Precise forming control method and system for aviation metal part manufacturing

Abstract

The invention provides a precision forming control method and system for aviation metal part manufacturing, and relates to the technical field of data processing, and the method comprises the steps: carrying out the finite element mechanical analysis of an aviation metal part according to the working condition characteristics of an application scene, and obtaining process mechanical characteristic partitions; stamping feature backtracking identification is conducted on the process mechanical feature subareas in the stamping part structure model of the aviation metal part, and stamping process feature subareas are obtained; and carrying out process priority analysis on the stamping process characteristic subareas, outputting a subarea stamping process sequence, then executing process parameter analysis, and outputting a subarea stamping control sequence to carry out batch production of the aviation metal parts. The technical problems that in the prior art, the machining efficiency is low, the machining precision is poor, and the final performance and the production efficiency of the aviation metal part are affected due to the fact that a stamping technology is adopted for machining the aviation metal part are solved. And the technical effect of improving the production quality and efficiency of the aviation metal part on the premise of ensuring high precision and high reliability of the stamping process is achieved.

Description

Technical Field

[0001] The present invention relates to the field of data processing technology, and in particular to a precision molding control method and system for manufacturing aviation metal parts. Background Art

[0002] Aviation metal parts are key components of aircraft, and their processing quality is of vital importance. In the existing technology, stamping technology is often used for the processing of aviation metal parts.

[0003] However, existing stamping processes have significant shortcomings. For one thing, stamping efficiency is low, making it difficult to meet the demands of large-scale production. Furthermore, stamping accuracy is difficult to guarantee, leading to significant deviations in the size and shape of the processed parts, impacting the ultimate performance of aviation metal parts.

[0004] These problems not only reduce production efficiency, but also increase production costs and limit the performance improvement of aviation metal parts. Therefore, a new processing technology is urgently needed to solve the shortcomings of the existing stamping process. Summary of the Invention

[0005] The present application provides a precision forming control method and system for the manufacture of aviation metal parts, which is used to solve the technical problem that the existing technology uses stamping technology to process aviation metal parts, which has low processing efficiency and poor processing accuracy, thereby affecting the final performance and production efficiency of aviation metal parts.

[0006] In view of the above problems, the present application provides a precision molding control method and system for the manufacture of aviation metal parts.

[0007] The first aspect of the present application provides a precision forming control method for the manufacture of aviation metal parts, the method comprising: collecting application scenario working conditions of the aviation metal parts to obtain application scenario working condition characteristics; performing finite element mechanical analysis on the aviation metal parts according to the application scenario working condition characteristics to obtain process mechanical characteristic partitions; performing stamping feature backtracking identification on the process mechanical characteristic partitions in the stamping component structure model of the aviation metal parts by running the process rule library to obtain stamping process characteristic partitions; performing process priority analysis on the stamping process characteristic partitions based on the partition stamping priority rules to output a partition stamping process sequence; performing process parameter analysis on the stamping process characteristic partitions with the partition stamping process sequence as a constraint to output a partition stamping control sequence; after scheduling the stamping sheet, using the partition stamping control sequence to carry out batch production of the aviation metal parts.

[0008] The second aspect of the present application provides a precision forming control system for the manufacture of aviation metal parts, the system comprising: a working condition feature acquisition unit for collecting working conditions of application scenarios of aviation metal parts to obtain working condition features of application scenarios; a mechanical analysis execution unit for performing finite element mechanical analysis on the aviation metal parts according to the working condition features of the application scenarios to obtain process mechanical feature partitions; a stamping feature backtracking unit for performing stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aviation metal parts by running a process rule library to obtain stamping process feature partitions; a process execution analysis unit for performing process priority analysis on the stamping process feature partitions based on partition stamping priority rules to output partition stamping process sequences; a process parameter analysis unit for performing process parameter analysis on the stamping process feature partitions with the partition stamping process sequence as a constraint to output a partition stamping control sequence; and a stamping control execution unit for using the partition stamping control sequence to carry out batch production of the aviation metal parts after scheduling the stamping sheet.

[0009] One or more technical solutions provided in this application have at least the following technical effects or advantages: The method provided in the embodiment of the present application obtains application scenario working condition characteristics by collecting application scenario working condition data for aviation metal parts; performs finite element mechanical analysis on the aviation metal parts based on the application scenario working condition characteristics to obtain process mechanical characteristic partitions; performs stamping feature backtracking identification on the process mechanical characteristic partitions in the stamping component structure model of the aviation metal parts by running a process rule library to obtain stamping process characteristic partitions; performs process priority analysis on the stamping process characteristic partitions based on the partition stamping priority rules to output a partition stamping process sequence; performs process parameter analysis on the stamping process characteristic partitions using the partition stamping process sequence as a constraint to output a partition stamping control sequence; and after scheduling the stamping plates, uses the partition stamping control sequence to carry out batch production of the aviation metal parts. The method achieves the technical effect of improving the production quality and efficiency of aviation metal parts while ensuring the high precision and high reliability of the stamping process. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 A flow chart of the precision forming control method for aviation metal parts manufacturing provided in this application; Figure 2 This is a schematic diagram of the structure of the precision forming control system for aviation metal parts manufacturing provided in this application.

[0011] Explanation of the accompanying symbols: working condition feature acquisition unit 11, mechanical analysis execution unit 12, stamping feature backtracking unit 13, process execution analysis unit 14, process parameter analysis unit 15, stamping control execution unit 16. DETAILED DESCRIPTION

[0012] This application provides a precision forming control method and system for the manufacture of aviation metal parts. This method addresses the low efficiency and poor precision of conventional stamping processes for aviation metal parts, which in turn impacts the final performance and production efficiency of these parts. This method achieves the technical effect of improving the production quality and efficiency of aviation metal parts while ensuring the high precision and reliability of the stamping process.

