Deformation control machining method and adaptive clamping device for aircraft alloy steel structural components

Abstract

This invention belongs to the field of mechanical manufacturing equipment technology, and specifically relates to a deformation control processing method and adaptive clamping device for aircraft alloy steel structural parts. The device includes: a base plate (1), spring steel sheets (2) and multiple process joints (3); the base plate (1) is a rectangular base, and the upper end face is distributed with mounting grooves (10) in an equally spaced matrix array, and spring steel sheets (2) are installed in the mounting grooves (10); the upper end face of the base plate is also distributed with equally spaced threaded holes (4) and positioning pin holes (5); multiple process joints are connected around the structural part to be processed, of which two process joints (3) are installed on the positioning pin holes (5) located on the same straight line to form a processing reference axis, and the remaining process joints (3) are distributed on both sides of the reference axis; the process joints (3) are provided with grooves (6) in the thickness direction of the raw material, and pressure plates are inserted into the grooves and the pressure plates are locked and fixed to the base plate by bolts.

Description

Technical Field

[0001] This invention belongs to the field of mechanical manufacturing equipment technology, and specifically relates to a deformation control processing method and adaptive clamping device for aircraft alloy steel structural parts. Background Technology

[0002] Currently, there are many types of aircraft parts known in this field, especially connector parts, which are irregularly shaped and have complex and irregular structures.

[0003] The machining process for complex, irregularly shaped aircraft parts, especially complex high-strength alloy steel structural components, is extremely complex. The deformation of the parts themselves and after heat treatment has a significant impact on quality and machining cycle time, making it one of the most challenging problems in the machining process. The typical machining process involves leaving a pre-defined blank space and repeatedly clamping the parts to achieve machining. This method is time-consuming, labor-intensive, difficult, and inefficient. Summary of the Invention

[0004] Objective of the Invention: To address the aforementioned problems, this invention provides a deformation control machining method and adaptive clamping device for aircraft alloy steel structural components. This addresses the shortcomings of existing machining methods for complex aircraft parts, which require repeated clamping to achieve machining, resulting in time-consuming, labor-intensive, difficult, and inefficient processes. Simultaneously, it effectively eliminates the combined effects of inherent structural deformation and post-heat treatment deformation on the machining process. Summary of the Invention:

[0006] An adaptive clamping device for aircraft alloy steel structural components includes: a base plate 1, spring steel sheets 2, and multiple process joints 3;

[0007] The base plate 1 is a rectangular base with mounting holes arranged in an array at equal intervals on the upper surface. Spring steel sheets 2 are installed in the mounting holes.

[0008] The upper surface of the base plate also features equally spaced threaded holes 4 and locating pin holes 5.

[0009] The structural part to be processed is connected to multiple process joints around its periphery. Two of the process joints 3 are installed on the positioning pin holes 5 located on the same straight line to form a processing reference axis. The remaining process joints 3 are distributed on both sides of the reference axis.

[0010] The process connector 3 has a groove 6 in the thickness direction of the raw material. A pressure plate is inserted into the groove and the pressure plate is locked to the base plate by bolts.

[0011] Furthermore, the upper and lower surfaces of the two process connectors that form the machining reference axis are provided with mounting and positioning holes;

[0012] The two ends of the locating pin are inserted into the locating pin holes on the base plate and the mounting locating holes on the process connector to achieve the installation of the process connector and the base plate.

[0013] Furthermore, the locating pin is a short locating pin with a round head;

[0014] One end is a cylindrical head, the other end is a spherical head, and there is a ring in the middle;

[0015] One end of the ball head is inserted into the process connector, and the other end of the cylindrical head is inserted into the positioning pin hole.

[0016] Furthermore, the mounting holes in the base plate are provided with two threaded holes;

[0017] The spring steel sheet has flat plates at both ends and an arc shape in the middle. One flat plate has a round hole, and the other flat plate has an oblong hole.

[0018] The spring steel sheet is locked at both ends to the mounting holes in the base plate by screws.

