Deformation control machining method for aircraft alloy steel structural part and self-adaptive clamping device

Abstract

The invention belongs to the technical field of mechanical manufacturing equipment, and particularly relates to a deformation control machining method for an aircraft alloy steel structural part and a self-adaptive clamping device. The device comprises a bottom plate (1), a spring steel sheet (2) and a plurality of process laps (3), the bottom plate (1) is a rectangular base, mounting grooves (10) are distributed in the upper end face of the bottom plate in an equally-spaced matrix array mode, and the spring steel sheets (2) are mounted in the mounting grooves (10). Threaded holes (4) and positioning pin holes (5) are distributed in the upper end face of the bottom plate at equal intervals in an array mode. A plurality of process laps are connected to the periphery of the structural part to be machined, two of the process laps (3) are installed on the positioning pin holes (5) located in the same straight line to form a machining reference axis, and the other process laps (3) are distributed on the two sides of the reference axis; the process lap (3) is provided with a groove (6) in the thickness direction of the blank, a pressing plate is clamped in the groove, and the pressing plate is locked and fixed to the bottom plate through a bolt.

Description

Technical Field

[0001] The invention belongs to the technical field of mechanical manufacturing equipment, and in particular relates to a deformation control processing method and an adaptive clamping device for aircraft alloy steel structural parts. Background Art

[0002] At present, there are many types of aircraft parts known in the art, especially joint parts, and the joint parts are special-shaped parts with complex structures and no regularity.

[0003] The processing technology of the above-mentioned aircraft parts with complex structures, especially complex high-strength alloy steel structural parts, is very complicated; the deformation of the parts themselves and the deformation after heat treatment have a huge impact on the quality and processing cycle. It is the most difficult problem in the processing process. Its processing technology usually adopts a reserved rough material process frame and realizes the part processing through repeated clamping. This processing technology is time-consuming and labor-intensive, with high processing difficulty and low processing efficiency. Summary of the invention

[0004] Purpose of the invention: In order to solve the above problems, the present invention provides a deformation control processing method and an adaptive clamping device for aircraft alloy steel structural parts, so as to solve the existing processing methods for aircraft parts with complex structures, which require repeated clamping to realize part processing, resulting in time-consuming and labor-intensive processing, high processing difficulty, and low processing efficiency. At the same time, the influence of the structural deformation itself and the deformation after heat treatment on the processing process can be effectively eliminated. Summary of the invention:

[0006] An adaptive clamping device for aircraft alloy steel structural parts, comprising: a base plate 1, a spring steel sheet 2 and a plurality of process overlaps 3;

[0007] The bottom plate 1 is a rectangular base, and the upper end surface has mounting holes distributed in an array with equal intervals, and the spring steel sheets 2 are installed in the mounting holes;

[0008] The upper end surface of the bottom plate also has threaded holes 4 and positioning pin holes 5 arranged in an array with equal spacing;

[0009] A plurality of process laps are connected around the structure to be processed, wherein two process laps 3 are installed on the positioning pin holes 5 located in the same straight line to form a processing reference axis, and the remaining process laps 3 are distributed on both sides of the reference axis;

[0010] The process lap joint 3 is provided with a groove 6 in the thickness direction of the rough material, and a pressing plate is inserted into the groove, and the pressing plate is fixed to the bottom plate by bolts.

[0011] Furthermore, the upper and lower surfaces of the two process laps forming the machining reference axis are both provided with mounting positioning holes;

[0012] The two ends of the locating pin are respectively inserted into the locating pin hole of the base plate and the installation locating hole on the process lap joint to realize the installation of the process lap joint and the base plate.

[0013] Further, the positioning pin is a short positioning pin with a round head;

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

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

[0016] Further, two threaded holes are provided in the mounting hole of the bottom plate;

[0017] The spring steel sheet has flat plates at both ends and an arc-shaped middle portion. A circular hole is provided on the flat plate at one end and an oblong hole is provided on the flat plate at the other end.

[0018] Both ends of the spring steel sheet are locked in the mounting holes of the base plate by screws.

