Deformation control machining method for aircraft structural component with complex full-curved-surface configuration

Abstract

The invention belongs to the technical field of mechanical manufacturing equipment, and discloses a deformation control machining method for a full-curved-surface complex aircraft structural component, a virtual machining axis is constructed on a complex wing surface, then positioning bosses are symmetrically arranged on the two sides of the virtual machining axis, and in the process of correcting material deformation, the positioning bosses are symmetrically arranged on the two sides of the virtual machining axis. Boss end face references on different sides are symmetrically corrected, and it is guaranteed that the bosses form a mirror symmetry structure along the virtual machining axis all the time. The method has the advantages that the stress of the material is released step by step in order, and the defect that new stress accumulation is generated after correction by a traditional bench worker is overcome. And meanwhile, the full-curved-surface configuration artificially forms a mirror symmetry structure along the virtual machining axis, and positioning configuration deviation caused by positioning reference conversion does not need to be considered during repeated clamping.

Description

Technical Field

[0001] This invention belongs to the field of mechanical manufacturing equipment technology, and specifically relates to a deformation control processing method for complex aircraft structural components with full curved surface configuration. Background Technology

[0002] Currently, there are many types of aircraft parts known in this field, especially complex aircraft structural parts with full curved surface configurations, whose structures are complex and irregular.

[0003] For complex aircraft structural components with fully curved surface configurations, the deformation of the parts themselves and the severe vibration in weakly rigid areas have a significant impact on quality and processing cycle, making them the most challenging problems in the processing.

[0004] Traditional machining is a combination of CNC machining and conventional milling, and the part material is forging, where the internal stress is much greater than that of a pre-stretched plate. First, the two wing surfaces of the complex, fully curved aircraft structural component are machined to the required position. However, the subsequent machining of the wing surface grooves involves scribing, clamping the plate, and then machining the grooves with allowance on a conventional milling machine. Finally, a fitter finishes and grinds the grooves. This process is inefficient and results in inconsistent product quality. Summary of the Invention To address the aforementioned problems, this invention provides a deformation control machining method for complex aircraft structural components with a fully curved surface configuration. First, a virtual machining axis is constructed, which is a spatially symmetrical axis. Subsequent roughing, semi-finishing, and finishing processes are all performed symmetrically around this virtual machining axis. Specifically, small-sized process bosses are symmetrically arranged on both sides of the fully curved surface configuration along the virtual machining axis. Locating pin holes are located at the centers of these process bosses, and these holes are used for positioning and connection with the clamping device. This effectively solves problems such as time-consuming and labor-intensive processing, high processing difficulty, and low processing efficiency, while also eliminating structural deformation and its impact on the processing process.

[0005] A deformation control machining method for complex aircraft structural components with fully curved surface configurations, comprising the following steps: Step 1: In the raw material state, stress relief grooves 11 are opened in the main stress areas of the complex aircraft structural parts with full curved surface configuration. The main stress areas are the areas with the largest material allowance, the weak areas of the parts that are easy to deform and lack reinforcement structures. Step 2: According to the minimum process allowance requirements, the raw material is initially squared to expose the thickness direction of the part, and the initial datum for rough machining of the part is established. A virtual machining axis is constructed. The virtual machining axis is a spatially symmetrical axis. Subsequent rough machining, semi-finishing, and finishing processes are all carried out symmetrically around the virtual machining axis. Step 3: Roughly machine one side of the structural component's profile in the thickness direction and integrally form a boss; Step 4: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 180° to rough machine the other side of the surface and integrally form the process boss; Step 5: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 90°, and the structural component is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is then rough-machined. Step 6: The structural component is rotated 180° using the virtual machining axis along its length as the rotation axis. The structural component is then positioned and clamped using a clamping device, and rough machining is performed on one side of the wing surface cavity. Step 7: After completing the above steps, leave the container to stand still for 24 hours to allow it to naturally age. Step 8: Check the deformation of the structural component, re-square the structural component according to the actual deformation, remove the allowance evenly on both sides in the thickness direction, ensure that the position of the virtual machining axis in the length direction remains unchanged, and correct the structural component datum by removing material. Step 9: Repeat the processing operation of Step 3 to perform semi-finishing of the surface at this workstation, leaving a 3mm allowance during semi-finishing. Step 10: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 180° to perform semi-finishing on the other side of the surface; Step 11: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 90°, and the part is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is then semi-finished. Step 12: The structural component is rotated 180° using the virtual machining axis along its length as the rotation axis. The part is then positioned and clamped using a clamping device, and the groove on the other side of the wing surface is semi-finished. Step 13: After completing the above steps, leave the container to stand still for 24 hours to allow it to naturally thaw. Step Fourteen: Check the deformation of the part, square the raw material again according to the actual deformation, remove the excess material evenly on both sides, ensure that the position of the virtual machining axis in the length direction remains unchanged, and correct the structural part datum by removing material. Step 15: Repeat steps 9 to 12 to perform finishing on the parts; Step 16: Use milling to remove the process bosses on the structural parts.

