Precision forming control methods and systems for aerospace metal parts manufacturing

Abstract

This invention provides a precision forming control method and system for manufacturing aerospace metal parts, relating to the field of data processing technology. It involves performing finite element mechanical analysis on aerospace metal parts based on the characteristics of the application scenario's working conditions to obtain process mechanical feature partitions. Then, it performs stamping feature backtracking identification on the stamping component structural model of the aerospace metal parts to obtain stamping process feature partitions. Finally, it performs process priority analysis on the stamping process feature partitions, outputs a partitioned stamping process sequence, executes process parameter analysis, and outputs a partitioned stamping control sequence for the mass production of aerospace metal parts. This invention solves the technical problems of low processing efficiency and poor processing accuracy in existing stamping processes for aerospace metal parts, which consequently affect the final performance and production efficiency of the aerospace metal parts. It achieves the technical effect of improving the production quality and efficiency of aerospace metal parts while ensuring high precision and high reliability of the stamping process.

Description

Technical Field

[0001] This invention relates to the field of data processing technology, and more specifically to a precision forming control method and system for manufacturing aerospace metal parts. Background Technology

[0002] Aerospace metal parts are key components of aircraft, and their processing quality is of paramount importance. In existing technologies, stamping processes are commonly used for processing aerospace metal parts.

[0003] However, existing stamping processes have significant shortcomings. On the one hand, stamping efficiency is low, making it difficult to meet the demands of large-scale production. On the other hand, stamping accuracy is difficult to guarantee, resulting in significant deviations in the size and shape of the manufactured parts, which affects the final performance of aerospace metal components.

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

[0005] This application provides a precision forming control method and system for manufacturing aerospace metal parts, which addresses the technical problems of low processing efficiency and poor processing accuracy in the existing stamping process for aerospace metal parts, thus affecting the final performance and production efficiency of aerospace metal parts.

[0006] In view of the above problems, this application provides a precision forming control method and system for the manufacturing of aerospace metal parts.

[0007] The first aspect of this application provides a precision forming control method for manufacturing aerospace metal parts. The method includes: collecting application scenario operating conditions data for the aerospace metal parts to obtain application scenario operating condition characteristics; performing finite element mechanical analysis on the aerospace metal parts based on the application scenario operating condition characteristics to obtain process mechanical feature partitions; performing stamping feature backtracking identification on the process mechanical feature partitions in the stamping component structure model of the aerospace metal parts by running a process rule library to obtain stamping process feature partitions; performing process priority analysis on the stamping process feature partitions based on partitioned stamping priority rules to output partitioned stamping process sequences; performing process parameter analysis on the stamping process feature partitions using the partitioned stamping process sequences as constraints to output partitioned stamping control sequences; and using the partitioned stamping control sequences for mass production of the aerospace metal parts after scheduling the stamping sheet metal.

[0008] A second aspect of this application provides a precision forming control system for manufacturing aerospace metal parts. The system includes: a working condition feature acquisition unit for acquiring working conditions of the aerospace metal parts in application scenarios to obtain application scenario working condition features; a mechanical analysis execution unit for performing finite element mechanical analysis on the aerospace metal parts based on the application scenario working condition features 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 aerospace 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 partitioned stamping priority rules and outputting partitioned stamping process sequences; a process parameter analysis unit for performing process parameter analysis on the stamping process feature partitions using the partitioned stamping process sequences as constraints and outputting partitioned stamping control sequences; and a stamping control execution unit for using the partitioned stamping control sequences to perform batch production of the aerospace metal parts after scheduling the stamping sheet metal.

[0009] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0010] The method provided in this application embodiment collects application scenario operating conditions data for aerospace metal parts to obtain application scenario operating condition characteristics; performs finite element mechanical analysis on the aerospace metal parts based on the application scenario operating condition characteristics to obtain process mechanical feature partitions; by running a process rule library, performs stamping feature backtracking identification on the stamping component structure model of the aerospace metal parts to obtain stamping process feature partitions; based on partitioned stamping priority rules, performs process priority analysis on the stamping process feature partitions to output partitioned stamping process sequences; uses the partitioned stamping process sequences as constraints to perform process parameter analysis on the stamping process feature partitions to output partitioned stamping control sequences; after scheduling the stamping sheet metal, uses the partitioned stamping control sequences for mass production of the aerospace metal parts. This achieves the technical effect of improving the production quality and efficiency of aerospace metal parts while ensuring high precision and high reliability of the stamping process. Attached Figure Description

[0011] Figure 1 A schematic diagram of the precision forming control method for manufacturing aerospace metal parts provided in this application;

[0012] Figure 2 This is a schematic diagram of the precision forming control system for manufacturing aerospace metal parts, provided in this application.