[0013] Below, the technical solutions of the present invention will be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments of the present invention. It should be understood that the present invention is not limited to the example embodiments described herein. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. It should also be noted that, for the convenience of description, only the parts related to the present invention, rather than all, are shown in the accompanying drawings.

[0014] Example 1, as Figure 1 As shown, the present application provides a precision molding control method for manufacturing aviation metal parts, the method comprising: A100: Collect application scenario working conditions of aviation metal parts to obtain application scenario working condition characteristics.

[0015] In one embodiment, application scenario working conditions of aviation metal parts are collected to obtain application scenario working condition characteristics. Step A100 of the method provided by the present invention includes: A110: Application scenario data is collected based on the unique identifier of the aviation metal part to obtain multiple historical application scenario records, wherein the historical application scenario records include load condition records, environmental condition records, and usage condition records.

[0016] A120: Obtain application scenario working condition information by extracting extreme scenario features from the multiple historical application scenario records.

[0017] A130: Calling a transmission component according to the component assembly characteristics of the aviation metal part to obtain multiple component codes of multiple related transmission components.

[0018] A140: Using the multiple component codes to perform network data call to obtain multiple related component information.

[0019] A150: The application scenario operating condition information and multiple related component information constitute the application scenario operating condition characteristics.

[0020] Specifically, it should be understood that the unique identifier is a code used to uniquely identify an aviation metal part, which can be a part number, serial number, etc. Through the unique identifier, the application scenario record related to the aviation metal part can be called from a database or data storage system. Based on this, this embodiment collects application scenario data based on the unique identifier of the aviation metal part to obtain multiple historical application scenario records. The data structure of each historical application scenario record includes but is not limited to: load condition records (recording the load conditions borne by the aviation metal part in different application scenarios, such as transmission torque, centrifugal force, vibration excitation, etc.), environmental condition records (recording the environmental conditions of the aviation metal part in different application scenarios, such as temperature, humidity, pressure, etc.), and usage condition records (recording the usage conditions of the aviation metal part in different application scenarios, such as speed, operating frequency, working time, etc.).

[0021] It should be understood that extreme scenario feature extraction refers to extracting the most representative and extreme working condition features from the multiple historical application scenario records. These features can reflect the maximum loads, the most severe environmental conditions and the most complex usage conditions that aviation metal parts may encounter in actual applications.

[0022] This embodiment obtains application scenario operating condition information by extracting extreme scenario features from the multiple historical application scenario records. The application scenario operating condition information includes static scenario operating condition information reflecting the load and environmental conditions of aviation metal parts under static conditions, and dynamic scenario operating condition information reflecting the load and environmental conditions of aviation metal parts under dynamic conditions. This embodiment describes the specific application of the application scenario operating condition information in the subsequent description.

[0023] It should be understood that component assembly features refer to the assembly relationship between an aviation metal component and other transmission components, including the connection method, assembly position, and assembly sequence. This embodiment uses these component assembly features to retrieve multiple associated transmission components connected to the aviation metal component and obtain the component codes of these transmission components. It should be understood that a component code is a code used to uniquely identify a transmission component and can be a part number, serial number, or the like.

[0024] Using these component codes, information related to multiple transmission components can be retrieved from a database or data storage module. This information includes, but is not limited to, the geometric dimensions, shape, and key features of the transmission components; the material grade and mechanical properties (such as elastic modulus, yield strength, and strain hardening exponent) of the transmission components; and the connection method and assembly relationship between the transmission components and aviation metal parts. This information provides foundational data for the subsequent construction of the assembly structure model.

[0025] The application scenario working condition information and multiple related transmission component information are integrated to form the application scenario working condition characteristics.

[0026] It should be noted that the working condition collection method of this embodiment is to collect historical data through a unique identifier and extract extreme scenario characteristics to form working condition information. The method is flexible and can adapt to the information collection of the structure and performance requirements of different aviation metal parts, providing basic data for subsequent process optimization.

[0027] This embodiment collects the working condition characteristics of the application scenario to provide basic data for subsequent finite element mechanics analysis and stamping process optimization, indirectly achieving the technical effect of ensuring the high-precision fit and reliability of the processed aviation metal parts in a complex working environment.

[0028] A200: Perform finite element mechanical analysis on the aviation metal parts according to the working condition characteristics of the application scenario to obtain process mechanical characteristic partitioning.

[0029] In one embodiment, finite element mechanical analysis is performed on the aviation metal part according to the working condition characteristics of the application scenario to obtain process mechanical characteristic partitions. Step A200 of the method provided by the present invention includes: A210: Perform local data call based on the unique identifier of the aviation metal part to obtain aviation stamping part information.

[0030] A220: Assemble and integrate the aviation stamping component information and multiple related component information according to the component assembly features to obtain an assembly structure model.

[0031] A230: After applying multivariate loads to the assembly structure model based on the application scenario working condition information, a mechanical response diagram is extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint.

[0032] A240: traverse the mechanical response diagram using a process mechanical threshold value, and filter and output the process mechanical characteristic partitions.

[0033] In one embodiment, after applying multivariate loads to the assembly structure model based on the application scenario working condition information, a mechanical response diagram is extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint. Step A230 of the method provided by the present invention includes: A231: Extracting static scene operating condition information and dynamic scene operating condition information from the application scene operating condition information.

[0034] A232: After applying a static load to the assembly structure model according to the static scene working condition information, the static stress cloud map and the static deformation vector map are extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint.

[0035] A233: After applying dynamic load to the assembly structure model according to the dynamic scene working condition information, the transient stress cloud map and transient deformation vector map are extracted from the assembly structure model using the stamping component structure model as the stamping influence range constraint.

[0036] A234: Use the transient stress nephogram to compensate the static stress nephogram to obtain a corrected stress nephogram.

