Method for manufacturing butt joint hole, butt joint method and manufacturing device

Abstract

The application provides a butt joint hole manufacturing method, a butt joint method and a manufacturing device, and relates to the technical field of assembly. The butt joint hole manufacturing method comprises the following steps: manufacturing a first rough positioning hole and a second rough positioning hole on a butt joint area; providing a drill jig matched with the butt joint area, wherein the drill jig comprises a first positioning hole and a second positioning hole; adjusting the butt joint area and the drill jig to a horizontal state, and the projection of the first positioning hole along the axial direction covers the first rough positioning hole, and a first fine positioning hole is manufactured by taking the first positioning hole as a mold hole; rotating the second positioning hole around the axis corresponding to the first fine positioning hole within a first set error range until the projection of the second positioning hole along the axial direction covers the second rough positioning hole, and a second fine positioning hole is manufactured by taking the second positioning hole as a mold hole. The distance between the first fine positioning hole and the second fine positioning hole is kept constant, and the height difference is within the first set error allowable range, thereby ensuring the interchangeability of assembly of the first component and the second component.

Description

Technical Field

[0001] This invention relates to the field of assembly technology, and specifically to a method for manufacturing a mating hole, a mating method, and a manufacturing apparatus. Background Technology

[0002] In aircraft manufacturing, the interchangeability of aircraft parts, assemblies, sections, and components in production and use not only reduces the workload of assembly and docking, saving significant time, shortening production cycles, and lowering production costs, but also facilitates rhythmic mass production and avoids assembly deformation caused by forced assembly, as well as the concentration of residual and localized stresses within the aircraft structure. Furthermore, when an aircraft part, assembly, section, or component is damaged during use, it can be quickly replaced with a spare part, preventing localized damage from affecting normal aircraft operation, thus extending the aircraft's service life and ensuring its performance. Therefore, ensuring the interchangeability of aircraft parts and components in production and use is of great significance to both aircraft manufacturing and operation. However, aircraft fuselages have complex structures and shapes, with numerous, large, and low-rigidity parts prone to deformation. The aircraft manufacturing process is lengthy, involving a wide variety and quantity of process equipment, resulting in numerous points where errors can occur. Therefore, many factors affect interchangeability and coordination. However, users increasingly demand improved product performance, while manufacturing must ensure a high degree of accuracy in the coordination and interchangeability of aircraft structural components. Ensuring interchangeability and coordination has long been a challenge in aircraft manufacturing, and it is also a key difference between aircraft manufacturing technology and general mechanical manufacturing technology. This is precisely the characteristic of aircraft manufacturing technology.

[0003] Today, with the rise of digital assembly coordination technology and the widespread application of computer-aided design / computer-aided manufacturing (CAD / CAM) technology in aircraft manufacturing, the interchangeability and coordination of a large number of parts, especially metal parts, has been resolved.

[0004] During assembly, four-hole mating is often used, where each component has two mating holes, which are then aligned and fixed together. However, due to errors in the tooling itself, manufacturing errors in the parts, positioning errors, and the accumulation of stress release errors after assembly, the interchangeability and compatibility between components, between components and parts, and between parts remains unresolved.

[0005] Taking airplanes as an example, modern large aircraft designs often employ a biplane design, with each wing docking with the fuselage separately, using either a fork-shaped joint or a multi-hole frame connection. To ensure proper wing-fuselage docking, two methods are typically employed:

[0006] 1. After the wings and fuselage are manufactured independently, they are adjusted to the optimal position on the mating platform and the connecting holes are made together to ensure that the wings and fuselage can be smoothly connected.

[0007] 2. After the wings and fuselage are manufactured independently, the precision machining platform is used to ream the holes to eliminate the accumulation of errors during the component assembly process and ensure that the wings and fuselage are successfully connected.

[0008] The first method, while ensuring successful wing-body docking, increases the workload on the docking platform, making mass production difficult. Furthermore, it relies on shared holes for docking coordination, preventing interchangeability.

[0009] The second method is suitable for biplane structure designs. The wing-fuselage connection uses a fork-ear joint or a traditional frame-type multi-hole connection, meaning the left and right wings are connected on both sides of the fuselage without affecting each other.

[0010] In today's rapidly developing aviation industry, the application of aircraft is expanding into various fields. In addition to traditional uses in national defense and military operations and high-altitude transportation, they are increasingly being used in agriculture, low-altitude transportation, firefighting, and other areas. The design requirements for these aircraft differ from those of traditional large passenger planes and fighter jets, and there is a greater need for mass production and automation. As a result, the monoplane design with an integral wing is becoming increasingly popular.

[0011] From a design perspective, monoplane wings employ an integral design, which effectively balances the bending and torque moments of the left and right wings, reducing joint loads. The integral wing also offers higher structural rigidity and reduces structural weight. From a manufacturing perspective, the integral design makes it easier to ensure wing symmetry with the fuselage centerline during production, simplifying assembly and improving manufacturability. The wing and fuselage connection can be completed in a single step, unlike traditional aircraft where the left and right wings are connected separately. However, this also places higher demands on interchangeability. The integral wing design, using a four-hole connection at the front and rear of the wing, makes it difficult for traditional methods to meet interchangeability requirements. Therefore, a method for manufacturing the connecting holes is needed to ensure interchangeability even after the connecting holes are individually fabricated on the components. Summary of the Invention

[0012] In view of the above-mentioned shortcomings of the prior art, the present invention provides a method for manufacturing a mating hole to improve the technical problems of existing four-hole mating components being difficult to coordinate and interchange, and difficult to replace and repair.

[0013] To achieve the above and other related objectives, the present invention provides a method for manufacturing mating holes, used to process mating holes in the mating areas of a first component and a second component that are mated through four holes, the method comprising:

[0014] A first coarse positioning hole and a second coarse positioning hole are made in the docking area;

[0015] A drill jig is provided that matches the docking area, the drill jig including a first positioning hole and a second positioning hole;

[0016] The docking area and the drill jig are both adjusted to a horizontal state, and the projection of the first positioning hole along the axial direction covers the first coarse positioning hole, and the first positioning hole is used as the mold hole to make the first fine positioning hole.

