An integrated tooling and method of use

Abstract

This invention discloses an integrated tooling and its usage method. The integrated tooling includes a forming tooling, which comprises: a frame; a forming mold, with the frame disposed at the bottom of the forming mold; and an assembly tooling, which comprises: a frame rib positioning component, disposed at the top of the forming mold; a frame beam positioning component, disposed on one side of the frame rib positioning component; a positioning mold, disposed on one side of the forming mold, used for positioning the upper skin; and a beam intersection locator, disposed on the other side of the frame rib positioning component, used for positioning the intersection of the wing's front and rear beams with the precision-machined holes. By integrating the forming and assembly tooling into a single design, this invention reduces the time and labor costs associated with separate forming and assembly processes in traditional production, significantly improving production efficiency. It also avoids dimensional errors between the forming and assembly tooling, reduces cumulative errors, and improves overall manufacturing precision.

Description

Technical Field

[0001] This invention relates to the field of wing processing and manufacturing technology, and in particular to an integrated tooling and its usage method. Background Technology

[0002] Composite aircraft are gradually replacing traditional metal aircraft due to their advantages such as light weight, high strength, and corrosion resistance. However, the manufacturing of composite aircraft wings requires forming tooling and assembly tooling, but existing tooling manufactures both separately, resulting in low utilization and cumbersome transfer and storage. Summary of the Invention

[0003] To address the problems of low utilization and cumbersome transfer and storage caused by separating molding and assembly tooling in existing technologies, this invention provides an integrated tooling and its usage method.

[0004] The technical solution adopted in this invention is:

[0005] Firstly, this application provides an integrated tooling, comprising:

[0006] frame;

[0007] A forming mold, wherein the frame is disposed at the bottom of the forming mold;

[0008] Assembly fixture, the assembly fixture including:

[0009] A frame rib positioning assembly is disposed on the top of the frame;

[0010] A frame beam positioning assembly, wherein the frame beam positioning assembly is disposed on one side of the frame rib positioning assembly;

[0011] A beam intersection locator is located on the other side of the frame rib positioning assembly. The beam intersection locator is used to locate the intersection of the front and rear beams of the wing with the precision-machined holes.

[0012] A positioning mold is disposed on one side of the forming mold, and the positioning mold is used to position the upper skin.

[0013] Secondly, this application provides an integrated tooling and its usage method, including the following:

[0014] A frame is installed at the bottom of the forming mold based on its shape and size.

[0015] The wing is formed by hot pressing on a forming mold;

[0016] Install the beam intersection locator onto the forming mold, align and connect the holes on the front and rear beams of the wing with the holes on the beam intersection locator;

[0017] Install frame rib positioning components and frame beam positioning components on the forming mold, and position the frame, beam and rib of the wing by means of frame rib positioning components and frame beam positioning components;

[0018] After determining the positions of the wing frame, beams, and ribs, the skin connection holes are made; the precise hole positions are made using a drilling template;

[0019] After the skin connection holes are made, the skin is connected to the frame, beams, and ribs of the wing through connectors;

[0020] Install a positioning mold on one side of the forming mold; use the positioning mold as a reference to position the upper skin;

[0021] Using the frame rib positioning assembly and the frame beam positioning assembly as references, and taking into account the position of the skin connection hole, ear pieces are reserved on the edge of the skin, and the skin and beam connection hole is made with the ear piece and the beam intersection locator as references.

