fit ​​plate 11 disposed on the side of the wing panel body 1.

[0038] In this embodiment, the snap-on plate 11 is installed on the side of the wing panel body 1 and cooperates with the corresponding slots or snaps on other components to achieve quick connection. The snap-on plate 11 makes the connection between the wing panel body 1 and other components more convenient and faster, greatly improving the efficiency of aircraft assembly. When it is necessary to repair or replace parts, it can also be easily disassembled, reducing maintenance costs and time.

[0039] Combination Figure 1-2 As shown, the screw fastener 3 includes a screw plate 12 disposed on the side of the wing panel body 1, and the screw plate 12 has a screw hole 13.

[0040] In this embodiment, the screw plate 12 is located on the side of the wing panel body 1. By screwing bolts or other connectors into the screw holes 13, it is fixedly connected to the corresponding screw holes or threaded structures on other components. The screw fixing method provides a stable and reliable connection, ensuring that the wing panel body 1 is tightly integrated with other components during flight, can withstand large loads, and ensure the integrity and safety of the aircraft structure.

[0041] Combination Figure 1-2 As shown, the wall panel positioning part 4 includes a plurality of positioning square holes 14 disposed in the wing wall panel body 1.

[0042] In this embodiment, during the assembly process, the positioning square hole 14 cooperates with positioning components such as positioning pins to accurately determine the position of the wing panel body 1. The setting of the positioning square hole 14 ensures the accuracy and precision of the wing panel body 1 during installation, enabling the wing panel to be accurately installed in the predetermined position, ensuring the overall assembly quality of the aircraft wing, and thus ensuring the aerodynamic performance and flight safety of the aircraft.

[0043] Combination Figure 1-2 As shown, the mounting alignment part 5 includes an accessory mounting groove 15 disposed in the wing panel body 1, and the accessory mounting groove 15 is staggered with the positioning square hole 14.

[0044] In this embodiment, the accessory mounting slot 15 is used to place various accessories. It is staggered with the positioning square hole 14 and does not affect each other. After the positioning square hole 14 determines the position of the wing panel body 1, the accessory mounting slot 15 can accurately position and install the accessories. The accessory mounting slot 15 facilitates the installation of various accessories, improves assembly efficiency and accuracy, and at the same time, the staggered arrangement with the positioning square hole 14 optimizes the internal structural layout of the wing panel body 1, making the whole structure more compact and reasonable.

[0045] The working principle of this utility model is as follows:

[0046] During the manufacturing of the aircraft wing panel body 1, the first reinforcing rib 7 and the second reinforcing rib 8 are tightly attached to the bottom of the wing panel body 1 according to the V-shaped design requirements. Through welding, riveting, or other suitable connection methods, the first reinforcing rib 7 and the second reinforcing rib 8 are ensured to be firmly connected to the wing panel body 1. Simultaneously, the first bending web 9 and the first reinforcing rib 7, and the second bending web 10 and the second reinforcing rib 8 are ensured to be perpendicular to each other, forming an effective T-shaped reinforcement structure.

[0047] On the side of the wing panel body 1, a snap-fit ​​plate 11 is installed as a snap-fit ​​connector 2, and a screw plate 12 is installed with screw holes 13 as a screw fastener 3. Inside the wing panel body 1, a positioning square hole 14 is made as a panel positioning part 4, and an accessory mounting groove 15 is made as an installation alignment part 5, according to design requirements, and their staggered arrangement is ensured.

[0048] During the assembly of the aircraft wing, the wing panel body 1 is first accurately positioned in the predetermined position by cooperating with the positioning pin through the positioning square hole 14 of the panel positioning part 4. Then, the accessories to be installed are placed in the accessory mounting slot 15 of the mounting alignment part 5 for initial fixation. Next, the snap-on plate 11 of the snap-on connector 2 is used to quickly connect with other components to achieve initial assembly. Finally, the screw plate 12 and screw hole 13 of the screw fastener 3 are used to finally fix the wing panel body 1 with bolts and other connectors to ensure that the wing panel body 1 is firmly connected with other components.