[0017] The second positioning hole is rotated around the axis corresponding to the first fine positioning hole within a first set error range until the projection of the second positioning hole along the axial direction covers the second coarse positioning hole, and the second positioning hole is used as a mold hole to make the second fine positioning hole.

[0018] In an exemplary embodiment of this application, the manufacturing method further includes:

[0019] A locator is provided that matches and docks with the docking area, the locator comprising a first positioning part and a second positioning part;

[0020] Connect the first positioning part to the first coarse positioning hole, and connect the second positioning part to the second coarse positioning hole;

[0021] The components of the first component or the second component are assembled in the mating area to complete the assembly of the first component or the second component.

[0022] In an exemplary embodiment of this application, obtaining the locator includes:

[0023] Obtain the digital model of the docking area;

[0024] The locator digital model is obtained based on the docking area digital model;

[0025] The positioner is manufactured by machining the positioner digital model.

[0026] In an exemplary embodiment of this application, the locator includes a first component locator and a second component locator. The locator is manufactured by machining a digital model of the locator, comprising:

[0027] The first component positioner body and the second component positioner body are produced according to the first component positioner digital model and the second component positioner digital model, respectively.

[0028] The first component locator body and the second component locator body are docked in the combined state of the first component and the second component;

[0029] A first bushing hole and a second bushing hole are jointly formed on the first component positioner body and the second component positioner body;

[0030] Separate the first component locator body from the second component locator body, and install bushings in the first bushing hole and the second bushing hole respectively.

[0031] In an exemplary embodiment of this application, obtaining the drill jig includes:

[0032] Obtain the digital model of the docking area;

[0033] The drill jig digital model is obtained based on the docking area digital model;

[0034] The drill jig is manufactured by machining the drill jig digital model.

[0035] In an exemplary embodiment of this application, the drill jig includes a first component drill jig and a second component drill jig, and the drill jig is manufactured by machining according to the drill jig digital model, including:

[0036] The main body of the first component drill jig and the main body of the second component drill jig are respectively manufactured according to the first component drill jig digital model and the second component drill jig digital model;

[0037] Connect the first component drill jig body and the second component drill jig body in the combined state of the first component and the second component;

[0038] A first coordinating bushing hole and a second coordinating bushing hole are jointly formed on the first component drill jig body and the second component drill jig body, wherein the second coordinating bushing hole is an arc-shaped slot hole with the center of the first coordinating bushing hole as the center.

[0039] Separate the first component drill jig body and the second component drill jig body, and install bushings in the first coordinating bushing hole and the second coordinating bushing hole respectively, wherein the bushing in the second coordinating bushing hole slides along the second coordinating bushing hole.

[0040] In an exemplary embodiment of this application, the drill jig is provided with a level and a scale.

[0041] In an exemplary embodiment of this application, the first component is the fuselage and the second component is the wing.

[0042] In an exemplary embodiment of this application, the docking area includes:

[0043] A front frame of the fuselage is disposed on the fuselage, and the first precision positioning hole and the second precision positioning hole are formed on the front frame of the fuselage.

[0044] A rear frame is disposed on the body of the machine, and the first precision positioning hole and the second precision positioning hole are formed on the rear frame of the machine.

[0045] A wing front spars are disposed on the wing and configured to connect with the fuselage front frame. The wing front spars are provided with a first precision positioning hole and a second precision positioning hole.

[0046] A wing rear spars are provided on the wing and configured to connect with the rear frame of the fuselage. The wing rear spars are provided with a first precision positioning hole and a second precision positioning hole.

[0047] Wherein, after the fuselage and the wing are aligned, the first precision positioning holes are all coaxial, and the second precision positioning holes are all coaxial.

[0048] This application also provides a docking method for docking a first component and a second component with four holes, wherein the docking areas of the first component and the second component are provided with docking holes made according to the method described in any one of the above claims.

[0049] Connect the mating holes at corresponding positions of the first component and the second component to achieve the mating of the first component and the second component.

[0050] This application also provides an apparatus for manufacturing a connector, comprising:

[0051] The drill jig is provided with a first positioning hole and a second positioning hole, and the second positioning hole rotates around the axis of the first positioning hole within a first set error range;

[0052] The drill jig includes a first component drill jig and a second component drill jig, wherein the first positioning hole and the second positioning hole of the first component drill jig and the second component drill jig are co-fabricated in a mating state.

[0053] The beneficial effects of this invention are as follows:

[0054] This application utilizes a drill jig that mates with the mating area. The drill jig has a first positioning hole and a second positioning hole that rotates around the axis of the first positioning hole within a first preset error allowable range. After adjusting the level of the first or second component and the corresponding drill jig, the drill jig position is adjusted so that the projection of the first positioning hole covers the first coarse positioning hole in the mating area, thus creating a first fine positioning hole. Then, the second positioning hole is adjusted to rotate along the axis of the first fine positioning hole so that its axial projection covers the second positioning hole, thus creating a second fine positioning hole. The distance between the first and second fine positioning holes obtained through this application remains constant, and the height difference between their horizontal projections is within a first preset error allowable range. This ensures interchangeable assembly of the first and second components, and that the assembly accuracy of the first and second components meets design requirements. This facilitates rapid repair and replacement of the first and second components during use, meeting the requirements of various application scenarios. The drilling jig of this application is obtained independently, which avoids the transmission of errors during the manufacturing process of the first and second components, effectively ensuring the positional accuracy requirements of the first and second precision positioning holes, and improving the compatibility of the first and second components. Attached Figure Description

[0055] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0056] Figure 1 This is a schematic diagram of an exemplary method for manufacturing a mating hole according to this application;

[0057] Figure 2 This is an exemplary flowchart of obtaining a drill jig for this application;

[0058] Figure 3 For this application Figure 2 An exemplary schematic diagram of step S230;

[0059] Figure 4 This is a schematic diagram illustrating an exemplary positioner participating in a method for fabricating a docking hole according to this application;

[0060] Figure 5 A flowchart is provided for obtaining an exemplary locator in this application;

[0061] Figure 6 For this application Figure 5 An exemplary detailed diagram of step S530

[0062] Figure 7 This is a schematic diagram of an exemplary drill jig obtained according to this application;

[0063] Figure 8 This is a schematic diagram obtained from an exemplary locator of this application;

[0064] Figure 9 This is an exemplary wing assembly diagram of this application;

[0065] Figure 10 This is an exemplary fuselage assembly diagram of this application;

[0066] Figure 11 This is a schematic diagram of the connection holes between the fuselage and wing, as exemplified in this application.