[0022] The beneficial effects of this invention are: by adopting an integrated design of molding tooling and assembly tooling, this application can reduce the time and labor costs of the two separate molding and assembly processes in the traditional production process, greatly improve production efficiency, avoid dimensional errors between molding tooling and assembly tooling, reduce cumulative errors, and improve overall manufacturing accuracy. Attached Figure Description

[0023] Figure 1 This is a three-dimensional structural diagram of Embodiment 1 of the present invention;

[0024] Figure 2 This is a schematic diagram of the frame rib positioning component according to Embodiment 1 of the present invention;

[0025] Figure 3 for Figure 2 Enlarged structural diagram at point A;

[0026] Figure 4 This is a structural schematic diagram of the frame beam positioning assembly according to Embodiment 1 of the present invention;

[0027] Figure 5 for Figure 4 Enlarged structural diagram at point B;

[0028] Figure 6 This is a three-dimensional structural diagram of the beam intersection locator in Embodiment 1 of the present invention;

[0029] Figure 7 This is a side view of the beam intersection locator in Embodiment 1 of the present invention.

[0030] Figure 8 This is a top view schematic diagram of the structure with positioning mold and drilling template according to Embodiment 1 of the present invention.

[0031] Reference numerals: 1. Frame; 2. Molding mold; 3. Frame rib positioning assembly; 31. First frame positioning support; 311. First slot; 312. First pin hole; 32. First frame positioning plate; 33. Rib locator; 34. First pin; 4. Frame beam positioning assembly; 41. Second frame positioning support; 411. Second slot; 412. Second pin hole; 42. Second frame positioning plate; 43. Beam locator; 44. Second pin; 5. Beam intersection locator; 51. Fixing element; 52. Positioning seat; 53. Positioning groove; 54. Positioning hole; 55. Gasket; 56. Drill sleeve; 57. Positioning pin; 6. Positioning mold; 7. Drill template. Detailed Implementation

[0032] To make the objectives, solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the embodiments and accompanying drawings. The illustrative embodiments and descriptions of the present invention are only used to explain the present invention and are not intended to limit the present invention.

[0033] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that these specific details are not necessary to practice the invention. In other embodiments, well-known structures, circuits, materials, or methods have not been specifically described in order to avoid obscuring the invention.

[0034] Throughout this specification, references to "an embodiment," "an example," or "an example" mean that a particular feature, structure, or characteristic described in connection with that embodiment or example is included in at least one embodiment of the invention. Therefore, the phrases "an embodiment," "an example," "an example," or "an example" appearing in various places throughout the specification do not necessarily refer to the same embodiment or example. Furthermore, specific features, structures, or characteristics can be combined in one or more embodiments or examples in any suitable combination and / or sub-combination. Moreover, those skilled in the art will understand that the illustrations provided herein are for illustrative purposes and are not necessarily drawn to scale. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0035] In the description of this invention, the terms "front," "rear," "left," "right," "up," "down," "vertical," "horizontal," "high," "low," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, 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 limiting the scope of protection of this invention.

[0036] Example 1:

[0037] like Figure 1 As shown, an integrated tooling includes:

[0038] A forming fixture, comprising: a frame 1; a forming mold 2, wherein the frame 1 is disposed at the bottom of the forming mold 2.

[0039] Among them, molding mold 2 is a composite molding mold. Composite molding molds are commonly used process equipment in the manufacturing of composite materials. After the reinforcing material and the base material are laid on the tooling surface, they are cured by high temperature and high pressure to form composite parts. At the same time, because the molding mold is equipped with assembly tooling, the part position can be restored by the assembly tooling to check whether the part is deformed, and whether there are any problems such as the shape or hole position deviation of the part during the manufacturing process. This can ensure the shape and size accuracy of the wing and improve the quality and reliability of the wing.

[0040] The frame 1 at the bottom of the forming mold 2 is used to provide support for the shape of the wing. The main function of the frame 1 is to support the mold body of the forming mold 2 and to allow airflow to flow evenly during the hot pressing process, so that all parts of the mold body of the forming mold 2 are heated evenly.

[0041] Considering the inconsistency between the thermal expansion coefficient of the composite material and the metal tooling, after recooling, the part surface and the tooling surface did not fit together. Subsequently, through assembly of the tooling, correction, constraint, and alignment, the skin surface was brought into contact with the tooling surface.