[0019] A deformation control processing method for aircraft alloy steel structural parts is implemented based on the device, and the steps are as follows:

[0020] Step 1: Install the structural part to be processed on the locating pin holes on the same straight line of the base plate through two of the process laps; use the center line of the two process laps as the processing reference axis; the rough processing, semi-finishing and finishing of the front and back sides of the part are all flipped around the reference axis as the flip axis;

[0021] Step 2: Install the pressure plate in the groove of the process overlap and lock it on the bottom plate;

[0022] Step 3: Remove the rough material outside the process overlap; after removing the excess rough material area, it can effectively prevent the internal stress in this area from directly acting on the part body, and avoid the extrusion deformation caused by the internal stress in this part;

[0023] Step 4: Remove the structural parts to be processed from the base plate and reinstall them; release the internal stress deformation caused by removing the rough material;

[0024] Step 5: Perform single-sided rough machining. After the single-sided rough machining is completed, disassemble the structural part to be machined, turn it over and reinstall it, and perform rough machining on the other side.

[0025] Step 6: Remove the rough machined structural parts from the base plate for heat treatment;

[0026] Step 7: Install the heat-treated structural parts on the bottom plate for single-side semi-finishing. After the single-side semi-finishing is completed, remove the structural parts, turn them over and reinstall them, and perform semi-finishing on the other side.

[0027] Step 8: Remove the semi-finished structural parts from the base plate and reinstall them for single-side finishing. After the single-side finishing is completed, remove the structural parts and reinstall them for the other side finishing. At the end of the processing, remove all the process overlaps.

[0028] Furthermore, a margin of more than 10 mm is reserved during rough machining to ensure that thermal deformation after heat treatment can be effectively contained. However, the maximum thickness of the entire area of ​​the rough-machined part cannot exceed 25 mm to fully ensure the hardenability of the heat treatment.

[0029] Furthermore, the structural parts are placed in a naturally suspended state during heat treatment. They cannot be placed on a bracket. There are only two stress points during heat treatment of parts in a naturally suspended state, and only one pair of forces is applied to the parts, which minimizes the impact on heat treatment deformation.

[0030] Furthermore, during semi-finishing, the allowance is uniformly processed from more than 10mm before heat treatment to 3mm~5mm. The internal stress generated by the heat treatment deformation of the part is released again. Then the upper surface of the part is fine-milled to correct the semi-finishing reference surface after turning over.

[0031] The beneficial effects of this application are:

[0032] (1) The adaptive clamping device in the embodiment of the present invention has two process overlaps set as required to set positioning holes for part reference positioning. The two holes are located on the same straight line to form a reference axis. The remaining process overlaps can be arranged as required; the remaining process overlaps are provided with grooves in the thickness direction; the grooves are used for the pressure position of the pressure plate, thereby avoiding the upper and lower reference surfaces of the upper and lower parts, and avoiding processing interference when refining the reference during processing. Then all the excess rough material areas are removed. Since the key stress points are pre-destroyed, they are released in advance before rough processing, avoiding the influence of stress deformation on the processing process.

[0033] (2) The adaptive clamping device provided in the embodiment of the present invention is used to simplify the parts clamping method that requires multiple stations (for example, more than 6 stations) in the traditional process to be completed into two-station clamping of forward and reverse stations.

[0034] (3) By using the adaptive clamping device provided in the embodiment of the present invention, it is no longer necessary to manufacture a set of special milling tools for each process complex structural part of the same family of parts, thereby greatly saving tooling costs; moreover, the complex high-strength alloy steel structural parts (8) are mostly family parts, and the production form is typically multi-variety and small batch; the product line is frequently changed 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 for each part will have the disadvantages of high manufacturing cost, long production cycle, and occupied space. The adaptive clamping device provided in the embodiment of the present invention can solve these problems;

[0035] (4) The processing method performed by the adaptive clamping device provided in the embodiment of the present invention changes the reserved rough material process frame in the traditional processing technology, and realizes the process mode of 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 technology, effectively preventing vibration during processing, and improving the surface quality of parts; in addition, for each complex process part of the same family of parts, it is no longer necessary to manufacture a set of special milling tools, which greatly saves tooling costs.