[0067] Figure 12 This is an exemplary schematic diagram of the fuselage and wing assembly according to this application;

[0068] Figure 13 This is a schematic diagram of an exemplary wing placed on a wing leveling device according to this application;

[0069] Figure 14 This is an exemplary schematic diagram of the connection between the wing drill jig and the wing in this application;

[0070] Figure 15 This is a schematic projection of an exemplary connection hole on a wing according to this application;

[0071] Figure 16 This is a schematic diagram of an exemplary wing skew in this application;

[0072] Figure 17 This is a schematic diagram of the fuselage of this application placed on the leveling equipment;

[0073] Figure 18 This is an exemplary schematic diagram of the connection between the fuselage drilling jig and the fuselage in this application;

[0074] Figure 19 This is a schematic diagram of the projection of the connection hole on an exemplary body of this application;

[0075] Figure 20 This is an exemplary schematic diagram of fuselage tilting according to this application;

[0076] Figure 21 This is an exemplary schematic diagram of fuselage and wing engagement according to this application;

[0077] Figure 22 This is a schematic diagram illustrating the dimensional fit of an exemplary fuselage and wing during engagement, as described in this application.

[0078] Figure 23 This is a schematic diagram of an exemplary fuselage and wing docking method according to this application;

[0079] Figure 24This is a schematic diagram of an exemplary apparatus for manufacturing a mating hole according to this application.

[0080] Component designation explanation

[0081] 100. Fuselage; 110. Front frame of fuselage; 120. Rear frame of fuselage;

[0082] 200. Wing; 210. Wing front spars; 220. Wing rear spars;

[0083] 300. Drill jig; 310. Fuselage drill jig; 311. Fuselage drill jig body; 320. Wing drill jig; 321. Wing drill jig body; 330. First positioning hole; 331. First coordinating bushing hole; 340. Second positioning hole; 341. Second coordinating bushing hole; 350. Scale; 360. Level;

[0084] 400, Positioner; 410, Fuselage Positioner; 411, Fuselage Positioner Body; 420, Wing Positioner; 421, Wing Positioner Body; 430, First Initial Positioning Hole; 440, Second Initial Positioning Hole;

[0085] 510. Wing leveling equipment; 520. Fuselage leveling equipment. Detailed Implementation

[0086] The following specific examples illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, unless otherwise specified, the following embodiments and features can be combined with each other. It should also be understood that the terminology used in the embodiments of the present invention is for describing specific implementation schemes and not for limiting the scope of protection of the present invention. Test methods in the following embodiments that do not specify specific conditions are generally performed under conventional conditions or according to the conditions recommended by the respective manufacturers.

[0087] When numerical ranges are given in the embodiments, it should be understood that, unless otherwise stated in the present invention, both endpoints of each numerical range and any value between the two endpoints may be selected. Unless otherwise defined, all technical and scientific terms used in this invention, as well as the prior art known to those skilled in the art and the description of this invention, may be implemented using any prior art methods, devices, and materials similar to or equivalent to those described, used, or made of materials in the embodiments of this invention.

[0088] It should be noted that the terms such as "upper", "lower", "left", "right", "middle" and "one" used in this specification are only for clarity of description and are not intended to limit the scope of the invention. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered as part of the scope of the invention.

[0089] This application provides a method for manufacturing mating holes, used to process mating holes in the mating areas of a first component and a second component that are connected via four holes. This method can improve existing problems such as poor component interchangeability and inconvenient maintenance. The first component and the second component are mated using a four-hole mating method, meaning that both the first and second components have two mating holes. The mating holes on the first and second components are then matched in pairs for connection and fixation. Please refer to [link to relevant documentation]. Figure 1 The specific steps for fabricating the mating holes are as follows:

[0090] Step S110: Make a first coarse positioning hole and a second coarse positioning hole on the docking area.

[0091] For example, during the production stages of the first and second components, a first coarse positioning hole and a second coarse positioning hole need to be fabricated on both components. For example, the first and second coarse positioning holes are directly machined during the production of the first and second components to ensure the basic precision requirements of the mating holes. For example, taking the mating of the fuselage and wing as an example, where the fuselage corresponds to the first component and the wing corresponds to the second component, the mating areas of both the fuselage and the wing need to have the first and second coarse positioning holes fabricated.

[0092] For example, taking the fuselage and wing as an example, the mating area includes the front frame and rear frame of the fuselage on the fuselage, and the front spars and rear spars of the wing on the wing. A first coarse positioning hole and a second coarse positioning hole are formed in the mating area. After the fuselage and the wing are mated, the first coarse positioning holes are all coaxial, and the second coarse positioning holes are all coaxial.

[0093] Step S120: Provide a drill jig that matches and mates with the mating area, the drill jig including a first positioning hole and a second positioning hole.

[0094] For example, the drill jig includes a first component drill jig and a second component drill jig. The first component drill jig matches the mating area on the first component, and the second component drill jig matches the mating area on the second component. The drill jig is machined independently of the first and second components to avoid the assembly errors of the first and second components affecting the accuracy of the drill jig. For example, taking the fuselage and wing of an aircraft as an example, the drill jig includes a fuselage drill jig and a wing drill jig.