[0042] The assembly fixture includes: a frame rib positioning assembly 3, which is disposed on the top of the frame 1; a frame beam positioning assembly 4, which is disposed on one side of the frame rib positioning assembly 3; a beam intersection locator 5, which is disposed on the other side of the frame rib positioning assembly 4 and is used to locate the intersection of the wing's front and rear beams with the precision-machined holes; and a positioning mold 6, which is disposed on one side of the forming mold 2 and is used to locate the upper skin.

[0043] Among them, the frame rib positioning component 3 is used to determine the position of internal ribs, frames, beams and other components of the wing.

[0044] It should be noted that the beam intersection locator 5, used to locate the intersection of the front and rear wing beams with the precision-machined holes, is a precision machining fixture used for the precision machining and positioning of the connection holes between the wing and the fuselage. By using the beam intersection locator 5, the intersection position of the front and rear beams can be accurately determined, and this can be used as a reference for precision machining of the holes, thereby ensuring that the position and accuracy of the holes meet design requirements. This can improve the aerodynamic and sealing performance of the wing while ensuring the overall structural stability and reliability of the wing.

[0045] Understandably, the positioning mold 6 is used to position the upper skin. This means that during wing assembly, the positioning mold 6 serves as a reference to determine the position and attitude of each wing component, and then the skin is fixed to these components whose positions and attitudes have been determined. The positioning mold 6 is an auxiliary tool used to determine the position and attitude of each wing component to ensure the assembly accuracy and quality between them. During wing assembly, the positioning mold 6 is placed at various points on the wing to provide an accurate positioning reference.

[0046] It should be noted that the skin is the outer covering of the wing, used to protect the internal structure and components of the wing from the influence of the external environment, while also providing certain aerodynamic performance. During wing assembly, the skin needs to be fixed to the various components of the wing under the guidance of positioning mold 6 to ensure the appearance and quality of the wing.

[0047] The working process of this embodiment is as follows: A frame 1 is installed at the bottom of the forming mold 2 based on its shape and size. An airfoil is formed on the forming mold 2. A frame rib positioning assembly 3 and a frame beam positioning assembly 4 are installed on the forming mold 2, and the positions of the airfoil's frame, beam, and ribs are positioned using these components. A beam intersection locator 5 is installed on the forming mold 2, aligning and connecting the holes on the front and rear beams of the airfoil with the holes on the beam intersection locator 5. After determining the positions of the airfoil's frame, beam, and ribs, skin connection holes are made; precise hole positions are achieved using a drilling template 7. After the skin connection holes are made, the skin is connected to the airfoil's frame, beam, and ribs using connectors. A positioning mold 6 is installed on one side of the forming mold 2. The upper skin is positioned using the positioning mold 6 as a reference. Using the frame rib positioning assembly 3 and the frame beam positioning assembly 4 as references, and considering the positions of the skin connection holes, lugs are pre-reserved at the edge of the skin. The skin and beam connection holes are made using the lugs and the beam intersection locator 5 as references.

[0048] This application adopts an integrated design of molding tooling and assembly tooling, which can reduce the time and labor costs of the two separate molding and assembly processes in the traditional production process, greatly improve production efficiency, avoid dimensional errors between molding tooling and assembly tooling, reduce cumulative errors, and improve overall manufacturing accuracy.

[0049] like Figure 2 As shown, in one possible implementation, the frame rib positioning assembly 3 includes: two first frame positioning supports 31, which are disposed opposite to each other on the top sides of the forming mold 2; a first frame positioning plate 32, one end of which is connected to one of the first frame positioning supports 31, and the other end of which is connected to the other first frame positioning support 31; and a rib locator 33, which is connected to the first frame positioning plate 32.

[0050] It should be noted that the first frame positioning plate 32 is a tool used to position and fix the internal frame structure of the wing. The internal frame structure of the wing includes components such as beams, ribs, and upper and lower skins, which need to be precisely aligned and fixed during assembly.