[0036] (5) During the processing of alloy steel structural parts, the superimposed deformation caused by the deformation of the parts themselves causes the installation reference surface to be unable to fit with the machine tool platform surface, which can easily cause vibration during the processing process, seriously affecting the surface quality of the parts. In severe cases, resonance effects will definitely occur, and even damage tools and fixtures, and even cause serious technical safety accidents caused by parts falling out. In order to avoid the above problems, it is necessary to install gaskets of different thicknesses and sizes at the fitting parts of the parts and the machine tool bed surface to ensure that they can fit tightly before processing. Different workstations and different parts of each part need to be adjusted according to the actual deformation amount, which is time-consuming and labor-intensive.

[0037] After the complex high-strength alloy steel structural part (8) is locked in the groove (6) by a pressing plate, the Ω-shaped adaptive spring steel sheet (2) is subjected to a downward clamping force and elastically deforms, and the reaction force of the deformation acts on the part, thereby effectively eliminating processing chatter;

[0038] After the complex high-strength alloy steel structural part (8) is locked in the groove (6) with a pressing plate, the part is semi-finished and the excess is evenly processed from more than 10MM before heat treatment to 3-5MM, so that the internal stress generated by the heat treatment deformation of the part is released again. Then, the upper surface of the part is fine-milled to correct the semi-finished reference surface after turning over.

[0039] Release the pressure plate to release the parts from processing stress and thermal stress deformation again, turn over and repeat the steps to perform semi-finishing on the other side.

[0040] Repeat the process of removing the rough material area on both sides according to the projection contour → front side (rough) → back side (rough) → heat treatment → front side (semi-finished) → back side (semi-finished) → front side (finished) → back side (finished). At present, the flipping process allows the deformation of both sides to be compensated, thereby eliminating some deformation effects by itself. In addition, correcting the deformation of parts by removing materials is far better than correcting the deformation of parts by correction. After the parts are finally processed, there is no stress accumulation as a whole, avoiding subsequent stress assembly. In addition, there is no need to arrange the natural aging process of the intermediate process, which greatly shortens the part manufacturing cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0042] Figure 1 A schematic diagram of the structure of a complex structure aircraft part in an embodiment of the present invention;

[0043] Figure 2 A schematic diagram of the structure of an adaptive clamping device for complex high-strength alloy steel structural parts of aircraft provided by an embodiment of the present invention;

[0044] Figure 3 A schematic structural diagram of a clamping form of a complex high-strength alloy steel structural part of an aircraft by an adaptive clamping device for a complex high-strength alloy steel structural part of an aircraft provided by an embodiment of the present invention;

[0045] Figure 4 A schematic structural diagram of another clamping form of a self-adaptive clamping device for a complex high-strength alloy steel structural part of an aircraft provided by an embodiment of the present invention for clamping a complex high-strength alloy steel structural part of an aircraft after turning it over;

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

[0047] Figure 6 A schematic structural diagram of an adaptive bottom plate in an adaptive clamping device for complex high-strength alloy steel structural parts of aircraft provided by an embodiment of the present invention;

[0048] Description of reference numerals:

[0049] 1. Adaptive bottom plate; 2. Adaptive spring steel sheet; 3. Process overlap; 4. Threaded hole; 5. Locating pin hole; 6. Clamping groove on the ear piece; 7. Round head short locating pin; 8. Complex high-strength alloy steel structural parts; 9. Press plate; 10. Adaptive spring steel sheet installation groove. DETAILED DESCRIPTION

[0050] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the present invention.

[0051] The terms "first", "second", etc. in the specification and claims of the present invention are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second", etc. are generally of the same type, and the number of objects is not limited. For example, the first object can be one or more. In addition, "and / or" in the specification and claims represents at least one of the connected objects, and the character " / " generally indicates that the objects associated with each other are in an "or" relationship.

[0052] The above background technology has explained that the difficulty in processing complex structural special-shaped parts in aircraft parts is to use a reserved rough material process frame and realize the process of part processing through repeated clamping. The deformation of the parts in this processing method is not easy to control, especially the process deformation after heat treatment is difficult to eliminate. The process preparation before processing is time-consuming and labor-intensive, the processing difficulty is high, and the processing efficiency is low.