[0037] A235: Use the transient deformation vector diagram to compensate the static deformation vector diagram to obtain a corrected deformation vector diagram, wherein the corrected deformation vector diagram and the corrected stress cloud diagram constitute the mechanical response diagram.

[0038] In one embodiment, the mechanical response diagram is traversed using a process mechanical threshold value to filter and output the process mechanical characteristic partitions. Step A240 of the method provided by the present invention includes: A241: Preset grid scale.

[0039] A242: Segment the modified stress cloud map using the gridding scale to obtain a plurality of modified stress blocks.

[0040] A243: Using the yield stress threshold in the process mechanics threshold to traverse the multiple modified stress blocks, screening to obtain a high stress area distribution, wherein the high stress area distribution includes W modified stress blocks.

[0041] A244: Divide the corrected deformation vector map using the gridding scale to obtain a plurality of corrected deformation vector blocks.

[0042] A245: Use the significant deformation threshold in the process mechanics threshold to traverse the multiple corrected deformation vector blocks, and screen out the high deformation area distribution, wherein the high deformation area distribution includes M corrected deformation vector blocks, and the high stress area distribution and the high deformation area distribution constitute the process mechanics characteristic partition.

[0043] In one embodiment, after applying a dynamic load to the assembly structure model according to the dynamic scene working condition information, a transient stress cloud map and a transient deformation vector map are extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint. Step A233 of the method provided by the present invention includes: A2331: Evenly divide the dynamic scene working condition information to obtain K stages of scene working condition information.

[0044] A2332: After applying dynamic loads step by step to the assembly structure model using the K stage scenario working condition information, the stamping component structure model is used as the stamping influence range constraint, and K stage stress cloud maps and K stage deformation vector maps are extracted from the assembly structure model.

[0045] A2333: The transient stress cloud map is obtained by comparing the K stage stress cloud maps and performing regional stress extreme value integration.

[0046] A2334: Perform regional deformation extreme value integration by comparing the K stage deformation vector diagrams to obtain the transient deformation vector diagram.

[0047] In one embodiment, the aviation stamping component information and multiple related component information are assembled and integrated according to the component assembly characteristics to obtain an assembly structure model. Step A220 of the method provided by the present invention includes: A221: Use the aviation stamping component information to perform geometric simplification modeling to obtain the stamping component structure model.

[0048] A222: Extracting a plurality of associated component structural features and a plurality of associated component material features from the plurality of associated component information.

[0049] A223: Using the multiple associated component structural features and the multiple associated component material features as retrieval conditions to perform network modeling scheduling to obtain multiple transmission component structural models.

[0050] A224: performing assembly fitting of the stamping component structure model and multiple transmission component structure models according to the component assembly features to obtain the assembly structure model.

[0051] Specifically, in this embodiment, local data is first called based on the unique identifier of the aviation metal part to obtain the aviation stamping part information that characterizes the detailed information of the aviation stamping part. The aviation stamping part information includes but is not limited to geometric parameters, material properties, and design drawings, etc., providing basic data for subsequent finite element mechanics analysis.

[0052] Using information from aerospace stamping parts, geometric simplification modeling is performed to extract key features and remove non-critical features, resulting in a structural model of the stamping part. Specifically, key features such as transmission tooth profiles, seal grooves, and thin-walled areas can be extracted from the 3D model of the aerospace stamping part, while non-critical features such as chamfers and small holes can be removed. This geometric simplification reduces model complexity and improves the efficiency and accuracy of subsequent finite element analysis.

[0053] It should be understood that features such as transmission tooth profiles and sealing grooves contribute more than 95% to the mechanical response, while minor features such as chamfers / small holes have an impact of less than 1% on the global stress distribution. After deletion, the model error is controllable. At the same time, simplifying the model can reduce the number of meshes by 30%-50%, shortening the solution time without affecting the accuracy of high stress areas (such as thin-walled areas) (error <5%).

[0054] It should be understood that the purpose of retaining chamfers in physical manufacturing is to avoid injuries caused by sharp angles, and the purpose of adding small holes is to reduce weight or route wiring. Based on this, this embodiment obtains a variety of structural features for non-mechanical purposes as a variety of sample non-critical features through interactive aviation metal component manufacturers. Similarly, based on whether the component structural features affect the mechanical properties of the components, the same method is used to obtain a variety of sample mechanical-related structural features as modeling key features for reference in modeling simplification.

[0055] The essence of geometric simplification modeling is to simplify complex geometric models while retaining the original mechanical properties of the component. Specifically, the modeling focuses on removing non-critical features that have little impact on mechanical properties, such as chamfers and small holes, while retaining key features that significantly impact the mechanical properties and stress conditions of the component, such as transmission tooth profiles, sealing grooves, and thin-walled areas. Geometric simplification modeling effectively reduces model complexity and ensures that the model truly reflects the actual mechanical state of the component after the subsequent introduction of operating conditions and performance information.

[0056] All necessary information related to the aviation metal parts is extracted and obtained from the plurality of associated component information, specifically including a plurality of associated component structural features and a plurality of associated component material features of the plurality of associated transmission components.

[0057] Through network data calling, multiple sample transmission component finite element models that match the multiple related component structural features and multiple related component material features mentioned above are obtained from the database or data storage system as multiple transmission component structural models of the multiple related transmission components, providing necessary data support for subsequent assembly fitting.

[0058] Specifically, in this embodiment, the load is divided into static scene working condition information and dynamic scene working condition information according to the application scene working condition information, and the static load and dynamic load are applied to the assembly structure model respectively.

[0059] Among them, illustratively, the extraction of static scene working condition information includes extracting the first load condition (extracting the load conditions of aviation metal parts under static conditions, such as transmission torque, centrifugal force, etc.), extracting the first environmental condition (extracting the environmental conditions of aviation metal parts under static conditions, such as temperature, humidity, pressure, etc.), and extracting the first usage condition (extracting the usage conditions of aviation metal parts under static conditions, such as speed, working frequency, working time, etc.). The data structure obtained by extracting static scene working condition information is similar to this and will not be repeated here.