[0019] A deformation control processing method for aircraft alloy steel structural components, implemented based on the aforementioned device, comprises the following steps:

[0020] Step 1: Install the structural part to be processed onto the positioning pin holes on the base plate that are in the same straight line through two of the process joints; use the line connecting the centers of the two process joints as the machining reference axis; roughing, semi-finishing, and finishing of the front and back of the part are all done by rotating around the reference axis as the rotation axis;

[0021] Step 2: Install the pressure plate in the groove of the process joint and lock it to the base plate;

[0022] Step 3: Remove the excess material outside the process overlap; removing the excess material can effectively prevent the internal stress in that area from acting directly on the part body, thus avoiding the extrusion deformation caused by the internal stress in that part.

[0023] Step 4: Remove the structural component to be processed from the base plate and reinstall it; release the internal stress deformation generated during the removal of raw material.

[0024] Step 5: Perform rough machining on one side. After the rough machining on one side is completed, disassemble the structural component to be machined, flip it over and reinstall it, and then perform rough machining on the other side.

[0025] Step Six: Remove the roughly machined structural components from the base plate and perform heat treatment;

[0026] Step 7: Install the heat-treated structural component on the base plate and perform single-sided semi-finishing. After the single-sided semi-finishing is completed, disassemble the structural component, flip it over and reinstall it to perform the other side semi-finishing.

[0027] Step 8: Remove the semi-finished structural components from the base plate and reinstall them. Perform single-sided finishing. After single-sided finishing, remove the structural components, flip them over and reinstall them. Perform finishing on the other side. At the end of the machining process, cut off all process overlaps.

[0028] Furthermore, a margin of at least 10mm should be reserved during rough machining to ensure effective containment of thermal deformation after heat treatment. However, the maximum thickness of the entire part after rough machining should not exceed 25mm to fully guarantee the hardenability of the heat treatment.

[0029] Furthermore, the structural components are heat-treated in a naturally suspended state. They cannot be placed on brackets. With the components in a naturally suspended state, there are only two stress points during heat treatment, meaning only one pair of forces are applied to the components, minimizing the impact on heat treatment deformation.

[0030] Furthermore, during semi-finishing, the allowance is uniformly reduced from over 10mm before heat treatment to 3mm-5mm. This allows the internal stress caused by the deformation during heat treatment to be released again. Then, the upper surface of the part is precision milled to correct the semi-finishing reference surface after flipping.

[0031] The beneficial effects of this application are as follows:

[0032] (1) In the adaptive clamping device of this embodiment, the complex high-strength alloy steel structural parts have two process overlaps with positioning holes for part datum positioning. The two holes are located on the same straight line, forming a datum axis. The remaining process overlaps can be arranged as needed. The remaining process overlaps have grooves in the thickness direction. The grooves are used for the pressure application position of the pressure plate, thereby avoiding the upper and lower datum surfaces of the upper and lower parts and avoiding machining interference during the fine finishing of the datum. Then, all the excess raw material areas are removed. Because the key stress points are pre-destroyed, the stress is released in advance before rough machining, avoiding the influence of stress deformation on the machining process.

[0033] (2) By using the adaptive clamping device provided in the embodiments of the present invention, the part clamping method that requires multiple stations (e.g., more than 6 stations) in the traditional process is simplified to two-station clamping in both the forward and reverse directions.

[0034] (3) By using the adaptive clamping device provided in the embodiments of the present invention, it is no longer necessary to manufacture a complete set of special milling tools for each complex structural part of the same family of parts, which greatly saves tooling costs; moreover, the complex high-strength alloy steel structural parts (8) are mostly family of parts, and the production form is a typical multi-variety, small-batch production; the production line changes frequently during the production process. If traditional special tooling is used to clamp the parts, due to the lack of flexibility in the use of tooling, one set of milling tools is used for each part, which has disadvantages such as high manufacturing cost, long production cycle and space occupation; the adaptive clamping device provided in the embodiments of the present invention has these problems;

[0035] (4) The processing method performed by the adaptive clamping device provided in the embodiments of the present invention changes the traditional processing method of reserving the blank process border and realizing the part processing through repeated clamping. The advantages of the process method provided by the present invention are: effectively controlling and eliminating part deformation, greatly simplifying the part processing process, effectively preventing vibration during processing, and improving the surface quality of the part; in addition, for each complex part of the same family of parts, it is no longer necessary to manufacture a set of special milling tools, which saves a lot of tooling costs.