[0051] The first frame positioning plate 32 serves as a positioning reference for the frame structure, ensuring its precise position and attitude. Aligning the frame structure with the first frame positioning plate ensures its accuracy. The first frame positioning plate 32 can also be used to fix the frame structure, preventing movement or deformation during assembly. Using the frame positioning plate allows for more efficient connection between the frame structure and the fuselage, improving the overall strength and stability of the wing. The use of the first frame positioning plate 32 simplifies the assembly process and increases assembly efficiency. Aligning and fixing the frame structure with the frame positioning plate avoids tedious manual operations, reducing assembly time and costs.

[0052] The function of installing a rib locator on the first frame positioning plate 32 is to position and fix the rib structure inside the wing. The rib is an important supporting component in the wing, which, together with the beams, provides the main structural support for the wing.

[0053] Understandably, the rib locator 33 serves as a positioning reference for the wing's rib structure, ensuring its precise position and attitude. Aligning the wing's rib structure with the rib locator ensures its accuracy. The rib locator 33 can also be used to secure the wing's rib structure, preventing movement or deformation during assembly. Using the rib locator 33 allows for more efficient connection between the rib structure and the fuselage, improving the overall strength and stability of the wing. It also improves assembly efficiency by simplifying the assembly process. Aligning and securing the wing's rib structure with the rib locator 33 avoids tedious manual operations, reducing assembly time and costs. The design and use of the rib locator 33 ensures aircraft safety. Precisely positioning and securing the internal rib structure of the wing guarantees the overall structural strength and stability of the wing.

[0054] Among them, such as Figure 3 As shown, the first frame positioning support 31 is provided with a first slot 311, and the two opposite side walls of the first slot 311 are provided with first pin holes 312; the end of the first frame positioning plate 32 is provided in the first slot 311, and the end of the first frame positioning plate 32 is provided with a first through hole, which corresponds to the first pin hole 312; the end of the first frame positioning plate 32 is connected to the first slot 311 by a first pin 34, and the first pin 34 passes through the first pin hole 312 and the first through hole.

[0055] It should be noted that the first frame positioning plate 32 is connected to the forming mold 2 through the first frame positioning support 31 and the first slot 311, which can accurately position and fix the frame position. At the same time, the use of the first pin 34 can further enhance the stability of the first frame positioning plate 32, thereby ensuring the accuracy of wing manufacturing.

[0056] Understandably, the design of the first frame positioning support 31 and the first slot 31 enhances the connection strength and stability between the first frame positioning plate 32 and the first frame positioning support 31. The use of the first pin 34 provides additional support and fixation, preventing the first frame positioning plate 32 from moving or deforming within the first slot 31.

[0057] Furthermore, the first frame positioning support 31, the first slot 31, and the first pin 34 can be used to quickly and easily install the first frame positioning plate 32 onto the forming mold 2. This installation method reduces tedious manual operations, lowers assembly difficulty, and improves assembly efficiency. At the same time, the simplified assembly process can reduce costs and the possibility of errors.

[0058] The first frame positioning plate 32 is connected to the forming mold 2 via the first frame positioning support 31, the first slot 31, and the first pin 34, allowing for convenient maintenance and replacement when needed. If the first frame positioning plate 32 is damaged or requires adjustment, the pin can be easily loosened and removed for maintenance or replacement. This design enables rapid localized maintenance and replacement while maintaining the integrity of the overall wing structure.

[0059] like Figure 4 As shown, in one possible implementation, the frame beam positioning assembly 4 includes:

[0060] Two second frame positioning supports 41 are disposed opposite to each other on the top sides of the forming mold 2; the second frame positioning supports 41 are located on the side of the first frame positioning supports 31; a second frame positioning plate 42 is provided, one end of which is connected to one of the second frame positioning supports 41, and the other end of which is connected to the other second frame positioning support 41; a beam locator 43 is provided, which is connected to the second frame positioning plate 42.