[0060] Furthermore, the dynamic scenario condition information is divided into K stages. Each stage of the scenario condition information represents a specific phase of the dynamic load, such as the gradual increase of parameters such as amplitude and frequency. This staged approach can more accurately simulate the dynamic changes in actual working conditions.

[0061] Based on the extracted static scenario working condition information, a static load is applied to the assembly structure model. After the static load is applied, a static stress contour map and a static deformation vector map are extracted from the assembly structure model, using the stamping influence range constraint of the stamping component structure model. The static stress contour map displays the stress distribution of the assembly structure model under static load, while the static deformation vector map displays the deformation of the assembly structure model under static load. These maps provide basic data under static conditions for subsequent process mechanical feature partitioning.

[0062] Dynamic loads are applied to the assembly structure model step by step using the K stage scenario working condition information. In each stage, after applying the corresponding dynamic load, the stamping component structure model is used as the stamping influence range constraint to extract the stage stress cloud map and stage deformation vector map from the assembly structure model. Ultimately, K stage stress cloud maps and K stage deformation vector maps are extracted.

[0063] The stress values of the same region at different stages in the K-stage stress nephograms are compared, and the maximum value is taken as the transient stress value of the region. This method ensures that the transient stress nephogram reflects the maximum stress distribution of the assembly structure model under dynamic load. This method is used to integrate the regional stress extreme values of the K-stage stress nephograms to obtain the transient stress nephogram.

[0064] Similarly, the deformation values of each region at different stages are compared, and the maximum value is taken as the transient deformation value of the region. By comparing the K stage deformation vector diagrams and integrating the regional deformation extreme values, the transient deformation vector diagram is obtained.

[0065] The stress values in the transient stress cloud map are superimposed or maximized with the stress values in the static stress cloud map to obtain the modified stress cloud map that more accurately reflects the stress distribution. The modified stress cloud map integrates the stress information of aviation metal parts under static and dynamic conditions.

[0066] Similarly, the deformation value in the transient deformation vector diagram is superimposed on the deformation value in the static deformation vector diagram or the maximum value is taken to obtain the modified deformation vector diagram which more accurately reflects the deformation situation. The modified deformation vector diagram integrates the deformation information of aviation metal parts under static and dynamic conditions, and is consistent with the modified stress cloud diagram. Figure 1 Together they constitute the mechanical response diagram, providing comprehensive basic data for subsequent process mechanical characteristic zoning.

[0067] Furthermore, this embodiment presets a gridding scale to facilitate segmentation of the mechanical response map. The gridding scale can be set based on actual needs, for example, to 0.1 mm or less to ensure sufficient accuracy of the segmented blocks. The preset gridding scale provides a basis for subsequent block segmentation and threshold traversal.

[0068] The gridding scale is used to divide the modified stress cloud map into a plurality of small grid areas, each grid area being a modified stress block to obtain a plurality of modified stress blocks in total.

[0069] Set the yield stress threshold as a percentage of the material's yield strength , and then traverse each modified stress block, marking the block with a stress value exceeding the threshold as a high stress area, and the high stress area distribution includes W modified stress blocks.

[0070] The same method is adopted to segment the modified deformation vector map based on the gridding scale to obtain a plurality of modified deformation vector blocks.

[0071] The significant deformation threshold is set to the deformation exceeding a certain range (for example, based on the ductility of the aluminum alloy skin and the stamping process requirements, the significant deformation threshold is set to 15%, and its effectiveness in suppressing cracks is verified by the Airbus A320 skin fatigue test). Then, the significant deformation threshold is used to traverse each modified deformation vector block, and the blocks with deformation exceeding the significant deformation threshold are marked as high deformation areas. The high deformation area distribution includes M modified deformation vector blocks. It should be understood that in this embodiment, W and M are unspecified positive integers.

[0072] This embodiment, through finite element mechanical analysis of aviation metal parts, accurately assesses their mechanical properties under different operating conditions and identifies key areas, including high stress and high deformation zones, providing fundamental information for subsequent stamping control analysis for precision forming. A300: By running a process rule library, stamping feature backtracking is performed on the process mechanical feature partitions within the stamping component structural model of the aviation metal part to obtain stamping process feature partitions.

[0073] In one embodiment, by running a process rule library, stamping feature backtracking identification is performed on the process mechanical feature partitions in the stamping component structure model of the aviation metal part to obtain stamping process feature partitions. Step A300 of the method provided by the present invention includes: A310: Interactively obtain multiple sample stamping shape features for multiple sample stamping process types.

[0074] A320: Map and store the multiple sample stamping process types of the multiple sample stamping shape features to complete the construction of the process rule library.

[0075] A330: Using the W modified stress blocks in the high stress area distribution as local shape acquisition guides, backtracking the local stamping structure of the stamping component structure model to obtain W high stress associated stamping shapes.

[0076] A340: Traverse the W high-stress associated stamping shapes through the process rule library to perform stamping shape feature comparison to obtain W high-stress stamping process types.

[0077] A350: Similarly, M high deformation stamping process types of the M modified deformation vector blocks are obtained.

[0078] A360: Using the W high-stress stamping process types to identify the W modified stress blocks, and using the M high-deformation stamping process types to identify the M modified deformation vector blocks, to obtain the stamping process feature partitions.

[0079] Specifically, in this embodiment, stamping process types corresponding to different stamping shape features are collected, for example, hole-punching process, slot-punching process, boss-punching boss process, pit-punching pit process, bending-bending process, and stretching-stretching process, as the various sample stamping process types for the various sample stamping shape features.