[0053] In response to the problems existing in the processing methods of complex structure aircraft parts, the embodiments of the present invention provide an adaptive clamping device and a deformation control processing technology for complex high-strength alloy steel structural parts of aircraft, providing a novel concept and easy to use, which can construct a virtual reference axis on the part according to the multi-point structure of the complex structural part through the process lap and the locating pin holes thereon, and a flexible and adjustable adaptive clamping device to cleverly realize the posture adjustment of the part.

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

[0055] Figure 1 A schematic diagram of the structure of a complex structure aircraft part in an embodiment of the present invention; Figure 2 A schematic diagram of the structure of an adaptive clamping device for complex high-strength alloy steel structural parts of aircraft provided by an embodiment of the present invention;

[0056] Figure 3 A schematic structural diagram of a clamping form of a complex high-strength alloy steel structural part of an aircraft by an adaptive clamping device for a complex high-strength alloy steel structural part of an aircraft provided by an embodiment of the present invention; Figure 4 A schematic structural diagram of another clamping form of a self-adaptive clamping device for a complex high-strength alloy steel structural part of an aircraft provided by an embodiment of the present invention for clamping a complex high-strength alloy steel structural part of an aircraft after turning it over;

[0057] like Figure 1As shown, the clamping object of the adaptive clamping device in the embodiment of the present invention is, for example, a complex high-strength alloy steel structural part 8 with a special-shaped structure. The design idea of ​​the adaptive clamping device provided in the embodiment of the present invention is based on the structural characteristics of the complex high-strength alloy steel structural part 8, that is, the characteristics of having multiple process ears, and multiple process laps are set as required. Positioning pin holes 5 and mounting grooves 6 are set on the process laps 3. A virtual processing reference axis is constructed through the hole centers of the positioning pin holes 5 on the two process laps 3, and the posture flipping of the front and back processing of the part is carried out around this axis.

[0058] like Figure 2 and Figure 3 and Figure 4 As shown, the structure of the adaptive clamping device for complex high-strength alloy steel structural parts of aircraft provided by the embodiment of the present invention includes: an adaptive bottom plate 1, an adaptive spring steel sheet 2, and a plurality of process overlaps 3. It should be noted that the number of process overlaps 3 is set according to demand.

[0059] like Figure 2 and Figure 3 and Figure 4 In the adaptive clamping device shown in the figure, the adaptive bottom plate 1 in the embodiment of the present invention is set as a rectangular base with a certain thickness, and can also be a bottom plate of various other symmetrical shapes.

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

[0061] In the embodiment of the present invention, an adaptive clamping device of the above structure is adopted. The virtual symmetry axis of the complex high-strength alloy steel structural part 8 and the process-formed parts respectively installed on each process header 3, the round-headed short locating pin 7 fixed in the locating pin hole 5 on the adaptive base plate 1 can be quickly aligned with the locating pin hole 5 on the process header 3 due to its own adaptability, and at the same time has self-guiding properties, so that the complex high-strength alloy steel structural part 8 can be quickly positioned on the adaptive device, and the adaptive spring steel sheet 2 can quickly adjust the horizontal posture of the complex high-strength alloy steel structural part 8, thereby cleverly realizing the posture adjustment of the part, greatly simplifying the processing technology of such special-shaped complex parts; therefore, the processing technology realized by the adaptive clamping device has the characteristics of rapid positioning, flexible adjustment, efficient clamping, and simplicity.

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

[0063] A deformation controlled processing technology for complex high-strength alloy steel structural parts of aircraft.

[0064] Step 1, select two points of the complex high-strength alloy steel structural part 8, construct two positioning process laps 3, the process laps are provided with positioning pin holes, and the center line of the two positioning pin holes constitutes the processing reference axis. The rough machining, semi-finishing and finishing of the front and back sides of the part are all flipped around the reference axis as the flip axis; the remaining multiple clamping process laps 3 are set in the groove 6 in the thickness direction, and are distributed on both sides of the reference axis formed by the two positioning pin holes as needed.