[0061] It should be noted that the second frame positioning support 41 and the second frame positioning plate 42 have the same function as the first frame positioning support 31 and the first frame positioning plate 32, and will not be described again here.

[0062] In wing assembly, the function of the beam locator mounted on the second frame positioning plate 42 is to position and secure the beam structure inside the wing. The beam is one of the main supporting components in the wing, and together with the ribs, it provides the main structural support for the wing.

[0063] The functions of a beam locator include: serving as a positioning reference for the beam structure, ensuring its precise position and attitude; aligning the beam structure with the locator to ensure its accuracy; fixing the beam structure to prevent movement or deformation during assembly; more effectively connecting the beam structure to the fuselage, improving the overall strength and stability of the wing; simplifying the assembly process and increasing efficiency; avoiding tedious manual operations and reducing assembly time and costs; and ensuring aircraft safety. Precisely positioning and fixing the beam structure within the wing guarantees the overall structural strength and stability of the wing.

[0064] Among them, such as Figure 5 As shown, the second frame positioning support 41 is provided with a second slot 411, and the two opposite side walls of the second slot 411 are provided with second pin holes 412; the end of the second frame positioning plate 42 is provided in the second slot 411, and the end of the second frame positioning plate 42 is provided with a second through hole, which corresponds to the second pin hole 44; the end of the second frame positioning plate 42 is connected to the second slot 411 by a second pin 44, and the second pin 44 passes through the second pin hole 412 and the second through hole.

[0065] The functions and roles of the related structures in this embodiment are the same as those of the first frame positioning support 31, the first slot 311, the first pin hole 312, and the first pin 34, and will not be described again here.

[0066] like Figure 6 and Figure 7 As shown, in one possible implementation, the beam intersection locator 5 includes:

[0067] The fastener 51 is disposed on the top of the forming mold 2. For example, the top of the forming mold 2 has a boss, and the fastener 51 is installed with the boss surface as a reference. The fastener 51 is located on the other side of the frame rib positioning assembly 3. The positioning seat 52 is connected to the fastener 51. The positioning seat 52 has a positioning groove 53, and positioning holes 54 are provided on the opposite side walls of the positioning groove 53. The gasket 55 is disposed in the positioning groove 53, and the through hole on the gasket 55 corresponds to the positioning hole 54. The drill sleeve 56 is disposed in the positioning hole 54. The positioning pin 57 passes through the positioning hole 54, the gasket 55 and the drill sleeve 56.

[0068] It should be noted that the beam intersection locator 5 is a tool used to locate and determine the intersection of the fore and aft beams of the wing and the positions of the precision-machined holes. Using the beam intersection locator 5 can effectively improve the accuracy and efficiency of wing assembly, while also reducing assembly difficulty and cost.

[0069] Among them, drill bushing 56 is a multi-stage drill bushing, which is a tool used to finish the connection holes between the wing and the fuselage. It is usually composed of multiple drill bushings of different specifications and sizes, used to position and fix the drill bit at different stages of processing to ensure the position, size and accuracy of the hole. In the finishing process of the connection holes between the wing and the fuselage, the use of multi-stage drill bushings can greatly improve processing efficiency and accuracy.

[0070] It should be noted that the position of the beam intersection locator can be adjusted by increasing or decreasing the thickness of the shim 55. Adjusting the thickness of the shim 55 can also reduce the cumulative error generated during the manufacturing and assembly process of the parts, thereby reducing the final impact of the accumulated error on the parts.

[0071] The positioning hole 54 may enlarge during machining. If this happens, the corresponding positioning pin 57 needs to be replaced to verify the accuracy of the positioning hole 54. The main function of the positioning pin 57 is to provide a positional reference for drilling, ensuring that the drill bit can accurately drill the required position and shape. By replacing the corresponding positioning pin 57, the hole can be better adapted to changes in size, improving drilling accuracy and efficiency.