[0095] Please see Figure 2The specific steps for obtaining a drill jig are as follows:

[0096] Step S210: Obtain the digital model of the docking area

[0097] Data on the first and second components in their docking areas is extracted using digital models of the assembly. Transmitting this data through the digital model improves transmission speed and effectively ensures the accuracy of the docking area data. For example, the docking area data includes two parts: data from the docking area on the first component and data from the docking area on the second component, with the data from the two docking areas matching. Similarly, the digital model of the docking area also includes two parts from the first and second components. Taking the fuselage and wing of an aircraft as an example, data on the fuselage and wing in their docking areas is extracted using the aircraft's digital model, ensuring the accuracy of the docking area data.

[0098] Step S220: Obtain the drill jig digital model based on the docking area digital model.

[0099] A digital model of the drill jig is constructed using a digital model of the docking area. For example, the drill jig digital model includes a first component drill jig digital model and a second component drill jig digital model. The first component drill jig digital model can be constructed from the docking area digital model on the first component or from the docking area digital model on the second component, depending on the actual needs. Preferably, the first component drill jig digital model is constructed from the docking area digital model on the first component to facilitate the docking and matching of the first component drill jig with the first component. Similarly, the second component drill jig digital model can be constructed from the docking area digital model on the second component or from the docking area digital model on the first component; preferably, the second component drill jig digital model is constructed from the docking area digital model on the second component. In one embodiment, the drill jig digital model includes a fuselage drill jig digital model and a wing drill jig digital model.

[0100] Step S230: The drill jig is manufactured according to the drill jig digital model.

[0101] The first component drill jig and the second component drill jig are fabricated based on the first component drill jig digital model and the second component drill jig digital model, respectively. From extracting data of the first and second components in the docking area using the aircraft's digital model to constructing the drill jig digital model, the entire process utilizes CAD / CAM technology for digital geometric model dimensional transfer, thereby ensuring the accuracy of the drill jig data and the accuracy of the reference for obtaining the docking hole through drill jig coordination, thus ensuring the accuracy of the obtained docking hole. In one embodiment, the fuselage drill jig and the wing drill jig are fabricated based on the fuselage drill jig digital model and the wing drill jig digital model, respectively.

[0102] Please see Figure 3The present paper illustrates an exemplary process for machining a drill jig based on the drill jig digital model. The specific steps are as follows:

[0103] Step S310: The first component drill jig body and the second component drill jig body are respectively manufactured according to the first component drill jig digit model and the second component drill jig digit model.

[0104] For example, the main body of the first component drill jig is obtained by CNC machining or other machining methods based on the first component drill jig model; the main body of the second component drill jig is obtained by CNC machining or other machining methods based on the second component drill jig model.

[0105] Step S320: Connect the first component drill jig body and the second component drill jig body in the combined state of the first component and the second component.

[0106] The first and second drill jig bodies are connected in the combined state of the first and second parts, which facilitates the common positioning holes on the first and second drill jig bodies. The positioning holes on the first and second drill jigs are under a unified datum, ensuring that the coordination and dimensional relationship between the positioning holes on the first and second drill jigs meet the tolerance requirements, and effectively improving the accuracy of the first and second drill jigs.

[0107] Step S330: A first coordinating bushing hole and a second coordinating bushing hole are jointly formed on the first component drill jig body and the second component drill jig body, wherein the second coordinating bushing hole is an arc-shaped slot with the center of the first coordinating bushing hole as the center.

[0108] When the first component drill jig body and the second component drill jig body are combined, a first coordinating bushing hole is jointly produced. For example, the axis of the first coordinating bushing hole coincides with the axis of the first positioning hole.

[0109] A second coordinating bushing hole is jointly manufactured. For example, the second coordinating bushing hole is an arc-shaped slot hole, and the center of the arc is the center of the first coordinating bushing hole. In other words, the distance from any point on the center line of the first coordinating bushing hole to the center of the first coordinating bushing hole is equal, thereby ensuring that the distance between the first precision positioning hole and the second precision positioning hole remains constant, thus meeting the basic requirement of interchangeability between the first component and the second component.

[0110] Step S340: Separate the first component drill jig body and the second component drill jig body, and install bushings in the first coordinating bushing hole and the second coordinating bushing hole respectively, wherein the bushing in the second coordinating bushing hole slides along the second coordinating bushing hole.

[0111] Separate the first component drill jig body and the second component drill jig body, and install bushings in the first and second coordinating bushing holes respectively. For example, the bushings in the first and second coordinating bushing holes can be of the same or different specifications. Bushings of the same specifications are preferred to facilitate processing, while ensuring that the first and second precision positioning holes are the same size to facilitate the use of the same connectors.

[0112] For example, the inner diameter of the first coordinating bushing hole is the same as the outer diameter of the bushing, which facilitates the bushing being inserted into the first coordinating bushing hole.

[0113] For example, the radius difference of the arc on both sides of the second coordinating bushing hole is the same as the outer diameter of the bushing, so as to facilitate the bushing being inserted into the second coordinating bushing hole and to allow the bushing to slide along the second coordinating bushing hole, that is, the bushing in the second coordinating bushing hole rotates about the axis of the bushing in the first coordinating bushing hole.

[0114] For example, the bushing inner hole installed in the first coordinating bushing hole is the first positioning hole, and the bushing inner hole installed in the second coordinating bushing hole is the second positioning hole.

[0115] For example, the inner diameter of the bushing is the same as the inner diameter of the mating hole, so that the mating hole can be made according to the bushing.

[0116] For example, a level and a ruler are installed on the drill jig. The level is used to observe whether the drill jig is level, and the ruler is used to observe the position of the bushing hole inside the second coordinating bushing hole. Please refer to [link to relevant documentation]. Figure 7 As shown, the level and scale are installed in a convenient position for the drill jig to observe. In other words, after the level and scale are installed, the level and scale of the first drill jig can be easily observed after the first part drill jig is connected to the first part; after the second part drill jig is connected to the second part, the level and scale of the second drill jig can be easily observed by the engineer. Preferably, the scale is installed at the edge of the second coordinating bushing hole to facilitate viewing the position of the bushing inside the second coordinating bushing hole.