[0006] Furthermore, in steps three and four, a margin of more than 10mm should be reserved during rough machining.

[0007] Furthermore, in steps five and six, a margin of 5 to 10 mm is reserved on the wing surface during rough machining.

[0008] Furthermore, in step nine, during semi-finishing, because there is a margin in the shape of the groove cavity, the edge plate has a certain strength and rigidity, and the surface quality and processing efficiency are not affected.

[0009] Furthermore, in steps nine and ten, a 3mm allowance is reserved during semi-finishing; Furthermore, in steps eleven and twelve, Leave a 3mm allowance on the wing surface during semi-finishing.

[0010] Furthermore, in step sixteen, when removing the process boss, a step difference of 0.3-0.5mm is allowed, and then the fitter grinds the cut surface smooth.

[0011] The beneficial effects of this application are as follows: The virtual axis machining process for complex aircraft structural components with fully curved surface configurations involves constructing a virtual machining axis on the complex wing surface, and then symmetrically setting locating bosses on both sides of the virtual machining axis. Each boss has a locating hole at its center for mounting a locating pin. Auxiliary clamping bosses are also provided. Bosses on different sides of the complex curved surface have their end planes located in the same reference plane, forming a mirror-symmetric structure with the bosses on the other side along the virtual machining axis.

[0012] During the process of correcting material deformation, the end faces of the bosses on different sides must be symmetrically corrected to ensure that the bosses always form a mirror-symmetric structure along the virtual machining axis. This approach allows for the orderly and gradual release of material stress, overcoming the problem of new stress accumulation after traditional fitter correction. Furthermore, artificially creating a mirror-symmetric structure along the virtual machining axis for the entire curved surface eliminates the need to consider positioning deviations caused by changes in positioning datums during repeated clamping.

[0013] In the aforementioned processing technology, the entire part machining process can be completed on a 3-axis machine, reducing reliance on 5-axis machines and fully unleashing the production capacity of high-precision equipment. By changing the overlap mode of the process joints, the superposition of vibrations during machining with excessively long overhanging tools and machining of weakly rigid edge plates is avoided, effectively improving the surface quality of the parts and machining efficiency.

[0014] The virtual axis machining process for complex aircraft structural components with fully curved surface configurations involves constructing a virtual machining axis on the complex wing surface, and then symmetrically setting locating bosses on both sides of the virtual machining axis. Each boss has a locating hole at its center for mounting a locating pin. Auxiliary clamping bosses are also provided. Bosses on different sides of the complex curved surface have their end planes located in the same reference plane, forming a mirror-symmetric structure with the bosses on the other side along the virtual machining axis.

[0015] During the process of correcting material deformation, the end faces of the bosses on different sides must be symmetrically corrected to ensure that the bosses always form a mirror-symmetric structure along the virtual machining axis. This approach allows for the orderly and gradual release of material stress, overcoming the problem of new stress accumulation after traditional fitter correction. Furthermore, artificially creating a mirror-symmetric structure along the virtual machining axis for the entire curved surface eliminates the need to consider positioning deviations caused by changes in positioning datums during repeated clamping.

[0016] The process connector is characterized by being a small-sized cylindrical shape, but not limited to a cylindrical shape, with a connector diameter of 8-10mm. The process connectors are arranged in a low-density and uniform manner. Due to their small size and low density, the process bosses will not affect the shape accuracy of the entire curved surface configuration, and can be used for effective and reliable positioning and clamping in the clamping device.

[0017] The full-surface configuration is designed to make the clamping datum symmetrical along the virtual machining axis. This way, when the part is clamped, no matter how the part's machining posture and position are adjusted, the distance between the fixed mounting surface of the clamping device and the virtual machining axis remains consistent, that is, the position of the virtual machining axis remains unchanged.

[0018] The process overlap joint of the fully curved surface configuration is characterized by the fact that when the deformation of the part is corrected by removing material, the allowance must be removed evenly on both sides of the symmetrical side. The advantage of this is that it avoids the use of forced correction, thus preventing the creation of new internal stresses in the part, while ensuring that the position of the virtual machining axis remains unchanged.