[0049] The specific embodiments described herein are merely illustrative examples illustrating the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications or additions to the described specific embodiments or use similar methods to replace them, without departing from the spirit of this utility model.

[0050] Although this document frequently uses terms such as wing panel body 1, snap-fit ​​connector 2, screw fastener 3, panel positioning part 4, mounting alignment part 5, figure-eight reinforcing rib assembly 6, first reinforcing rib plate 7, second reinforcing rib plate 8, first bending web 9, second bending web 10, snap-fit ​​plate 11, screw plate 12, screw hole 13, positioning square hole 14, and accessory mounting slot 15, the possibility of using other terms is not excluded. The use of these terms is merely for the convenience of describing and explaining the essence of this utility model; interpreting them as any additional limitation would contradict the spirit of this utility model.

Claims

1. An aircraft wing panel forming apparatus having a stiffener structure, comprising a wing panel body (1), characterized in that, The wing panel body (1) is provided with a buckle connecting piece (2) and a screw fixing piece (3), the wing panel body (1) is provided with a panel positioning part (4) and a mounting alignment part (5), the panel positioning part (4) and the mounting alignment part (5) are staggered, the bottom of the wing panel body (1) is provided with a splayed reinforcing rib assembly (6), and the panel positioning part (4) and the mounting alignment part (5) are staggered with the splayed reinforcing rib assembly (6).

2. Aircraft wing panel forming equipment with stiffener structure according to claim 1, characterized in that The splayed reinforcing rib assembly (6) comprises a first reinforcing rib plate (7) and a second reinforcing rib plate (8) arranged at the bottom of the wing panel body (1), and the first reinforcing rib plate (7) and the second reinforcing rib plate (8) are arranged in a splayed shape.

3. The aircraft wing panel forming apparatus having a stiffened structure of claim 2, wherein, The top of the first reinforcing rib plate (7) is attached to the bottom of the wing panel body (1), the bottom of the first reinforcing rib plate (7) is provided with a first bending-resistant web (9), and the first bending-resistant web (9) is perpendicular to the first reinforcing rib plate (7).

4. The aircraft wing panel forming apparatus having a stiffened structure of claim 3, wherein, A line installation space is formed between the first bending-resistant web (9) and the first reinforcing rib plate (7).

5. The aircraft wing panel forming apparatus having a stiffened structure as defined in claim 4, wherein, The top of the second reinforcing rib plate (8) is attached to the bottom of the wing panel body (1), the bottom of the second reinforcing rib plate (8) is provided with a second bending-resistant web (10), and the second bending-resistant web (10) is perpendicular to the second reinforcing rib plate (8).

6. The aircraft wing panel forming apparatus having a stiffened structure as defined in claim 5, wherein, A line installation space is formed between the second bending-resistant web (10) and the second reinforcing rib plate (8).

7. The aircraft wing panel forming apparatus having a stiffened structure according to claim 6, wherein, The buckle connecting piece (2) comprises a buckle plate (11) arranged at the side of the wing panel body (1).

8. The aircraft wing panel forming apparatus having a stiffened structure according to claim 7, wherein, The screw fixing piece (3) comprises a screw plate (12) arranged at the side of the wing panel body (1), and the screw plate (12) is provided with a screw hole (13).

9. The aircraft wing panel forming apparatus having a stiffened structure of claim 8, wherein, The panel positioning part (4) comprises a plurality of positioning square holes (14) arranged in the wing panel body (1).

10. The aircraft wing panel forming apparatus having a stiffened structure of claim 9, wherein, The mounting alignment part (5) comprises a fitting mounting groove (15) arranged in the wing panel body (1), and the fitting mounting groove (15) is staggered with the positioning square hole (14).

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