[0065] Step 2, using two positioning pin holes located on the symmetry axis as positioning points, the complex high-strength alloy steel structural part 8 is quickly positioned on the adaptive bottom plate 1 through the round head short positioning pin 7, and the groove 6 of the pressing plate at the process overlap 3 is used to lock and install the part;

[0066] Step 3, the complex high-strength alloy steel structural part 8 removes all the rough materials of the process overlap according to the reserved process overlap 3 shape, and separates it from the part body. The purpose of this step is to effectively avoid the internal stress of this area from directly acting on the part body after removing the excess rough material area, and avoid the extrusion deformation caused by the internal stress of this part;

[0067] Step 4, loosen the pressure plate used to lock the parts on the process lap 3 of the complex high-strength alloy steel structure 8, release the internal stress deformation caused by removing the rough material, and re-clamp after the stress is released, and perform rough processing. During rough processing, ensure that more than 10MM of margin is reserved to ensure that the thermal deformation after heat treatment can be effectively contained. But at the same time, ensure that the maximum thickness of the whole area of ​​the rough-processed parts cannot exceed 25MM to fully ensure the hardenability of heat treatment.

[0068] Step 5, the main sequence of the processing technology is to remove the rough material area according to the projection contour → front side (rough) → back side (rough) → heat treatment → front side (semi-finished) → back side (semi-finished) → front side (finished) → back side (finished); the whole process uses a round-headed short locating pin 7 for positioning and installation. The advantage of the round-headed short locating pin 7 is that it has adaptability. During the clamping process, due to the heavy weight of the parts, ordinary cylindrical locating pins are used, which require visual aiming and alignment, which is time-consuming and labor-intensive and has poor operational safety. However, the round-headed short locating pin 7 only needs to be roughly aligned with the locating pin hole, and then the part is released, and it will slide and align the hole position by itself. The installation of another station of the complex high-strength alloy steel structural part 8 is completed by using a pressure plate to cooperate with the locking installation. At this time, there is no need to pay attention to the deformation of the parts. After turning over, the adaptability of the spring steel sheet itself will compensate for the deformation of the installation surface.

[0069] Step 6: After the heat treatment of the complex high-strength alloy steel structural part 8, the parts will inevitably bend or even twist due to its own special-shaped structure, the distribution of the thermal field in the heat treatment furnace, and the installation and suspension method in the furnace. The upper surface must be fine-milled once before each flipping, in order to correct the influence of the deformation of the parts on the positioning reference surface by removing material.

[0070] Step 7. During the preparation of the clamping process before semi-finishing milling, the superimposed deformation caused by the deformation of the parts themselves causes the installation reference surface to be unable to fit with the machine platform surface, which can easily cause vibration during the processing process, seriously affecting the surface quality of the parts. In severe cases, resonance effects will definitely occur, and even damage the tools and fixtures, and even cause serious technical safety accidents caused by parts falling out. In order to avoid the above problems, it is necessary to install gaskets of different thicknesses and sizes at the fitting parts of the parts and the machine tool bed surface to ensure that they can fit tightly before processing. Different workstations and different parts of each part need to be adjusted according to the actual deformation amount, which is time-consuming and labor-intensive.

[0071] Step 8, after the complex high-strength alloy steel structure 8 is locked in the groove 6 by the pressing plate, the Ω-shaped adaptive spring steel sheet 2 is subjected to the downward clamping force, and elastic deformation occurs, and the reaction force of the deformation acts on the part, thereby effectively eliminating the processing chatter;

[0072] Step 9, after locking the complex high-strength alloy steel structure 8 in the groove 6 with a pressing plate, semi-finish the part, uniformly process the margin from more than 10mm before heat treatment to 3-5mm, so that the internal stress generated by the heat treatment deformation of the part is released again. Then finish mill the upper surface of the part and correct the semi-finished reference surface after turning over.

[0073] Step 10, release the pressure plate to release the parts from processing stress and thermal stress deformation again, turn over and repeat step 9 to perform semi-finishing on the other side.

[0074] Step 11: Release the pressure plate to release the parts from processing stress and thermal stress deformation, and then turn them over.

[0075] Repeat step 9 to finish the first side.

[0076] Then the front and back sides are finely processed. However, it should be noted that the reference surface of the upper surface of the current station needs to be fine-tuned before the flipping operation to correct the influence of deformation on the accuracy of the part.