[0072] like Figure 8 As shown, in one possible implementation, a drill template 7 is also included, which is disposed on the forming mold 2 and located on one side of the positioning mold 6.

[0073] It should be noted that the top surface of the forming mold 2 includes the profile surface and the non-working surface. The area enclosed by the positioning mold 6 and the beam intersection locator 5 is the profile surface. The profile surface is used to form the shape of the part during part manufacturing. The part outside the profile surface is the non-working surface. However, the non-working surface is used as a reference surface for machining during the manufacturing process to ensure the positional accuracy of the other parts in the subsequent assembly work.

[0074] During wing assembly, a drill template 7 is used to precisely drill holes in locations requiring accurate drilling. The drill template 7 is an auxiliary tool, typically composed of positioning holes, anti-cracking holes, and clearance holes, used to position, support, and stabilize components during wing assembly, ensuring their accuracy. It can improve work efficiency, reduce costs, and decrease the technical requirements on operators.

[0075] By drilling precise holes in the template, each component can be accurately positioned and fixed in the correct place. The drilling accuracy is more accurate and reliable than traditional manual drilling, thus ensuring the manufacturing quality and reliability of the wing.

[0076] Example 2:

[0077] A method for using an integrated tooling fixture includes the following steps:

[0078] S1, Frame 1 is installed at the bottom of the forming mold 2 based on the shape and size of the forming mold 2.

[0079] Frame 1 protects the forming mold 2 from external factors (such as external forces and high temperatures), thus ensuring the safety of the wing manufacturing process. At the same time, the design and strength of frame 1 also ensure the stability of the entire manufacturing process, improving aircraft safety.

[0080] S2, forming the wing on the forming mold 2.

[0081] This refers to the process of manufacturing or shaping an airfoil using the shape and dimensions of a forming die (2). The forming die (2) is a tool specifically designed for manufacturing and shaping airfoils, possessing a profile and surface that matches the airfoil's shape and dimensions. During airfoil manufacturing, the forming die (2) can be used to shape, shape, and calibrate the airfoil to ensure that its shape and dimensions precisely meet design requirements. The design and manufacture of the forming die (2) must take into account factors such as the airfoil's structure, aerodynamic performance, and manufacturing processes to ensure that it meets manufacturing requirements.

[0082] S3, install the frame rib positioning component 3 and the frame beam positioning component 4 on the frame 1, and position the frame, beam and rib of the wing by using the frame rib positioning component 3 and the frame beam positioning component 4.

[0083] The frame rib positioning component 3 and the frame beam positioning component 4 include the corresponding structures described in Embodiment 1, such as the rib locator 32 and the beam locator 43. Pre-positioning is achieved through the frame rib positioning component 3 and the frame beam positioning component 4.

[0084] S4, install the beam intersection locator 5 onto the frame 1, align and connect the holes on the front and rear beams of the wing with the holes on the beam intersection locator 5.

[0085] Rib positioning assembly 3 and beam positioning assembly 4 are typically used for the initial positioning and securing of the rib and beam structures of the wing. The design and structure of these assemblies may vary depending on the manufacturing process and wing type, but they generally include structural features for positioning the ribs and beams, as well as pins or bolts for connection to the fuselage.

[0086] The rib positioning component 3, through precise cooperation with the rib structure, ensures the position and orientation of the rib on the frame 1; the beam positioning component 4, through cooperation with the beam structure, achieves the same goal. These components can pre-adjust the position and orientation of the ribs and beams to near their final state, thereby reducing the workload and difficulty of on-site assembly.

[0087] However, relying solely on the frame rib positioning assembly 3 and the frame beam positioning assembly 4 for pre-positioning may not be sufficient to ensure the accuracy of wing manufacturing. Therefore, a beam intersection locator is also required for precise positioning.

[0088] A beam intersection locator is a tool specifically designed to accurately determine the position of the intersection of the fore-and-aft beams of an airfoil. It typically has structural features for precise alignment with the airfoil structure, as well as indicators or markings for accurately positioning the intersection.