[0080] The construction of the process rule library is completed by mapping and storing the multiple sample stamping process types of the multiple sample stamping shape features. It should be understood that the process rule library stores various stamping shape features and their corresponding stamping process types, providing data support for subsequent stamping feature backtracking identification.

[0081] Based on the W corrected stress blocks in the high-stress area distribution, local shape acquisition is performed on the stamped component structure model. For example, if a corrected stress block is located around a hole, then that hole is a high-stress associated stamped shape. In this way, using the W corrected stress blocks as local shape acquisition guides, the local stamped structure of the stamped component structure model is traced back to obtain W high-stress associated stamped shapes.

[0082] Compare the W high-stress associated stamping shapes with the sample stamping shape features in the process rule library. For example, if a high-stress associated stamping shape is a hole, then through comparison, it can be determined that its corresponding stamping process type is a punching process. In this way, the W high-stress associated stamping shapes are traversed through the process rule library for stamping shape feature comparison, and W high-stress stamping process types are obtained.

[0083] Using a similar approach to the high-stress area distribution, the M modified deformation vector blocks are processed. For example, if a modified deformation vector block is located in a bend area, then that bend area is a high-deformation associated stamping shape. By comparing it with the process rule library, it can be determined that the corresponding stamping process type is a bending process. In this way, M high-deformation stamping process types are obtained.

[0084] The W high-stress stamping process types are used to identify the W modified stress blocks, and the M high-deformation stamping process types are used to identify the M modified deformation vector blocks, to obtain the stamping process feature partitions.

[0085] This embodiment runs the process rule library to perform stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aviation metal part, thereby obtaining stamping process feature partitions, thereby providing important basic data for subsequent stamping process optimization and ensuring the high precision and high reliability technical effects of the stamping process.

[0086] A400: Based on the partition stamping priority rule, process priority analysis is performed on the stamping process feature partitions, and a partition stamping process sequence is output.

[0087] Specifically, it should be understood that the partition stamping priority rules refer to the execution priorities of various stamping processes. According to these rules, the execution order of different stamping processes can be determined.

[0088] In this embodiment, the stamping order of each block is determined based on the W corrected stress blocks in the high-stress area distribution and the type of high-stress stamping process. The hierarchy refers to placing the same stamping processes in the same sorting level. For example, all punching processes are placed in the first level, all notching processes are placed in the second level, and so on. Multiple corrected stress blocks within the same level have no order because they use the same stamping process. In this way, the first stamping process hierarchy sequence is generated.

[0089] According to the M corrected deformation vector blocks in the high deformation area distribution, combined with the high deformation stamping process type, the stamping order of each block is determined. The hierarchy refers to placing the same stamping process in one sorting level, for example, all bending processes are placed in the first level, all stretching processes are placed in the second level, and so on. There is no order of precedence for multiple corrected deformation vector blocks in the same level because they use the same stamping process. Ultimately, the first stamping process level sequence and the second stamping process level sequence together constitute the partitioned stamping process sequence.

[0090] A500: Taking the partitioned stamping process sequence as a constraint, perform process parameter analysis on the stamping process feature partitions and output a partitioned stamping control sequence.

[0091] In one embodiment, the method step A500 provided by the present invention includes: A510: Based on the partitioned stamping priority rule and the W high-stress stamping process types, perform process priority analysis on the W modified stress blocks and output a first stamping process level sequence.

[0092] A520: Similarly, a process priority analysis is performed on the M corrected deformation vector blocks according to the M high deformation stamping process types, and a second stamping process level sequence is output, wherein the first stamping process level sequence and the second stamping process level sequence constitute the partitioned stamping process sequence.

[0093] A530: Using the W modified stress blocks as local parameter collection guides, backtracking the local structural parameters of the stamping component structural model to obtain W high stress associated structural parameters.

[0094] A540: Using the W high-stress stamping process types as constraints, process parameter matching is performed on the W high-stress associated structural parameters to obtain W first partition stamping control parameters.

[0095] A550: Combining the W first partition stamping control parameters according to the first stamping process level sequence to obtain a first stamping control sequence.

[0096] A560: And so on, we get the second stamping control sequence.

[0097] A570: Concatenate the first stamping control sequence and the second stamping control sequence, and output the partitioned stamping control sequence.

[0098] This embodiment has already described in detail the method for obtaining the partitioned stamping process sequence in step A400, so it will not be repeated here.

[0099] Furthermore, in this embodiment, based on the W corrected stress blocks in the high stress area distribution, the local structural parameters of the stamping component structure model are traced back, and the structural parameters related to high stress, such as geometric dimensions, material properties, etc., are extracted to obtain the W high stress associated structural parameters.

[0100] Furthermore, according to the high stress stamping process type, process parameter matching is performed on the high stress associated structural parameters to determine the key parameters in the stamping process, such as stamping force, die gap, stamping speed, etc., to obtain the W first partition stamping control parameters.

[0101] According to the first stamping process level sequence, W first partition stamping control parameters are combined in order, and two or more first partition stamping control parameters at the same level are sorted according to the stamping intensity, with the parameters with greater stamping intensity being ranked in front. In this way, the rationality and efficiency of the stamping process can be ensured, and the first stamping control sequence is finally generated.

[0102] A method similar to that of the first stamping control sequence is adopted, and according to the second stamping process level sequence, the M second partition stamping control parameters are combined in sequence to generate the second stamping control sequence.

[0103] The end of the first punching control sequence and the starting end of the second punching control sequence are connected in sequence to complete the splicing of the partitioned punching control sequences.

[0104] This embodiment uses the partitioned stamping process sequence as a constraint and combines it with process parameter analysis to generate an accurate partitioned stamping control sequence, thereby achieving the technical effect of ensuring high precision and high reliability of the stamping process and improving the production quality and efficiency of aviation metal parts.