[0036] (5) During the machining of alloy steel structural parts, the superimposed deformation caused by the deformation of the parts themselves can prevent the mounting reference surface from fitting properly with the machine tool platform, easily leading to vibration during machining. This severely affects the surface quality of the parts, and in severe cases, resonance can occur, potentially damaging the cutting tools and fixtures, or even causing serious safety accidents such as parts coming loose. To avoid these problems, shims of different thicknesses and sizes need to be installed at the contact points between the parts and the machine tool surface to ensure a tight fit before machining can proceed. Adjustments are required for different workstations and for different parts based on the actual deformation, which is time-consuming and labor-intensive.

[0037] After the complex high-strength alloy steel structural component (8) is locked in the groove (6) by the pressure plate, the Ω-shaped adaptive spring steel sheet (2) is subjected to downward clamping force and produces elastic deformation, which applies the reaction force of the deformation to the part, thereby effectively eliminating the processing vibration.

[0038] After locking the complex high-strength alloy steel structural component (8) in the groove (6) with a pressure plate, perform semi-finishing of the part, and uniformly process the allowance from more than 10 mm before heat treatment to 3-5 mm, so that the internal stress generated by the deformation of the part during heat treatment can be released again. Then, finish mill the upper surface of the part and correct the semi-finishing reference surface after flipping.

[0039] Release the pressure plate to allow the part to release the processing stress and thermal stress deformation again, flip it over for processing, repeat the steps, and perform semi-finishing on the other side.

[0040] The process of repeating the steps of removing rough material from both sides according to the projected contour → front (rough) → back (rough) → heat treatment → front (semi-finish) → back (semi-finish) → front (finish) → back (finish) is currently being used. The flipping process compensates for the deformation on both sides, thus eliminating some of the deformation's impact. Furthermore, correcting part deformation by removing material is far superior to correcting it by straightening. After final machining, there is no stress accumulation, avoiding stress-laden assembly later. Moreover, the natural aging process eliminates the need for intermediate steps, significantly shortening the part manufacturing cycle. Attached Figure Description

[0041] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0042] Figure 1 This is a structural schematic diagram of a complex aircraft part in an embodiment of the present invention;

[0043] Figure 2 This is a schematic diagram of an adaptive clamping device for complex high-strength alloy steel structural components of aircraft, provided in an embodiment of the present invention.

[0044] Figure 3 This is a schematic diagram of one clamping method for an adaptive clamping device for complex high-strength alloy steel structural components of aircraft, provided in an embodiment of the present invention.

[0045] Figure 4 This is a schematic diagram of another clamping method for clamping complex high-strength alloy steel structural components of aircraft after flipping, provided by the adaptive clamping device for complex high-strength alloy steel structural components of aircraft according to an embodiment of the present invention.

[0046] Figure 5 This is a schematic diagram of the Ω-shaped adaptive spring steel sheet in the adaptive clamping device for complex high-strength alloy steel structural parts of aircraft provided in an embodiment of the present invention;

[0047] Figure 6 This is a schematic diagram of an adaptive base plate in an adaptive clamping device for complex high-strength alloy steel structural parts of aircraft, provided in an embodiment of the present invention.

[0048] Explanation of reference numerals in the attached figures:

[0049] 1. Adaptive base plate; 2. Adaptive spring steel sheet; 3. Process connector; 4. Threaded hole; 5. Locating pin hole; 6. Clamping groove on the ear plate; 7. Round-headed short locating pin; 8. Complex high-strength alloy steel structural component; 9. Pressure plate; 10. Adaptive spring steel sheet mounting groove. Detailed Implementation

[0050] The technical solutions of the embodiments of the present invention will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention are within the scope of protection of the present invention.

[0051] The terms "first," "second," etc., used in the specification and claims of this invention are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that embodiments of the invention can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0052] As explained in the background section above, the difficulty in machining complex and irregularly shaped parts in aircraft is that the machining process involves reserving a blank process frame and repeatedly clamping the parts. This process makes it difficult to control part deformation, especially after heat treatment, and the process deformation is difficult to eliminate. The process preparation before machining is time-consuming and labor-intensive, the machining is difficult, and the machining efficiency is low.