[0077] It should be noted that, in this article, the terms "comprise", "include" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device including the element. In addition, it should be pointed out that the scope of the method and device in the embodiment of the present invention is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in reverse order according to the functions involved, for example, the described method may be performed in an order different from that described, and various steps may also be added, omitted, or combined. In addition, the features described with reference to certain examples may be combined in other examples.

[0078] Through the description of the above implementation modes, those skilled in the art can clearly understand that the above implementation modes can be implemented by means of software plus a necessary general hardware platform, and of course by means of hardware, but in many cases the former is a better implementation mode. The above describes the embodiments of the present invention in conjunction with the accompanying drawings, but the present invention is not limited to the above specific implementation modes, which are merely illustrative and not restrictive. Under the enlightenment of the present invention, those skilled in the art can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are within the protection of the present invention.

Claims

1. An adaptive clamping device for aircraft alloy steel structural parts, characterized in that: The device comprises: a base plate (1), a spring steel sheet (2) and a plurality of process joints (3); The bottom plate (1) is a rectangular base, and the upper end surface has mounting grooves (10) distributed in an evenly spaced matrix array, and the spring steel sheets (2) are installed in the mounting grooves (10); The upper end surface of the bottom plate is also provided with threaded holes (4) and positioning pin holes (5) arranged in an array with equal spacing; A plurality of process laps are connected around the structure to be processed, two of which (3) are mounted on positioning pin holes (5) located in the same straight line to form a processing reference axis, and the remaining process laps (3) are distributed on both sides of the reference axis; The process overlap (3) is provided with a groove (6) in the thickness direction of the rough material, a pressing plate is inserted into the groove, and the pressing plate is locked and fixed to the bottom plate by bolts.

2. The adaptive clamping device according to claim 1, characterized in that: The upper and lower surfaces of the two process overlaps forming the machining reference axis are both provided with mounting positioning holes; The two ends of the locating pin are respectively inserted into the locating pin hole of the base plate and the installation locating hole on the process lap joint to realize the installation of the process lap joint and the base plate.

3. The adaptive clamping device according to claim 2, characterized in that: The positioning pin is a short positioning pin with a round head; One end is a cylindrical head, the other end is a ball head, and there is an annular ring in the middle; One end of the ball head is inserted into the process joint, and one end of the cylindrical head is inserted into the positioning pin hole.

4. The adaptive clamping device according to claim 3, characterized in that: Two threaded holes are provided in the mounting hole of the bottom plate; The spring steel sheet has flat plates at both ends and an arc-shaped middle portion. A circular hole is provided on the flat plate at one end and an oblong hole is provided on the flat plate at the other end. Both ends of the spring steel sheet are locked in the mounting holes of the base plate by screws.

5. A deformation control processing method for aircraft alloy steel structural parts, implemented based on any of the above-mentioned devices, characterized in that: Here are the steps: Step 1: Install the structural part to be processed on the locating pin holes on the same straight line of the base plate through two of the process lap joints; use the center line connecting the two process lap joints as the processing reference axis; Step 2: Install the pressure plate in the groove of the process overlap and lock it on the bottom plate; Step 3: Remove the rough material except the process overlap; Step 4: Remove the structural parts to be processed from the base plate and reinstall them; Step 5: Perform single-sided rough machining. After the single-sided rough machining is completed, disassemble the structural part to be machined, turn it over and reinstall it, and perform rough machining on the other side. Step 6: Remove the rough machined structural parts from the base plate for heat treatment; Step 7: Install the heat-treated structural parts on the bottom plate for single-side semi-finishing. After the single-side semi-finishing is completed, remove the structural parts, turn them over and reinstall them, and perform semi-finishing on the other side. Step 8: Remove the semi-finished structural parts from the base plate and reinstall them for single-side finishing. After the single-side finishing is completed, remove the structural parts and reinstall them for the other side finishing. At the end of the processing, remove all the process overlaps.

6. The method according to claim 5, characterized in that: During rough machining, a margin of more than 10 mm should be reserved, but the maximum thickness of the entire area of ​​the part after rough machining cannot exceed 25 mm.

7. The method according to claim 6, characterized in that: During heat treatment, the structural parts are placed in a natural hanging state.

8. The method according to claim 7, characterized in that: During semi-finishing, the allowance is evenly processed from more than 10 mm before heat treatment to 3 mm to 5 mm.

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