[0019] The deformation of straightness and deflection across the entire range is reduced, while material utilization is significantly improved, thereby reducing costs and greatly improving the processing quality and production efficiency of parts.

[0020] For complex aircraft structural components with fully curved surfaces, the deformation of the parts themselves and the severe vibration in weakly rigid areas have a significant impact on quality and machining cycle, making it one of the most challenging problems in the machining process. The machining process usually involves scribing, milling, and bench work, which is time-consuming, labor-intensive, difficult, and inefficient. Attached Figure Description

[0021] 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.

[0022] Figure 1 This is a structural schematic diagram of a complex aircraft structural component with a fully curved surface configuration provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of a complex aircraft structural component with a fully curved surface configuration and its raw material in an embodiment of the present invention; Figure 3 A schematic diagram of a complex aircraft structural component with a fully curved surface configuration containing process bosses, provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of a complex aircraft structural component with a fully curved surface configuration under clamping conditions, as provided in an embodiment of the present invention. Figure 5 A schematic diagram illustrating a detailed explanation of clamping a complex aircraft structural component with a fully curved surface configuration, as provided in an embodiment of the present invention. Explanation of reference numerals in the attached figures: 1. Complex aircraft structural components with full curved surface configuration; 2. Raw material; 3. Process boss; 4. Virtual machining axis; 5. Part edge plate; 6. Left wing surface profile of the full curved surface structural component; 7. Right wing surface profile of the full curved surface structural component; 8. Part cavity; 9. Locating pin hole; 10. Clamping device jaws; 11. Stress relief groove; 12. Raw material pressure plate groove. Detailed Implementation

[0023] 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.

[0024] 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.

[0025] As explained in the background section, the virtual axis machining process for complex aircraft structural components with full curved surface configurations involves constructing a virtual machining axis on the complex wing surface, and then symmetrically setting locating bosses on both sides of the virtual machining axis. Each boss has a locating hole at its center for mounting a locating pin. Auxiliary clamping bosses are also provided. Bosses on different sides of the complex curved surface have their end planes located in the same reference plane, forming a mirror-symmetric structure with the boss on the other side along the virtual machining axis.

[0026] During the process of correcting material deformation, the end faces of the bosses on different sides must be symmetrically corrected to ensure that the bosses always form a mirror-symmetric structure along the virtual machining axis. This approach allows for the orderly and gradual release of material stress, overcoming the problem of new stress accumulation after traditional fitter correction. Simultaneously, artificially creating a mirror-symmetric structure along the virtual machining axis for the entire curved surface eliminates the need to consider positioning deviations caused by datum conversions during repeated clamping. However, this method is time-consuming and labor-intensive in pre-process preparation, has high processing difficulty, and low processing efficiency.

[0027] To address the problems existing in the processing methods of complex aircraft structural components with full curved surface configurations, this invention provides a deformation control processing technology for complex aircraft structural components with full curved surface configurations, offering a novel approach and a convenient programming and processing technology.

[0028] 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.

[0029] In this embodiment of the invention, a deformation control processing technology for a complex aircraft structural component with a fully curved surface configuration is described, referring to... Figure 1-5 The steps are as follows: Step 1: In the raw material state, stress relief grooves 11 are opened in the main stress area of ​​the complex aircraft structural parts with full curved surface configuration. The main stress area is the area with the largest material allowance, and the weak area where the parts are easy to deform and lack reinforcement structure. Step 2: According to the minimum process allowance requirements, the raw material is initially squared to expose the thickness direction of the part to light, establishing the initial datum for rough machining of the part, and constructing a virtual machining axis. This virtual machining axis is a spatially symmetrical axis. Subsequent rough machining, semi-finishing, and finishing processes are all carried out symmetrically around the virtual machining axis. This station has no strict requirements on the perpendicularity and parallelism of the raw material after exposure to light. Step 3: Roughly machine one side of the profile in the thickness direction and integrally form the boss. Leave a margin of more than 10mm during rough machining. Step 4: The structural component is rotated 180° using the virtual machining axis along the length direction as the rotation axis. The other side of the surface is rough machined, and the integral forming boss is formed. A margin of more than 10mm is reserved during rough machining. Step 5: The virtual machining axis along the length of the complex aircraft structural component with full curved surface configuration is the rotation axis. The component is flipped 90°, and the part is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is rough machined. During rough machining, a 5-10mm allowance is reserved on the wing surface. Step 6: For complex aircraft structural parts with full curved surface configurations, the virtual machining axis along the length direction is used as the rotation axis to perform a 180° flip. The part is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is rough-machined, leaving a 5-10mm allowance on the wing surface during rough machining. Step 7: Steps 2 to 6 are to fully release the internal stress of the parts. After the above steps are completed, the parts are left to stand still for 24 hours to allow for natural aging.