[0053] To address the problems existing in the processing methods of complex aircraft parts, this invention provides an adaptive clamping device and deformation control processing technology for complex high-strength alloy steel structural parts of aircraft. It provides a novel and easy-to-use adaptive clamping device that can construct a virtual reference axis on the part based on the multi-point structure of the complex part through process joints and positioning pin holes, and is flexibly adjustable, thus cleverly realizing the adjustment of the part's attitude.

[0054] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0055] Figure 1 This is a structural schematic diagram of a complex aircraft part in an embodiment of the present invention; Figure 2 This is a schematic diagram of an adaptive clamping device for complex high-strength alloy steel structural components of aircraft, provided in an embodiment of the present invention.

[0056] Figure 3 This is a schematic diagram of one clamping method for an adaptive clamping device for complex high-strength alloy steel structural components of aircraft, provided in an embodiment of the present invention. Figure 4 This is a schematic diagram of another clamping method for clamping complex high-strength alloy steel structural components of aircraft after flipping, provided by the adaptive clamping device for complex high-strength alloy steel structural components of aircraft according to an embodiment of the present invention.

[0057] like Figure 1As shown, in this embodiment of the invention, the clamping object of the adaptive clamping device is, for example, a complex high-strength alloy steel structural component 8 with an irregular shape. The design concept of the adaptive clamping device provided in this embodiment of the invention is based on the structural characteristics of the complex high-strength alloy steel structural component 8, namely, the characteristic of having multiple process lugs. Multiple process joints are set according to requirements. The process joint 3 is provided with positioning pin holes 5 and mounting grooves 6. A virtual machining reference axis is constructed through the center of the holes 5 on the two process joints 3. The orientation flipping of the front and back sides of the part is carried out around this axis.

[0058] like Figure 2 and Figure 3 and Figure 4 As shown in the figure, the adaptive clamping device for complex high-strength alloy steel structural components of aircraft provided in this embodiment of the invention includes: an adaptive base plate 1, an adaptive spring steel sheet 2, and multiple process joints 3. It should be noted that the number of process joints 3 is set according to requirements.

[0059] like Figure 2 and Figure 3 and Figure 4 The adaptive clamping device shown in the present invention has an adaptive base plate 1 configured as a rectangular base with a certain thickness, or it can be a base plate of various other symmetrical shapes.

[0060] In this embodiment of the invention, the size of the adaptive base plate 1 can be set according to the needs of part processing, so as to meet the standard of part installation; the threaded holes 4 and the positioning pin holes 5 on the adaptive base plate 1 are both set in a matrix structure.

[0061] In this embodiment of the invention, an adaptive clamping device with the above-described structure is used. The virtual axis of symmetry between the complex high-strength alloy steel structural component 8 and the process-formed parts respectively installed on each process joint 3 is used. The round-headed short positioning pin 7 fixed in the positioning pin hole 5 on the adaptive base plate 1 has self-adaptive properties and can quickly align with the positioning pin hole 5 on the process joint 3. At the same time, it has self-guiding properties, which can enable the complex high-strength alloy steel structural component 8 to be quickly positioned on the adaptive device. The adaptive spring steel plate 2 can quickly adjust the horizontal posture of the complex high-strength alloy steel structural component 8, thereby cleverly realizing the posture adjustment of the part and greatly simplifying the processing technology of such irregular and complex parts. Therefore, the processing technology achieved by using this adaptive clamping device has the characteristics of rapid positioning, flexible adjustment, efficient clamping, and simplicity.

[0062] The adaptive clamping device provided in this embodiment of the invention can ensure that the parts can be flipped along the virtual reference axis no matter how the clamping is arranged. The parts are positioned by the positioning pin hole 5 and the round-headed short positioning pin 7, and then locked by the adaptive spring steel sheet 2 and the pressure plate 9, thereby ensuring the accurate positioning and reliable locking of the parts, and thus achieving reliable processing. In addition, the above-mentioned symmetrical installation structure greatly reduces the number of processing stations for the parts and simplifies the processing steps.

[0063] A deformation control machining process for complex high-strength alloy steel structural components in aircraft.