[0013] Explanation of reference numerals in the attached figures: 11. Working condition feature acquisition unit; 12. Mechanical analysis execution unit; 13. Stamping feature backtracking unit; 14. Process execution analysis unit; 15. Process parameter analysis unit; 16. Stamping control execution unit. Detailed Implementation

[0014] This application provides a precision forming control method and system for manufacturing aerospace metal parts. It addresses the technical problems of low processing efficiency and poor processing accuracy in existing stamping processes for aerospace metal parts, which consequently affect the final performance and production efficiency of the parts. The method achieves the technical effect of improving the production quality and efficiency of aerospace metal parts while ensuring the high precision and reliability of the stamping process.

[0015] The technical solutions of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. It should be understood that the present invention is not limited to the exemplary embodiments described herein. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention. It should also be noted that, for ease of description, only the parts related to the present invention are shown in the accompanying drawings, not all of them.

[0016] Example 1, as Figure 1 As shown, this application provides a precision forming control method for manufacturing aerospace metal parts, the method comprising:

[0017] A100: Collects application scenario operating conditions data for aerospace metal parts to obtain application scenario operating condition characteristics.

[0018] In one embodiment, the application scenario operating conditions of aerospace metal parts are collected to obtain application scenario operating condition characteristics. The method step A100 provided by this invention includes:

[0019] A110: Based on the unique identifier of the aviation metal part, application scenario data is collected to obtain multiple historical application scenario records, including load condition records, environmental condition records, and usage condition records.

[0020] A120: By extracting extreme scenario features from the multiple historical application scenario records, application scenario operating condition information is obtained.

[0021] A130: Based on the component assembly characteristics of the aerospace metal parts, the transmission components are called up to obtain multiple component codes of multiple associated transmission components.

[0022] A140: Use the codes of the multiple components to call network data and obtain information about multiple associated components.

[0023] A150: The application scenario operating condition information and multiple related component information constitute the application scenario operating condition characteristics.

[0024] Specifically, it should be understood that a unique identifier is a code used to uniquely identify an aerospace metal part, which can be a part number, serial number, etc. Through the unique identifier, application scenario records related to the aerospace metal part can be retrieved from a database or data storage system. Based on this, this embodiment collects application scenario data according to the unique identifier of the aerospace metal part, obtaining multiple historical application scenario records. The data composition of each historical application scenario record includes, but is not limited to: load condition records (recording the load conditions borne by the aerospace metal part under different application scenarios, such as transmission torque, centrifugal force, vibration excitation, etc.), environmental condition records (recording the environmental conditions of the aerospace metal part under different application scenarios, such as temperature, humidity, pressure, etc.), and usage condition records (recording the usage conditions of the aerospace metal part under different application scenarios, such as rotational speed, operating frequency, operating time, etc.).

[0025] It should be understood that extreme scenario feature extraction refers to extracting the most representative and extreme working condition features from the records of the multiple historical application scenarios. These features can reflect the maximum load, the most severe environmental conditions and the most complex usage conditions that aerospace metal parts may encounter in actual applications.

[0026] This embodiment extracts extreme scenario features from the records of multiple historical application scenarios to obtain application scenario operating condition information. The application scenario operating condition information includes static scenario operating condition information reflecting the load and environmental conditions of aerospace metal parts under static conditions, and dynamic scenario operating condition information reflecting the load and environmental conditions of aerospace metal parts under dynamic conditions. The specific application of the application scenario operating condition information will be described in the following description.

[0027] It should be understood that component assembly features refer to the assembly relationship between aerospace metal parts and other transmission components, including connection methods, assembly positions, assembly sequences, etc. In this embodiment, the component assembly features are used to call multiple associated transmission components connected to the aerospace metal parts and obtain the component codes of these transmission components. It should be understood that the component code is a code used to uniquely identify the transmission component, and can be a part number, serial number, etc.