[0030] Step 8: Inspect the deformation of the structural component. Based on the actual deformation, square the raw material again, removing excess material evenly on both sides in the thickness direction. The purpose is to ensure that the position of the virtual machining axis in the length direction remains unchanged. Correct the part's datum by removing material. Do not forcibly correct it with a press, as this will create unknown internal stress in the part, and new deformation will occur after processing.

[0031] Step Nine: Repeat the processing operation of Step Three, this time performing semi-finishing of the surface at this station. Since there is allowance left in the shape of the groove cavity, and the edge plate has a certain strength and rigidity, the surface quality and processing efficiency are not affected.

[0032] Step 10: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 180° to perform semi-finishing on the other side of the surface, leaving a 3mm allowance during semi-finishing. Step 11: The virtual machining axis along the length of the complex aircraft structural component with full curved surface configuration is the rotation axis. The component is flipped 90° and the part is positioned and clamped using a clamping device. The wing surface cavity on one side is semi-finished. During the semi-finishing process, a 3mm allowance is reserved on the wing surface. Step 12: For complex aircraft structural parts with full curved surface configurations, the virtual machining axis along the length direction is used as the rotation axis to perform a 180° flip. The part is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is semi-finished. During the semi-finishing process, a 3mm allowance is reserved on the wing surface. Step Thirteen: Steps Nine through Twelve are for further releasing the internal stress of the parts. After the above steps are completed, the parts are left to stand still for 24 hours for natural aging. Due to the forming method, the internal stress of free forgings is much greater than that of pre-stretched plates. They must be processed repeatedly to allow the internal stress to be released naturally and evenly, in order to ensure the product quality during subsequent finishing.

[0033] Step Fourteen: Inspect the deformation of the part. Based on the actual deformation, square the raw material again, removing excess material evenly on both sides. The purpose is to ensure that the position of the virtual machining axis in the length direction remains unchanged. Correct the part's datum by removing material. Do not forcibly correct it with a press, as this will create unknown internal stress in the part, and new deformation will occur after processing.

[0034] Step 15: Repeat steps 9 to 12 to perform finishing on the part. The clamping force can be effectively transferred to the structural body. The flange has good strength and rigidity, and the surface quality and processing efficiency are not affected.

[0035] Step 16: Use milling to remove the process bosses on the full curved surface, allowing a step difference of 0.3-0.5. Then, the fitter grinds the cut edges smooth.

[0036] The process bosses are small-sized cylindrical shapes, but are not limited to cylindrical shapes; the overlap diameter can be 8-10mm. The process overlaps are arranged in a low-density and uniform manner. Due to their small size and low density, the process bosses will not affect the shape accuracy of the entire curved surface configuration, and can be used for effective and reliable positioning and clamping in the clamping device.

[0037] The virtual axis machining process for complex aircraft structural components with fully curved surface configurations involves constructing a virtual machining axis on the complex wing surface, and then symmetrically setting locating bosses on both sides of the virtual machining axis. Each boss has a locating hole at its center for mounting a locating pin. Auxiliary clamping bosses are also provided. Bosses on different sides of the complex curved surface have their end planes located in the same reference plane, forming a mirror-symmetric structure with the bosses on the other side along the virtual machining axis.

[0038] During the process of correcting material deformation, the end faces of the bosses on different sides must be symmetrically corrected to ensure that the bosses always form a mirror-symmetric structure along the virtual machining axis. This approach allows for the orderly and gradual release of material stress, overcoming the problem of new stress accumulation after traditional fitter correction. Furthermore, artificially creating a mirror-symmetric structure along the virtual machining axis for the entire curved surface eliminates the need to consider positioning deviations caused by changes in positioning datums during repeated clamping.

[0039] When correcting part deformation by removing material, the allowance must be removed evenly on both symmetrical sides. The advantage of this is that it avoids forcibly correcting the part, preventing the creation of new internal stresses, while ensuring that the virtual machining axis position remains unchanged.

[0040] The process of machining easily deformable materials through a multi-station process of roughing, semi-finishing, and finishing allows the internal stress of the easily deformable materials to be released evenly and naturally. Furthermore, the special virtual shaft machining process, coupled with a clamping device, makes the basic process flow cumbersome, but the use of efficient and precise positioning and fast clamping methods greatly improves the clamping and machining efficiency.

[0041] Parts processing can be completed entirely on 3-axis equipment, reducing reliance on 5-axis equipment and fully unleashing the production capacity of high-precision equipment.