[0117] Please see Figure 7 , Figure 7 Taking the fuselage and wing of an aircraft as examples, the specific process of producing fuselage and wing drilling jigs by combining fuselage drilling jigs and wing drilling jigs is shown.

[0118] Please continue reading. Figure 1 Step S130: Adjust both the docking area and the drill jig to a horizontal state, and make the projection of the first positioning hole along the axial direction cover the first coarse positioning hole, and make the first fine positioning hole using the first positioning hole as the mold hole.

[0119] The first precision positioning holes on the first component and the second component are each manufactured independently. For example, after the first component is assembled, it is placed on a first component leveling device. Taking the machine body as an example, ... Figure 17 As shown, the machine body leveling equipment is used to level the machine body, adjusting the docking area to be horizontal, i.e., adjusting the machine body to be level. Adjusting the machine body level refers to adjusting the machine body to the correct posture and parking in a horizontal position. The machine body drill jig is leveled, as shown... Figure 18 As shown, exemplarily, the machine body drilling jig is adjusted to a horizontal state by its own leveling device, and the axial projection of the first fine positioning hole on the machine body drilling jig onto the first coarse positioning hole on the machine body covers the first coarse positioning hole on the machine body. The first coarse positioning hole on the machine body is enlarged through the first fine positioning hole to form the first fine positioning hole. Exemplarily, the machine body drilling jig is connected to the machine body using connecting parts such as process bolts, ensuring that the machine body leveling equipment remains in a horizontal position.

[0120] For example, when the machine body drill jig is being leveled, the machine body drill jig can be fixed or abutted against the machine body using other auxiliary tools to facilitate leveling of the machine body drill jig and to facilitate observation of the relationship between the first positioning hole and the first coarse positioning hole.

[0121] Similarly, taking the wing as an example (the second component), after the wing itself is assembled, it is placed on the wing leveling equipment, such as... Figures 13-14 As shown, perform the same operations as those on the fuselage and fuselage drilling jig on the wing and wing drilling jig to obtain the first precision positioning hole on the wing.

[0122] For example, the fuselage is provided with two first precision positioning holes, and the two first precision positioning holes on the fuselage are coaxial; the wing is provided with two first precision positioning holes, and the two first precision positioning holes on the wing are coaxial.

[0123] Step S140: Rotate the second positioning hole around the axis corresponding to the first fine positioning hole within a first set error range until the projection of the second positioning hole along the axial direction covers the second coarse positioning hole, and use the second positioning hole as a mold hole to make the second fine positioning hole.

[0124] Rotate the second positioning hole around the axis of the first precision positioning hole within a first set error range until the axial projection of the second positioning hole covers the second coarse positioning hole. Then, the second precision positioning hole is made through the second positioning hole, and the axes of the second positioning hole and the second precision positioning hole coincide.

[0125] By rotating the second positioning hole around the axis of the first precision positioning hole, the distance between the second and first precision positioning holes is ensured to be a fixed value. This guarantees that when the first and second components are docked, their docking holes can be perfectly matched, meeting the basic requirements of interchangeability. The second positioning hole rotates within a first set error range. For example, the first set error is the height difference between the first and second precision positioning holes, that is, the distance between their horizontal projections. This first set error ensures that the height difference between the first and second precision positioning holes is within a preset range, thereby meeting the skewness requirements of the first and second components. Taking the fuselage and wing as an example, this ensures that the skewness of the aircraft is within a reasonable range after the fuselage and wing are assembled.

[0126] For example, the first component and the second component each have two second precision positioning holes, the axes of the two second precision positioning holes on the first component coincide, and the axes of the two second precision positioning holes on the second component coincide.

[0127] Please see Figures 15-16 For example, taking an airfoil as an example, the mating holes of the airfoil include two first precision positioning holes and two second precision positioning holes. The two first precision positioning holes of the airfoil are hole A1 and hole C1, and the axes of hole A1 and hole C1 coincide. The two second precision positioning holes are hole B1 and hole D1, and the axes of hole B1 and hole D1 coincide. Hole A1 and hole B1 are on the same side, and hole C1 and hole D1 are on the same side. The height difference between the projections of hole A1 and hole B1 along the horizontal direction is H2, and the height difference between the projections of hole C1 and hole D1 along the horizontal direction is H1. H1 and H2 have the same value and the same direction. For example, H1=H2≤X, the skew limit height between the docking holes on the same side of the fuselage and the wing is 2X. In other words, the skew value between the A1 hole and the B1 hole on the wing is not greater than half of the skew limit at the same position on the aircraft. This ensures that after the fuselage and the wing are assembled, the total skew value of the fuselage and the wing is less than the skew limit at the same position on the aircraft, and that the aircraft meets the design requirements after the fuselage or the wing is interchanged.

[0128] Please see Figures 19-20For example, taking the fuselage as an example, the fuselage has two first precision positioning holes and two second precision positioning holes. The two first precision positioning holes are A2 and C2, and their axes coincide. The two second precision positioning holes are B2 and D2, and their axes coincide. A2 and B2 are on the same side, as are C2 and D2. The height difference between the horizontal projections of A2 and B2 is h2, and the height difference between the horizontal projections of C2 and D2 is h1. h2 and h1 have the same value and the same direction. For example, h1 = h2 ≤ X, and the skew limit height between the fuselage and wing docking holes on the same side is 2X. In other words, the range of the first set error is -X to X, thus satisfying h1 = h2 ≤ X. The skew value between holes A2 and B2 on the fuselage is no greater than half of the skew limit at the same position on the aircraft. This ensures that after the fuselage and wing are assembled, the total skew value of the fuselage and wing is less than the skew limit at the same position on the aircraft, and that the aircraft meets the design requirements after the fuselage or wing is interchanged.