[0064] Step 1: Select two points of the complex high-strength alloy steel structural component 8 and construct two positioning process joints 3. The process joints are equipped with positioning pin holes. The line connecting the centers of the two positioning pin holes forms the machining reference axis. The roughing, semi-finishing, and finishing of the front and back of the part are all performed around the reference axis as the flipping axis. The remaining multiple clamping process joints 3 are set in the thickness direction of the groove 6 and distributed on both sides of the reference axis formed by the two positioning pin holes as needed.

[0065] Step 2: Use two positioning pin holes located on the axis of symmetry as positioning points for the complex high-strength alloy steel structural component 8. Use round-headed short positioning pins 7 to quickly position the complex high-strength alloy steel structural component 8 onto the adaptive base plate 1. Use the groove 6 of the pressure plate at the process overlap 3 to lock and install the part.

[0066] Step 3: The complex high-strength alloy steel structural component 8 removes all the previous rough material from the process joint according to the reserved process joint 3 shape and separates it from the part body. The purpose of this step is to remove the excess rough material area, which can effectively prevent the internal stress in this area from acting directly on the part body and avoid the extrusion deformation caused by the internal stress in this part.

[0067] Step 4: Loosen the pressure plate used to lock the parts on the process joint 3 of the complex high-strength alloy steel structural parts 8. This releases the internal stress deformation generated during the removal of the raw material. After the stress is released, reclamp the parts and perform rough machining. During rough machining, ensure that a margin of at least 10mm is left to effectively accommodate the thermal deformation after heat treatment. However, at the same time, ensure that the maximum thickness of the entire area of ​​the rough-machined part does not exceed 25mm to fully guarantee the hardenability of the heat treatment.

[0068] Step 5, the main processing sequence is as follows: remove the rough material area according to the projected contour → front (rough) → back (rough) → heat treatment → front (semi-finish) → back (semi-finish) → front (finish) → back (finish); the entire process uses round-headed short locating pins 7 for positioning and installation. The advantage of round-headed short locating pins 7 is their self-adaptability. During clamping, due to the heavy weight of the part, using ordinary cylindrical locating pins requires visual aiming and alignment, which is time-consuming, laborious, and has poor operational safety. However, with round-headed short locating pins 7, after roughly aligning with the locating pin hole, the part is released, and it will slide to align with the hole position on its own. A pressure plate is used for locking and installation, thus completing the installation of the complex high-strength alloy steel structural component 8 at another station. At this time, there is no need to pay attention to the deformation of the part; after flipping, the self-adaptability of the spring steel sheet will compensate for the deformation of the mounting surface.

[0069] Step 6: Due to the complex high-strength alloy steel structural parts 8, after heat treatment, warping or even twisting deformation is inevitable due to their irregular shape, the distribution of the thermal field in the heat treatment furnace, and the installation and suspension method within the furnace. Before each flipping, the upper surface must be precision milled to correct the impact of the part's deformation on the positioning reference surface by removing material.

[0070] Step 7: During the clamping preparation process before semi-finish milling, the cumulative deformation caused by the part's own deformation can prevent the mounting reference surface from fitting properly with the machine tool platform. This can easily lead to vibration during machining, severely affecting the surface quality of the part. In severe cases, resonance may occur, potentially damaging the cutting tool and fixture, or even causing the part to come loose, resulting in a serious safety accident. To avoid these problems, shims of different thicknesses and sizes need to be installed at the contact points between the part and the machine tool surface to ensure a tight fit before machining can proceed. Adjustments need to be made for different workstations and different parts based on the actual deformation amount, which is time-consuming and labor-intensive.

[0071] Step 8: After the complex high-strength alloy steel structural component 8 is locked in the groove 6 by the pressure plate, the Ω-shaped adaptive spring steel sheet 2 is subjected to downward clamping force and produces elastic deformation, which applies the reaction force of the deformation to the part, thereby effectively eliminating processing vibration.

[0072] Step 9: After locking the complex high-strength alloy steel structural component 8 in the groove 6 with a pressure plate, perform semi-finishing of the part, uniformly machining the allowance from more than 10mm before heat treatment to 3-5mm, allowing the internal stress generated by the deformation during heat treatment to be released again. Then, finish mill the upper surface of the part and correct the semi-finishing reference surface after flipping.