[0042] The machining process provided in this application involves constructing virtual machining axes at appropriate locations and symmetrically distributing these virtual machining axes among the process bosses. The two-station machining process for both front and back surfaces is transformed into a multi-station machining process using the virtual machining axes as rotation axes. By using small-sized process overlaps, material is saved, and the influence of internal material stress on part deformation is avoided. Simultaneously, the part can undergo all machining operations on a three-coordinate machine tool, reducing reliance on five-coordinate high-precision equipment on-site, lowering costs, and significantly increasing feed rate and cutting efficiency.

[0043] 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.

[0044] 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. A method for controlling the deformation of complex aircraft structural components with fully curved surface configurations, characterized in that, The steps are as follows: Step 1: In the raw material state, stress relief grooves 11 are opened in the main stress areas of the complex aircraft structural parts with full curved surface configuration. The main stress areas are the areas with the largest material allowance, the weak areas of the parts that are easy to deform and lack reinforcement structures. Step 2: According to the minimum process allowance requirements, the raw material is initially squared to expose the thickness direction of the part, and the initial datum for rough machining of the part is established. A virtual machining axis is constructed. The virtual machining axis is a spatially symmetrical axis. Subsequent rough machining, semi-finishing, and finishing processes are all carried out symmetrically around the virtual machining axis. Step 3: Roughly machine one side of the structural component's profile in the thickness direction and integrally form a boss; Step 4: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 180° to rough machine the other side of the surface and integrally form the process boss; Step 5: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 90°, and the structural component is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is then rough-machined. Step 6: The structural component is rotated 180° using the virtual machining axis along its length as the rotation axis. The structural component is then positioned and clamped using a clamping device, and rough machining is performed on one side of the wing surface cavity. Step 7: After completing the above steps, leave the container to stand still for 24 hours to allow it to naturally age. Step 8: Check the deformation of the structural component, re-square the structural component according to the actual deformation, remove the allowance evenly on both sides in the thickness direction, ensure that the position of the virtual machining axis in the length direction remains unchanged, and correct the structural component datum by removing material. Step 9: Repeat the processing operation of Step 3 to perform semi-finishing of the surface at this workstation, leaving a 3mm allowance during semi-finishing. Step 10: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 180° to perform semi-finishing on the other side of the surface; Step 11: Using the virtual machining axis along the length as the rotation axis, the structural component is flipped 90°, and the part is positioned and clamped using a clamping device. The groove cavity on one side of the wing surface is then semi-finished. Step 12: The structural component is rotated 180° using the virtual machining axis along its length as the rotation axis. The part is then positioned and clamped using a clamping device, and the groove on the other side of the wing surface is semi-finished. Step 13: After completing the above steps, leave the container to stand still for 24 hours to allow it to naturally thaw. Step Fourteen: Check the deformation of the part, square the raw material again according to the actual deformation, remove the excess material evenly on both sides, ensure that the position of the virtual machining axis in the length direction remains unchanged, and correct the structural part datum by removing material. Step 15: Repeat steps 9 to 12 to perform finishing on the parts; Step 16: Use milling to remove the process bosses on the structural parts.

2. The deformation control processing method for complex aircraft structural components with full curved surface configuration according to claim 1, characterized in that, In steps three and four, allowance of more than 10mm should be reserved during rough machining.

3. The deformation control processing method for complex aircraft structural components with full curved surface configuration according to claim 1, characterized in that, In steps five and six, a margin of 5-10mm should be left on the wing surface during rough machining.

4. The deformation control processing method for complex aircraft structural components with full curved surface configuration according to claim 1, characterized in that, In step nine, during semi-finishing, because there is a margin in the shape of the groove cavity, the edge plate has a certain strength and rigidity, and the surface quality and processing efficiency are not affected.

5. The deformation control processing method for complex aircraft structural components with full curved surface configuration according to claim 1, characterized in that, In steps nine and ten, a 3mm allowance is reserved during semi-finishing.

6. The deformation control machining method for a complex aircraft structural component with a fully curved surface configuration according to claim 1, characterized in that, In steps eleven and twelve, Leave a 3mm allowance on the wing surface during semi-finishing.

7. The deformation control machining method for complex aircraft structural components with full curved surface configuration according to claim 1, characterized in that, In step sixteen, when removing the process boss, a step difference of 0.3-0.5mm is allowed, and then the fitter grinds the cut smooth.

8. A complex aircraft structural component with a fully curved surface configuration, characterized in that, The aircraft structural components are manufactured using the method described in any one of claims 1-7.

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