[0129] Please see Figures 21-22 For example, when the fuselage and wing are engaged, the wing is directly above the fuselage. The wing and fuselage are engaged, that is, the wing moves towards the fuselage (moves downward) to achieve the connection of the docking holes, namely A1 / A2 connection, B1 / B2 connection, C1 / C2 connection, and D1 / D2 connection.

[0130] Wings: A1 and C1 are coaxial, B1 and D1 are coaxial; H1 = H2;

[0131] Fuselage: A2 and C2 are coaxial, B2 and D2 are coaxial; h1 = h2;

[0132] Length of A1B1 = Length of A2B2 = Length of C1D1 = Length of C2D2;

[0133] Before engagement, the wing is directly above the fuselage, i.e., F1 = F2; (F2: distance from wing hole A1 to fuselage hole A2; F1: distance from wing hole C1 to fuselage hole C2)

[0134] The distance between B1 and B2 = F2 + H2 - h2 = F3;

[0135] The distance between D1 and D2 = F1 + H1 - h1 = F4;

[0136] When F1 = F2 = F3 = F4, the wing moves downwards a distance F1. The holes A1, B1, C1, and D1 on the wing become coaxial with the holes A2, B2, C2, and D2 on the fuselage, respectively, thus achieving successful alignment. In other words, when h1 - H1 = 0 and h2 - H2 = 0, the wing can achieve alignment by moving downwards.

[0137] Rotate the wing around axis A1C1 until h1 = H1 (at this point, the positions of holes A1 and C1 remain unchanged), then move F1 downwards to achieve smooth alignment. Since h1 = h2 ≤ X and H1 = H2 ≤ X, the Z-axis skew distance between holes A and B after alignment is ≤ 2X, and the Z-axis skew distance between holes C and D is ≤ 2X, which meets the design wing skew requirements.

[0138] Smaller first and second coarse positioning holes are set in the docking area. After assembly, the first and second coarse positioning holes will deform due to assembly stress during the assembly process, and the distance between the first and second coarse positioning holes will also change accordingly. This application uses drilling jigs to coordinate hole making, which effectively ensures the positional and dimensional relationship between the first and second fine positioning holes. The docking holes made on the fuselage and wings by the method of this application meet the interchangeability requirements, improve the speed of maintenance and replacement, and are suitable for use in multiple scenarios and under multiple conditions.

[0139] For example, the method for manufacturing the mating hole further includes providing a locator, which is used to coarsely position the first coarse locating hole and the second coarse locating hole during the assembly of the first component and the second component. The steps of using the locator are as follows: Figure 1 For information between S110 and S120, please refer to [link / reference]. Figure 4 The details are as follows:

[0140] Step S410: Provide a locator that matches and docks with the docking area, the locator including a first positioning part and a second positioning part.

[0141] For example, the locator includes a first component locator and a second component locator. In one embodiment, the first component is a fuselage and the second component is a wing. The locator includes a fuselage locator and a wing locator. For example, the fuselage locator is disposed on a fuselage assembly frame to position the first coarse positioning hole and the second coarse positioning hole. The mating areas on the fuselage are the front frame and the rear frame, and the fuselage locator matches the front frame and the rear frame.

[0142] Step S420: Connect the first positioning part to the first coarse positioning hole, and connect the second positioning part to the second coarse positioning hole.

[0143] In one embodiment, the first positioning part is a first initial positioning hole, and the second positioning part is a second initial positioning hole. The first initial positioning hole is connected to the first coarse positioning hole by a positioning pin, and the second initial positioning hole is connected to the second coarse positioning hole by a positioning pin, so as to position and limit the first coarse positioning hole and the second coarse positioning hole through the first initial positioning hole and the second initial positioning hole.

[0144] Step S430: Assemble the components of the first component or the second component in the mating area to complete the assembly of the first component or the second component.

[0145] For example, taking the fuselage and wings as examples, such as Figure 10 As shown, the front and rear frames of the fuselage are positioned using fuselage locators, and other fuselage components are then assembled onto the front and rear frames until the fuselage assembly is complete. Figure 9 As shown, the wing locator is used to position the wing front spars and wing rear spars, and then the other wing components are assembled onto the wing front spars and wing rear spars until the wing assembly is complete.

[0146] By using a positioner to position and limit the docking area, it is effectively ensured that the basic dimensional relationship between the first coarse positioning hole and the second coarse positioning hole is maintained during the assembly process, reducing the possibility of excessive dimensional changes between the first coarse positioning hole and the second coarse positioning hole during the assembly process.

[0147] Please see Figure 5 , Figure 8 The locator is obtained independently, and the specific steps include:

[0148] Step S510: Obtain the digital model of the docking area.

[0149] The docking area digital model includes the docking area digital model on the first component and the docking area digital model on the second component.

[0150] Step S520: Obtain the locator digital model based on the docking area digital model.

[0151] Based on the digital model of the docking area, a digital model of the locator is constructed. The locator digital model includes a first component locator digital model and a second component locator digital model. In one embodiment, the locator digital model includes a fuselage locator digital model and a wing locator digital model. The fuselage locator digital model can be constructed from the docking area digital model on the fuselage or the docking area digital model on the wing. Preferably, the fuselage locator digital model is constructed from the docking area digital model on the fuselage. The wing locator digital model can be constructed from the docking area digital model on the wing or the docking area digital model on the fuselage. Preferably, the wing locator digital model is constructed from the docking area digital model on the wing.

[0152] Step S530: The positioner is manufactured by machining the positioner digital model.

[0153] The positioner is manufactured using CNC machining or other machining methods based on the digital model of the positioner. Please refer to [link / reference]. Figure 6 The specific steps for manufacturing the positioner based on the positioner's digital model include:

[0154] Step S610: Produce the main body of the first component positioner and the main body of the second component positioner according to the first component positioner digital model and the second component positioner digital model respectively.

[0155] By constructing digital models of the first and second component positioners using CAD / CAM technology, dimensional tolerances can be reduced, effectively ensuring design and manufacturing accuracy. The first component positioner body is manufactured using machining based on the first component positioner model, and the second component positioner body is manufactured using machining based on the second component positioner model.