[0089] When using a beam intersection locator for precise positioning, the holes on the fore and aft spars of the wing must be aligned with the holes on the beam intersection locator, and then they are secured together using connectors such as pins or bolts. This ensures that the position of the intersection of the fore and aft spars of the wing accurately meets design requirements, thereby guaranteeing the overall structural strength and stability of the wing.

[0090] S5, after determining the positions of the wing frame, beam, and ribs, make the skin connection holes; the precise hole positions are made using the drilling template 7.

[0091] S6, after the skin connection holes are made, the skin is connected to the frame, beam and rib of the wing through the connectors.

[0092] Ribs, frames, and beams play crucial supporting and load-bearing roles in the wing, and their positions significantly impact the overall shape, size, and aerodynamic performance of the wing. During wing assembly, rib and beam positioners are used to precisely measure and control the positions of these components, ensuring that their positions and attitudes meet design requirements.

[0093] After determining the positions of components such as ribs, frames, and beams, corresponding connection holes are then fabricated based on this positional information to ensure the accuracy and quality of the connections between these components. These connection holes are used to fix and connect components such as ribs, frames, and beams to the skin and other components, which is a crucial step in ensuring the overall structural stability and reliability of the wing.

[0094] Connectors are key components used to connect the skin to the wing's frame, beams, ribs, and other structural elements. Depending on the connection method and components, connectors can include the following types: Bolts and nuts: These are used to securely connect the skin to the structure by drilling holes in the skin and wing structure, passing bolts through these holes, and tightening them with nuts. Rivets: Rivets are fasteners that form a strong connection by press-fitting the skin to the wing structure and then upsetting the head through impact or static force. Screws: Screws are threaded fasteners that connect the skin to the wing structure by rotating and tightening. Washers and spring rings: Washers and spring rings are auxiliary connectors that increase the contact area, improve the fastening effect, and prevent loosening or corrosion. Structural adhesives: Structural adhesives are high-strength, corrosion-resistant glues that firmly bond the skin to the wing structure.

[0095] These connectors play a crucial role in wing manufacturing, ensuring a precise connection between the skin and the structure, and improving the overall strength and stability of the wing. Different connection methods and techniques can be selected based on the specific structure and materials used.

[0096] S7, Install positioning mold 6 on one side of molding mold 2, and position the upper skin using positioning mold 6 as a reference.

[0097] During the wing assembly process, the position and attitude of each wing component are determined using positioning module 6 as a reference, and then the skin is fixed to these components whose positions and attitudes have been determined.

[0098] S8, using the frame rib positioning component 3 and the frame beam positioning component 4 as references, and combining the position of the skin connection hole, a lug is reserved on the edge of the skin, and the skin and beam connection hole is made with the lug and beam intersection locator 5 as references.

[0099] During wing assembly, the louver and beam intersection positioning assembly is used as a reference to determine the connection position between the wing skin and the beam, and then the corresponding connection holes are fabricated. The louver and beam intersection positioning device 5 is an auxiliary tool used to determine the position and attitude of various wing components to ensure assembly accuracy and quality. During wing assembly, the skin needs to be fixed to the various wing components under the guidance of the louver and beam intersection positioning device 5 to ensure the quality and reliability of the wing.

[0100] As a crucial load-bearing component in the wing, the way the beam is connected to the skin directly affects the performance and service life of the entire wing. Therefore, it is necessary to create corresponding connection holes before connection to ensure the accuracy and quality of the connection.