[0073] Step 10: Loosen the pressure plate to release the processing stress and thermal stress deformation of the part again, flip it over for processing, and repeat the operation of step 9 to perform semi-finishing on the other side.

[0074] Step 11: Loosen the pressure plate to allow the part to release machining and thermal stress deformation, then flip it over for machining.

[0075] Repeat step 9 to perform finishing on the first side.

[0076] Then, fine machining is performed on both sides. However, it should be noted that before flipping, the reference surface of the upper surface of the current workstation must be finely repaired to correct the impact of deformation on the accuracy of the part.

[0077] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element. Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments of the present invention is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. Additionally, features described with reference to certain examples may be combined in other examples.

[0078] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art, under the guidance of the present invention, can make many other forms without departing from the spirit and scope of protection of the claims, and all such forms are within the protection scope of the present invention.

Claims

1. An adaptive clamping device for aircraft alloy steel structural components, characterized in that, The device includes: a base plate (1), spring steel sheets (2) and multiple process connectors (3); The base plate (1) is a rectangular base, and the upper surface is arranged with mounting slots (10) in an equally spaced matrix array. Spring steel sheets (2) are installed in the mounting slots (10). The upper surface of the base plate is also provided with equally spaced threaded holes (4) and locating pin holes (5); The structural component to be processed is connected to multiple process joints around its periphery. Two of the process joints (3) are installed on the positioning pin holes (5) located on the same straight line to form a processing reference axis. The remaining process joints (3) are distributed on both sides of the reference axis. The process connector (3) has a groove (6) in the thickness direction of the raw material. A pressure plate is inserted into the groove and the pressure plate is locked to the base plate by bolts. Both process connectors that form the machining reference axis have mounting and positioning holes on their upper and lower surfaces. The two ends of the positioning pin are inserted into the positioning pin hole of the base plate and the mounting positioning hole of the process connector to realize the installation of the process connector and the base plate. The locating pin is a short, round-headed locating pin; One end is a cylindrical head, the other end is a spherical head, and there is a ring in the middle; One end of the ball head is inserted into the process connector, and the other end of the cylindrical head is inserted into the positioning pin hole.

2. The adaptive clamping device according to claim 1, characterized in that, The mounting holes in the base plate are equipped with two threaded holes; The spring steel sheet has flat plates at both ends and an arc shape in the middle. One flat plate has a round hole, and the other flat plate has an oblong hole. The spring steel sheet is locked at both ends to the mounting holes in the base plate by screws.

3. A deformation control processing method for aircraft alloy steel structural components, implemented based on the apparatus described in claim 1 or 2, characterized in that, The steps are as follows: Step 1: Install the structural component to be processed onto the positioning pin holes on the base plate that are on the same straight line through two of the process joints; use the line connecting the centers of the two process joints as the processing reference axis; Step 2: Install the pressure plate in the groove of the process joint and lock it to the base plate; Step 3: Remove the raw material except for the process overlap; Step 4: Remove the structural component to be processed from the base plate and then reinstall it; Step 5: Perform rough machining on one side. After the rough machining on one side is completed, disassemble the structural component to be machined, flip it over and reinstall it, and then perform rough machining on the other side. Step Six: Remove the roughly machined structural components from the base plate and perform heat treatment; Step 7: Install the heat-treated structural component on the base plate and perform single-sided semi-finishing. After the single-sided semi-finishing is completed, disassemble the structural component, flip it over and reinstall it to perform the other side semi-finishing. Step 8: Remove the semi-finished structural components from the base plate and reinstall them. Perform single-sided finishing. After single-sided finishing, remove the structural components, flip them over and reinstall them. Perform finishing on the other side. At the end of the machining process, cut off all process overlaps.

4. The method according to claim 3, characterized in that: Leave a margin of more than 10mm during rough machining, but the maximum thickness of the entire area of ​​the part after rough machining should not exceed 25mm.

5. The method according to claim 4, characterized in that: During heat treatment, the structural components are suspended in a natural state.

6. The method according to claim 5, characterized in that: During semi-finishing, the allowance is uniformly reduced from more than 10mm before heat treatment to 3mm~5mm.

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