[0156] Step S620: Connect the first component locator body and the second component locator body in the state of the first component and the second component combined.

[0157] For example, the first component locator body and the second component locator body are docked in the state of the first component and the second component combined to ensure that the first initial positioning hole and the second initial positioning hole at the corresponding positions on the first component locator and the second component locator are accurately positioned, thereby improving the overall accuracy and fit.

[0158] Step S630: A first bushing hole and a second bushing hole are jointly formed on the first component locator body and the second component locator body.

[0159] Step S640: Separate the first component locator body from the second component locator body, and install bushings in the first bushing hole and the second bushing hole respectively to form a locator.

[0160] Please see Figure 8 For example, taking the fuselage and wing as examples, the fuselage positioner and wing positioner are manufactured based on the fuselage positioner digital model and the wing positioner digital model.

[0161] In one embodiment, no bushing is required in the first bushing hole and the second bushing hole. A locating pin connects the first bushing hole and the first coarse locating hole, and a locating pin also connects the second bushing hole and the second coarse locating hole, thus satisfying the positioning and limiting requirements. Preferably, the inner diameter of the first bushing hole is the same as the inner diameter of the first coarse locating hole, and the inner diameter of the second bushing hole is the same as the inner diameter of the second coarse locating hole. In another embodiment, a bushing is installed in the first bushing hole, and the inner diameter of the bushing is the same as the inner diameter of the first coarse locating hole; a bushing is also installed in the second bushing hole, and the inner diameter of the bushing installed in the second bushing hole is the same as the inner diameter of the second coarse locating hole. This reduces wear on the positioner body, increases the positioner's service life, and ensures the positioner's accuracy requirements. Preferably, the bushings installed in the first bushing hole and the second bushing hole are of the same specification to facilitate replacement and ensure uniformity.

[0162] This application also provides a docking method for docking a first component and a second component with four holes, wherein the docking areas of the first component and the second component are provided with docking holes made according to the docking hole manufacturing method of any of the above claims.

[0163] Connect the mating holes at corresponding positions of the first and second components to achieve the mating of the first and second components.

[0164] Please see Figure 23 , Figure 23 Taking the fuselage and wing as an example, the docking method of the fuselage and wing is shown. First, the structural digital model of the docking area is obtained through the aircraft digital model. Then, the docking area is divided into three routes based on the digital model of the docking area: the wing assembly route, the fuselage assembly route, and the drill jig coordinated drilling.

[0165] The wing assembly process involves creating a wing locator model using the aircraft's digital model, machining the wing locator using CNC machining, positioning the first and second coarse positioning holes on the wing's front and rear spars for docking with the fuselage, and then assembling the wing.

[0166] The fuselage assembly process involves creating a fuselage locator model using the aircraft's digital model, machining the fuselage locator using CNC machining, positioning the first and second coarse positioning holes on the front and rear fuselage frames for docking with the wings, and then assembling the fuselage.

[0167] Drilling jigs are used to coordinate drilling. Based on design requirements, wing and fuselage drill jigs are created using digital models. The wing and fuselage drill jigs are then CNC machined. The drill jigs participate in the finishing of the wing and fuselage. Specifically, the first and second precision positioning holes on the fuselage and wing are made through the first and second positioning holes on the drill jigs. The first and second precision positioning holes are made on leveling equipment, with the fuselage placed on the fuselage leveling equipment and the wing placed on the wing leveling equipment, to ensure the coordination and accuracy of the wing-fuselage connection holes when the wing and fuselage are joined.

[0168] After obtaining the first and second precision positioning holes, the fuselage and wing are aligned. All the first precision positioning holes and all the second precision positioning holes of the fuselage and wing are coaxial. The alignment and fixation of the fuselage and wing are achieved through the connector.

[0169] The method of docking the fuselage and wings has the following beneficial effects:

[0170] 1. In the coordinated route, the positioners are all directly input into the CNC equipment, and the machining center processes them in one go, with high precision and no data transmission error.

[0171] 2. The wings and fuselage are manufactured independently, resulting in high production efficiency.

[0172] 3. By using wing and fuselage drilling jigs, first and second precision positioning holes are respectively made on the wing and fuselage, allowing for docking of the wing and fuselage. The wing and fuselage can be interchangeably docked, improving interchangeability and maintainability. The wing and fuselage drilling jigs effectively control the impact of wing and fuselage assembly errors on the wing-fuselage docking, ensuring that the assembled fuselage and wing errors meet requirements.

[0173] This application also provides a device for manufacturing a mating hole, including a drill jig 300. The drill jig 300 is provided with a first positioning hole 330 and a second positioning hole 340. The second positioning hole 340 rotates around the axis of the first positioning hole 330 within a first set error range. For example, the drill jig includes a first component drill jig and a second component drill jig. Taking a fuselage and a wing as examples, the drill jig 300 includes a fuselage drill jig 310 and a wing drill jig 320. The first positioning hole 330 and the second positioning hole 340 of the fuselage drill jig 310 and the wing drill jig 320 are co-manufactured in the mating state.

[0174] For example, please refer to Figure 24 The drill jig 300 is provided with a first bushing hole and a second bushing hole. The second bushing hole is an arc-shaped slot, with the center of the arc being the center of the first bushing hole. In other words, any point on the centerline of the second bushing hole is equidistant from the center of the first bushing hole. Both the first and second bushing holes are fitted with bushings. The inner hole of the bushing in the first bushing hole is a first positioning hole 330, and the inner hole of the bushing in the second bushing hole is a second positioning hole 340. The bushing in the second bushing hole slides along the second bushing hole, that is, the bushing in the second bushing hole rotates around the axis of the bushing in the first bushing hole, thereby ensuring that the distance between the first positioning hole 330 and the second positioning hole 340 remains constant. The mating holes between the first and second components obtained through the drill jig of this application can meet the interchangeability requirements of the first and second components. Especially for aircraft fuselages and wings, it facilitates the replacement of the aircraft fuselage or wing, simplifying maintenance and adapting to various usage scenarios.