[0101] The embodiments described above are merely illustrative of specific implementations of the present invention, and while the descriptions are detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. An integrated tooling characterized by, include: The molding tooling includes: Framework (1); A forming mold (2), wherein the frame (1) is disposed at the bottom of the forming mold (2); Assembly fixture, the assembly fixture including: A frame rib positioning assembly (3) is disposed on the top of the forming mold (2); A frame beam positioning assembly (4) is disposed on one side of the frame rib positioning assembly (3); Beam intersection locator (5), the beam intersection locator (5) is set on the other side of the frame rib positioning assembly (3), the beam intersection locator (5) is used to locate the intersection of the front and rear beams of the wing with the precision-machined hole; Positioning mold (6), the positioning mold (6) is disposed on one side of the forming mold (2), the positioning mold (6) is used to position the upper skin; The frame rib positioning component (3) includes: Two first frame positioning supports (31) are arranged opposite to each other on the top sides of the forming mold (2); The first frame positioning plate (32) has one end connected to a first frame positioning support (31) and the other end connected to another first frame positioning support (31). Rib locator (33), which is connected to the first frame positioning plate (32); The frame beam positioning component (4) includes: Two second frame positioning supports (41) are arranged opposite each other on the top sides of the forming mold (2); the second frame positioning supports (41) are located on one side of the first frame positioning support (31); The second frame positioning plate (42) has one end connected to a second frame positioning support (41) and the other end connected to another second frame positioning support (41). Beam locator (43), which is connected to the second frame positioning plate (42); The first frame positioning support (31) is provided with a first slot (311), and the first pin holes (312) are opened on the opposite side walls of the first slot (311). The end of the first frame positioning plate (32) is disposed in the first slot (311), and the end of the first frame positioning plate (32) is provided with a first through hole, which corresponds to the first pin hole (312). The end of the first frame positioning plate (32) is connected to the first slot (311) by a first pin (34), and the first pin (34) passes through the first pin hole (312) and the first through hole; The second frame positioning support (41) is provided with a second slot (411), and the two side walls opposite to the second slot (411) are provided with second pin holes (412). The end of the second frame positioning plate (42) is disposed in the second slot (411), and the end of the second frame positioning plate (42) is provided with a second through hole, which corresponds to the second pin hole (412). The end of the second frame positioning plate (42) is connected to the second slot (411) by a second pin (44), and the second pin (44) passes through the second pin hole (412) and the second through hole; The beam intersection locator (5) includes: A fastener (51) is disposed on the top of the forming mold (2) and the fastener (51) is located on the other side of the frame rib positioning assembly (3); Positioning seat (52), the positioning seat (52) is connected to the fixing member (51); the positioning seat (52) is provided with a positioning groove (53), and positioning holes (54) are provided on the opposite side walls of the positioning groove (53); Gasket (55), the gasket (55) is disposed in the positioning groove (53), and the through hole on the gasket (55) corresponds to the positioning hole (54); Drill sleeve (56), the drill sleeve (56) is disposed in the positioning hole (54); Positioning pin (57), which passes through the positioning hole (54), the washer (55) and the drill bushing (56); It also includes a drill template (7), which is disposed on the top of the forming mold (2) and is located on one side of the positioning mold (6).

2. A method of using an integrated tooling, the integrated tooling of claim 1, wherein, Includes the following: Based on the shape and size of the forming mold (2), a frame (1) is installed at the bottom of the forming mold (2); The wing is formed by hot pressing on the forming mold (2); Install the frame rib positioning assembly (3) and the frame beam positioning assembly (4) on the forming mold (2) to position the frame, beam and rib of the wing; Install the beam intersection locator (5) onto the forming mold (2), align and connect the holes on the front and rear beams of the wing with the holes on the beam intersection locator (5); After determining the positions of the wing frame, beams, and ribs, the skin connection holes are made; the precise hole positions are made using a drilling template (7); After the skin connection holes are made, the skin is connected to the frame, beams, and ribs of the wing through connectors; Install a positioning mold (6) on one side of the top of the forming mold (2), and position the upper skin with the positioning mold (6) as a reference; Using the frame rib positioning component (3) and the frame beam positioning component (4) as references, and taking into account the position of the skin connection hole, a lug is reserved on the edge of the skin, and the skin and beam connection hole is made based on the lug and beam intersection locator (5).

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