[0105] Furthermore, this implementation is universal and applicable to the precision forming of any aviation metal parts. Specifically, this implementation collects data through unique identifiers, extracts extreme scenario characteristics, forms general working condition information, and provides comprehensive support for analysis and optimization; utilizes finite element mechanics analysis, combines component assembly characteristics and multi-factor load application, generates mechanical response diagrams, and screens out key areas through process mechanics thresholds to form process mechanics feature partitions; based on the process rule library, combines process mechanics feature partitions with stamping component structural models, retrospectively identifies stamping process feature partitions, and generates partitioned stamping process sequences through process priority analysis; then performs process parameter analysis and outputs partitioned stamping control sequences.

[0106] Steps A100-A500 of this embodiment cover the complete process from data collection to production. Each link adopts universal and scalable methods and technologies. Whether it is simple or complex aviation metal parts, through appropriate adjustment and optimization, this solution can be applied to achieve precision molding control, effectively improving production efficiency and processing accuracy.

[0107] A600: After scheduling the stamping sheets, the partitioned stamping control sequence is used to carry out batch production of the aviation metal parts.

[0108] Specifically, in this embodiment, parameters of the stamping equipment are set and process control is performed according to the partitioned stamping control sequence. After the scheduling of the stamping sheets is completed, the partitioned stamping control sequence is used to operate the stamping equipment to carry out batch production of the aviation metal parts.

[0109] For example, the comparative table showing the improvement in precision of parts produced after the processing of this embodiment is as follows:

[0110] This embodiment realizes precise control of the stamping forming of aviation metal parts, achieving the technical effect of improving the production quality and efficiency of aviation metal parts while ensuring high precision and high reliability of the stamping process.

[0111] The second embodiment is based on the same inventive concept as the precision forming control method for manufacturing aviation metal parts in the above embodiment. Figure 2 As shown, the present application provides a precision molding control system for manufacturing aviation metal parts, wherein the system includes: The working condition feature collection unit 11 is used to collect working conditions of application scenarios of aviation metal parts to obtain working condition features of application scenarios.

[0112] The mechanical analysis execution unit 12 is used to perform finite element mechanical analysis on the aviation metal part according to the working condition characteristics of the application scenario to obtain process mechanical characteristic partitions.

[0113] The stamping feature backtracking unit 13 is used to perform stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aviation metal part by running the process rule library to obtain stamping process feature partitions.

[0114] The process execution analysis unit 14 is configured to perform process priority analysis on the stamping process feature partitions based on the partition stamping priority rule, and output a partition stamping process sequence.

[0115] The process parameter analysis unit 15 is used to perform process parameter analysis on the stamping process feature partitions based on the partitioned stamping process sequence as a constraint, and output a partitioned stamping control sequence.

[0116] The stamping control execution unit 16 is used to perform batch production of the aviation metal parts using the partitioned stamping control sequence after scheduling the stamping plates.

[0117] In one embodiment, the operating condition characteristic acquisition unit 11 is further configured to: Application scenario data is collected based on the unique identifier of the aviation metal part to obtain multiple historical application scenario records, wherein the historical application scenario records include load condition records, environmental condition records, and usage condition records; application scenario working condition information is obtained by extracting extreme scenario features from the multiple historical application scenario records; transmission component calls are performed based on the component assembly features of the aviation metal part to obtain multiple component codes of multiple related transmission components; network data calls are performed using the multiple component codes to obtain multiple related component information; the application scenario working condition information and the multiple related component information constitute the application scenario working condition features.

[0118] In one embodiment, the mechanical analysis execution unit 12 is further configured to: Local data is called according to the unique identifier of the aviation metal part to obtain aviation stamping component information; the aviation stamping component information and multiple related component information are assembled and integrated according to the component assembly characteristics to obtain an assembly structure model; after applying multivariate loads to the assembly structure model based on the application scenario working condition information, a mechanical response diagram is extracted from the assembly structure model with the stamping component structure model as the stamping influence range constraint; the mechanical response diagram is traversed using a process mechanics threshold to filter and output the process mechanics feature partition.

[0119] In one embodiment, the mechanical analysis execution unit 12 is further configured to: Static scenario working condition information and dynamic scenario working condition information are extracted from the application scenario working condition information; after applying a static load to the assembly structure model according to the static scenario working condition information, a static stress cloud map and a static deformation vector map are extracted from the assembly structure model with the stamping component structure model as the stamping influence range constraint; after applying a dynamic load to the assembly structure model according to the dynamic scenario working condition information, a transient stress cloud map and a transient deformation vector map are extracted from the assembly structure model with the stamping component structure model as the stamping influence range constraint; the transient stress cloud map is used to compensate the static stress cloud map to obtain a corrected stress cloud map; the transient deformation vector map is used to compensate the static deformation vector map to obtain a corrected deformation vector map, wherein the corrected deformation vector map and the corrected stress cloud map constitute the mechanical response map.

[0120] In one embodiment, the mechanical analysis execution unit 12 is further configured to: A gridding scale is preset; the gridding scale is used to segment the corrected stress cloud map to obtain a plurality of corrected stress blocks; the yield stress threshold in the process mechanics threshold is used to traverse the plurality of corrected stress blocks, and a high stress area distribution is obtained by screening, wherein the high stress area distribution includes W corrected stress blocks; the gridding scale is used to segment the corrected deformation vector map to obtain a plurality of corrected deformation vector blocks; the significant deformation threshold in the process mechanics threshold is used to traverse the plurality of corrected deformation vector blocks, and a high deformation area distribution is obtained by screening, wherein the high deformation area distribution includes M corrected deformation vector blocks, and the high stress area distribution and the high deformation area distribution constitute the process mechanics characteristic partition.