[0175] For example, the drill jig 300 is also provided with a scale and a level, the scale being used to observe the position of the second positioning hole 340 and the level being used to observe the level of the drill jig.

[0176] Therefore, this invention effectively overcomes some practical problems in the prior art, thus possessing high utilization value and significance. The above embodiments are merely illustrative of the principles and effects of this invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this invention should still be covered by the claims of this invention.

Claims

1. A method for manufacturing mating holes, used to process mating holes in the mating areas of a first component and a second component that are mated through four holes, characterized in that, The manufacturing method includes: A first coarse positioning hole and a second coarse positioning hole are made in the docking area; A drill jig is provided that matches the docking area, the drill jig including a first positioning hole and a second positioning hole; The docking area and the drill jig are both adjusted to a horizontal state, and the projection of the first positioning hole along the axial direction covers the first coarse positioning hole, and the first positioning hole is used as the mold hole to make the first fine positioning hole. The second positioning hole is rotated around the axis corresponding to the first fine positioning hole within a first set error range until the projection of the second positioning hole along the axial direction covers the second coarse positioning hole, and the second positioning hole is used as a mold hole to make the second fine positioning hole. Obtaining the drill jig includes machining the drill jig according to the drill jig digital model; The drill jig includes a first component drill jig and a second component drill jig. The drill jig is manufactured by machining according to the drill jig digital model, including: The main body of the first component drill jig and the main body of the second component drill jig are respectively manufactured according to the first component drill jig digital model and the second component drill jig digital model; Connect the first component drill jig body and the second component drill jig body in the combined state of the first component and the second component; A first coordinating bushing hole and a second coordinating bushing hole are jointly formed on the first component drill jig body and the second component drill jig body, wherein the second coordinating bushing hole is an arc-shaped slot hole with the center of the first coordinating bushing hole as the center. Separate the first component drill jig body and the second component drill jig body, and install bushings in the first coordinating bushing hole and the second coordinating bushing hole respectively, wherein the bushing in the second coordinating bushing hole slides along the second coordinating bushing hole.

2. The method for manufacturing a mating hole according to claim 1, characterized in that, The manufacturing method further includes: A locator is provided that matches and docks with the docking area, the locator comprising a first positioning part and a second positioning part; Connect the first positioning part to the first coarse positioning hole, and connect the second positioning part to the second coarse positioning hole; The parts of the first component or the second component are assembled in the mating area to complete the assembly of the first component or the second component.

3. The method for manufacturing a mating hole according to claim 2, characterized in that, The acquisition of the locator includes: Obtain the digital model of the docking area; The locator digital model is obtained based on the docking area digital model; The positioner is manufactured by machining the positioner digital model.

4. The method for manufacturing a mating hole according to claim 3, characterized in that, The positioner includes a first component positioner and a second component positioner. The positioner is manufactured by machining a digital model of the positioner, including: The first component positioner body and the second component positioner body are produced according to the first component positioner digital model and the second component positioner digital model, respectively. The first component locator body and the second component locator body are docked in the combined state of the first component and the second component; A first bushing hole and a second bushing hole are jointly formed on the first component positioner body and the second component positioner body; Separate the first component locator body from the second component locator body, and install bushings in the first bushing hole and the second bushing hole respectively.

5. The method for manufacturing a mating hole according to claim 1, characterized in that, Obtaining the drill jig digital model includes: Obtain the digital model of the docking area; The drill jig digital model is obtained based on the docking area digital model.

6. The method for manufacturing a mating hole according to claim 1, characterized in that, The drill jig is equipped with a level and a ruler.

7. The method for manufacturing a mating hole according to claim 1, characterized in that, The first component is the fuselage, and the second component is the wing.

8. The method for manufacturing a mating hole according to claim 7, characterized in that, The docking area includes: A front frame of the fuselage is disposed on the fuselage, and the first precision positioning hole and the second precision positioning hole are formed on the front frame of the fuselage. A rear frame is disposed on the body of the machine, and the first precision positioning hole and the second precision positioning hole are formed on the rear frame of the machine. A wing front spars are disposed on the wing and configured to connect with the fuselage front frame. The wing front spars are provided with a first precision positioning hole and a second precision positioning hole. A wing rear spars are provided on the wing and configured to connect with the rear frame of the fuselage. The wing rear spars are provided with a first precision positioning hole and a second precision positioning hole. Wherein, after the fuselage and the wing are aligned, the first precision positioning holes are all coaxial, and the second precision positioning holes are all coaxial.

9. A docking method for docking a first component and a second component with four holes, characterized in that, include: The mating areas of the first component and the second component are both provided with mating holes made according to the method described in any one of claims 1 to 8; Connect the corresponding docking holes of the first component and the second component to achieve the mating of the fuselage and the wing.

10. An apparatus for manufacturing a mating hole, characterized in that, include: The drill jig is provided with a first positioning hole and a second positioning hole, and the second positioning hole rotates around the axis of the first positioning hole within a first set error range; The drill jig includes a first component drill jig and a second component drill jig, wherein the first positioning hole and the second positioning hole of the first component drill jig and the second component drill jig are co-fabricated in a mating state; The process of obtaining the drill jig includes machining the drill jig according to the drill jig digital model. The drill jig is manufactured by machining the drill jig digital model, including: The main body of the first component drill jig and the main body of the second component drill jig are respectively manufactured according to the first component drill jig digital model and the second component drill jig digital model; Connect the first component drill jig body and the second component drill jig body in the combined state of the first component and the second component; A first coordinating bushing hole and a second coordinating bushing hole are jointly formed on the first component drill jig body and the second component drill jig body, wherein the second coordinating bushing hole is an arc-shaped slot hole with the center of the first coordinating bushing hole as the center. Separate the first component drill jig body and the second component drill jig body, and install bushings in the first coordinating bushing hole and the second coordinating bushing hole respectively, wherein the bushing in the second coordinating bushing hole slides along the second coordinating bushing hole.

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