[0121] In one embodiment, the stamping feature backtracking unit 13 is further configured to: Interactively obtain a variety of sample stamping process types with a variety of sample stamping shape features; map and store the multiple sample stamping process types with the multiple sample stamping shape features to complete the construction of the process rule library; use the W corrected stress blocks in the high stress area distribution as local shape acquisition guidelines, and trace back the local stamping structure of the stamping component structure model to obtain W high stress associated stamping shapes; traverse the W high stress associated stamping shapes through the process rule library to perform stamping shape feature comparison to obtain W high stress stamping process types; and so on, obtain M high deformation stamping process types of the M corrected deformation vector blocks; use the W high stress stamping process types to identify the W corrected stress blocks, and use the M high deformation stamping process types to identify the M corrected deformation vector blocks to obtain the stamping process feature partitions.

[0122] In one embodiment, the process parameter analysis unit 15 is further configured to: Based on the partitioned stamping priority rule and W high-stress stamping process types, a process priority analysis is performed on the W corrected stress blocks to output a first stamping process level sequence; similarly, a process priority analysis is performed on the M corrected deformation vector blocks according to the M high-deformation stamping process types to output a second stamping process level sequence, wherein the first stamping process level sequence and the second stamping process level sequence constitute the partitioned stamping process sequence; the W corrected stress blocks are used as local parameter collection guidelines, and the local structural parameters of the stamping component structure model are traced back to obtain W high-stress associated structural parameters; with the W high-stress stamping process types as constraints, process parameter matching is performed on the W high-stress associated structural parameters to obtain W first partitioned stamping control parameters; the W first partitioned stamping control parameters are combined according to the first stamping process level sequence to obtain a first stamping control sequence; similarly, a second stamping control sequence is obtained; the first stamping control sequence and the second stamping control sequence are spliced to output the partitioned stamping control sequence.

[0123] In one embodiment, the mechanical analysis execution unit 12 is further configured to: The dynamic scenario working condition information is evenly divided to obtain K stage scenario working condition information; after applying dynamic loads to the assembly structure model step by step using the K stage scenario working condition information, the stamping component structure model is used as the stamping influence range constraint, and K stage stress cloud maps and K stage deformation vector maps are extracted from the assembly structure model; regional stress extreme value integration is performed by comparing the K stage stress cloud maps to obtain the transient stress cloud map; regional deformation extreme value integration is performed by comparing the K stage deformation vector maps to obtain the transient deformation vector map.

[0124] In one embodiment, the mechanical analysis execution unit 12 is further configured to: The aviation stamping component information is used to perform geometric simplification modeling to obtain the stamping component structural model; multiple related component structural features and multiple related component material features are extracted from the multiple related component information; the multiple related component structural features and multiple related component material features are used as retrieval conditions to perform network modeling scheduling to obtain multiple transmission component structural models; the stamping component structural model and multiple transmission component structural models are assembled and fitted according to the component assembly features to obtain the assembly structural model.

[0125] Any of the methods or steps described above may be stored as computer instructions or programs in various types of computer memories, and the computer instructions or programs may be recognized by various types of computer processors to implement any of the methods or steps described above.

[0126] Based on the above specific embodiments of the present invention, any improvements and modifications made to the present invention by those skilled in the art without departing from the principles of the present invention shall fall within the scope of patent protection of the present invention.

Claims

1. A precision forming control method for aviation metal parts manufacturing, characterized in that: The method comprises: Collect application scenario working conditions of aviation metal parts to obtain application scenario working condition characteristics; Performing finite element mechanics analysis on the aviation metal part according to the working condition characteristics of the application scenario to obtain process mechanics characteristic partitions; By running the process rule library, performing stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aviation metal part, thereby obtaining stamping process feature partitions; Based on the partition stamping priority rule, the process priority analysis is performed on the stamping process feature partitions, and the partition stamping process sequence is output; Taking the partitioned stamping process sequence as a constraint, performing process parameter analysis on the stamping process feature partitions, and outputting a partitioned stamping control sequence; After scheduling the stamping sheets, the partitioned stamping control sequence is used to carry out batch production of the aviation metal parts.

2. The precision forming control method for aviation metal parts manufacturing according to claim 1, characterized in that: The method for collecting application scenario working conditions of aviation metal parts to obtain application scenario working condition characteristics includes: Collecting application scenario data based on the unique identifier of the aviation metal part to obtain a plurality of historical application scenario records, wherein the historical application scenario records include load condition records, environmental condition records, and usage condition records; Extracting extreme scenario features from the plurality of historical application scenario records to obtain application scenario working condition information; Calling a transmission component according to the component assembly characteristics of the aviation metal part to obtain multiple component codes of multiple related transmission components; Using the multiple component codes to perform network data call to obtain multiple related component information; The application scenario operating condition information and multiple related component information constitute the application scenario operating condition characteristics.

3. The precision forming control method for aviation metal parts manufacturing according to claim 2, characterized in that: Finite element mechanics analysis is performed on the aviation metal part according to the working condition characteristics of the application scenario to obtain process mechanics characteristic partitions, the method comprising: Performing local data call based on the unique identifier of the aviation metal part to obtain aviation stamping part information; Assembling and integrating the aviation stamping component information and multiple related component information according to the component assembly features to obtain an assembly structure model; After applying multivariate loads to the assembly structure model based on the application scenario working condition information, a mechanical response diagram is extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint; The mechanical response diagram is traversed using a process mechanical threshold value to filter and output the process mechanical characteristic partitions.

4. The precision forming control method for aviation metal parts manufacturing according to claim 3, characterized in that: After applying multivariate loads to the assembly structure model based on the application scenario working condition information, extracting a mechanical response diagram from the assembly structure model using the stamping component structure model as a stamping influence range constraint, the method includes: Extracting static scene working condition information and dynamic scene working condition information from the application scene working condition information; After applying a static load to the assembly structure model according to the static scene working condition information, a static stress cloud map and a static deformation vector map are extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint; After applying dynamic loads to the assembly structure model according to dynamic scene working condition information, a transient stress cloud map and a transient deformation vector map are extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint; Using the transient stress nephogram to compensate the static stress nephogram to obtain a modified stress nephogram; The transient deformation vector diagram is used to compensate the static deformation vector diagram to obtain a modified deformation vector diagram, wherein the modified deformation vector diagram and the modified stress cloud diagram constitute the mechanical response diagram.

5. The precision forming control method for manufacturing aviation metal parts according to claim 4, characterized in that: The mechanical response diagram is traversed using a process mechanical threshold value to screen and output the process mechanical characteristic partitions, the method comprising: Preset grid scale; Segmenting the modified stress cloud map using the gridding scale to obtain a plurality of modified stress blocks; Using the yield stress threshold in the process mechanics threshold to traverse the plurality of modified stress blocks, screening to obtain a high stress area distribution, wherein the high stress area distribution includes W modified stress blocks; Segmenting the modified deformation vector map using the gridding scale to obtain a plurality of modified deformation vector blocks; The significant deformation threshold in the process mechanics threshold is used to traverse the multiple corrected deformation vector blocks to screen out the high deformation area distribution, wherein the high deformation area distribution includes M corrected deformation vector blocks, and the high stress area distribution and the high deformation area distribution constitute the process mechanics characteristic partition.

6. The precision forming control method for manufacturing aviation metal parts according to claim 5, characterized in that: By running a process rule library, performing stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aviation metal part to obtain stamping process feature partitions, the method includes: Interactively obtain multiple sample stamping shape features of multiple sample stamping process types; Mapping and storing a plurality of sample stamping process types of the plurality of sample stamping shape features to complete the construction of the process rule library; Using the W modified stress blocks in the high stress area distribution as local shape acquisition guides, tracing back the local stamping structure of the stamping component structure model to obtain W high stress associated stamping shapes; Traversing the W high-stress associated stamping shapes through the process rule library to perform stamping shape feature comparison to obtain W high-stress stamping process types; By analogy, M high deformation stamping process types of the M modified deformation vector blocks are obtained; The W high-stress stamping process types are used to identify the W modified stress blocks, and the M high-deformation stamping process types are used to identify the M modified deformation vector blocks, to obtain the stamping process feature partitions.

7. The precision forming control method for manufacturing aviation metal parts according to claim 6, characterized in that: The method comprises: Based on the partitioned stamping priority rule and the W high-stress stamping process types, performing process priority analysis on the W modified stress blocks, and outputting a first stamping process level sequence; Similarly, a process priority analysis is performed on the M modified deformation vector blocks according to the M high deformation stamping process types, and a second stamping process level sequence is output, wherein the first stamping process level sequence and the second stamping process level sequence constitute the partitioned stamping process sequence; Using the W modified stress blocks as local parameter collection guides, backtracking the local structural parameters of the stamping component structure model to obtain W high stress associated structural parameters; Taking the W high-stress stamping process types as constraints, process parameter matching is performed on the W high-stress associated structural parameters to obtain W first partition stamping control parameters; Combining the W first partition stamping control parameters according to the first stamping process level sequence to obtain a first stamping control sequence; And so on, the second punching control sequence is obtained; The first punching control sequence and the second punching control sequence are spliced together to output the partitioned punching control sequence.

8. The precision forming control method for manufacturing aviation metal parts according to claim 4, characterized in that: After applying dynamic loads to the assembly structure model according to dynamic scene working condition information, a transient stress cloud map and a transient deformation vector map are extracted from the assembly structure model using the stamping component structure model as a stamping influence range constraint. The method includes: Evenly divide the dynamic scene working condition information to obtain K stages of scene working condition information; After applying dynamic loads step by step to the assembly structure model using the K stage scenario working condition information, using the stamping component structure model as a stamping influence range constraint, extracting K stage stress cloud maps and K stage deformation vector maps from the assembly structure model; By comparing the K stage stress cloud maps and performing regional stress extreme value integration, the transient stress cloud map is obtained; The transient deformation vector diagram is obtained by comparing the K stage deformation vector diagrams and performing regional deformation extreme value integration.

9. The precision forming control method for manufacturing aviation metal parts according to claim 3, characterized in that: According to the component assembly features, the aviation stamping component information and multiple related component information are assembled and integrated to obtain an assembly structure model, the method comprising: Using the aviation stamping component information to perform geometric simplified modeling to obtain a structural model of the stamping component; extracting a plurality of associated component structural features and a plurality of associated component material features from the plurality of associated component information; Using the multiple associated component structural features and the multiple associated component material features as retrieval conditions to perform network modeling scheduling to obtain multiple transmission component structural models; The stamping component structure model and a plurality of transmission component structure models are assembled and fitted according to the component assembly features to obtain the assembly structure model.

10. Precision molding control system for aviation metal parts manufacturing, characterized by: The steps for implementing the method according to any one of claims 1 to 9 include: A working condition feature acquisition unit is used to collect working conditions of application scenarios of aviation metal parts and obtain working condition features of application scenarios; A mechanical analysis execution unit, configured to perform finite element mechanical analysis on the aviation metal part according to the working condition characteristics of the application scenario to obtain a process mechanical characteristic partition; A stamping feature backtracking unit is configured to perform stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aviation metal part by running a process rule library to obtain stamping process feature partitions; A process execution analysis unit, configured to perform process priority analysis on the stamping process feature partitions based on the partition stamping priority rule, and output a partition stamping process sequence; a process parameter analysis unit, configured to perform process parameter analysis on the stamping process feature partitions based on the partitioned stamping process sequence as a constraint, and output a partitioned stamping control sequence; The stamping control execution unit is used to use the partitioned stamping control sequence to carry out batch production of the aviation metal parts after scheduling the stamping plates.

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