[0028] By encoding these multiple components, information about multiple associated transmission components can be retrieved from a database or data storage module. This associated component information includes, but is not limited to, the geometric dimensions, shape, and key features of the transmission components; the material grade and mechanical property parameters (such as elastic modulus, yield strength, strain hardening index, etc.) of the transmission components; and the connection methods and assembly relationships between the transmission components and aerospace metal parts. This information about multiple associated components provides the foundational data for subsequent assembly structure model construction.

[0029] The application scenario operating condition information and information from multiple related transmission components are integrated to form the application scenario operating condition characteristics.

[0030] It should be noted that the working condition acquisition method in this embodiment is a flexible method that collects historical data through a unique identifier and extracts extreme scenario features to form working condition information. This method is adaptable to the information acquisition of different aerospace metal parts with different structural and performance requirements, and provides basic data for subsequent process optimization.

[0031] This embodiment collects the working conditions of the application scenario, providing basic data for subsequent finite element mechanical analysis and stamping process optimization, and indirectly achieving the technical effect of ensuring the high-precision fit and reliability of the processed aerospace metal parts in complex working environments.

[0032] A200: Based on the operating conditions of the application scenario, perform finite element mechanical analysis on the aerospace metal parts to obtain process mechanical feature partitions.

[0033] In one embodiment, finite element mechanical analysis is performed on the aerospace metal part according to the operating conditions of the application scenario to obtain process mechanical feature partitioning. Step A200 of the method provided by this invention includes:

[0034] A210: Retrieve local data based on the unique identifier of the aerospace metal part to obtain information on aerospace stamping components.

[0035] A220: Based on the assembly features of the components, the information of the aerospace stamping components and the information of multiple related components are assembled and integrated to obtain an assembly structure model.

[0036] A230: After applying multiple loads to the assembly structure model based on the application scenario working condition information, the mechanical response diagram is extracted from the assembly structure model using the stamping component structure model as the stamping influence range constraint.

[0037] A240: Use the process mechanics threshold to traverse the mechanical response map and filter out the process mechanics feature partitions.

[0038] In one embodiment, after applying multiple loads to the assembly structure model based on the application scenario working condition information, and using the stamping component structure model as the stamping influence range constraint, a mechanical response diagram is extracted from the assembly structure model. Step A230 of the method provided by this invention includes:

[0039] A231: Extract static scene operating condition information and dynamic scene operating condition information from the application scenario operating condition information.

[0040] A232: After applying static loads to the assembly structure model based on the static scene working condition information, the static stress cloud map and static deformation vector map are extracted from the assembly structure model, using the stamping component structure model as the stamping influence range constraint.

[0041] A233: After applying dynamic loads to the assembly structure model based on 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.

[0042] A234: The transient stress cloud diagram is used to compensate the static stress cloud diagram to obtain a corrected stress cloud diagram.

[0043] A235: The transient deformation vector diagram is used 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.

[0044] In one embodiment, the mechanical response map is traversed using a process mechanical threshold, and the process mechanical feature partitions are filtered and output. Step A240 of the method provided by this invention includes:

[0045] A241: Preset grid scale.

[0046] A242: The modified stress cloud map is divided using the aforementioned gridding scale to obtain multiple modified stress blocks.

[0047] A243: Using the yield stress threshold in the process mechanics threshold, the multiple modified stress blocks are traversed to obtain the high stress zone distribution, wherein the high stress zone distribution includes W modified stress blocks.

[0048] A244: The modified deformation vector map is divided using the aforementioned gridding scale to obtain multiple modified deformation vector blocks.

[0049] A245: Using the significant deformation threshold in the process mechanics threshold, the multiple modified deformation vector blocks are traversed to filter and obtain the high deformation region distribution, wherein the high deformation region distribution includes M modified deformation vector blocks, and the high stress region distribution and the high deformation region distribution constitute the process mechanics feature partition.

[0050] In one embodiment, after applying dynamic loads to the assembly structure model based on dynamic scene working condition information, and using the stamping component structure model as a constraint on the stamping influence range, transient stress cloud map and transient deformation vector map are extracted from the assembly structure model. Step A233 of the method provided by this invention includes:

[0051] A2331: Divide the dynamic scene condition information equally to obtain K stages of scene condition information.

[0052] A2332: After applying dynamic loads to the assembly structure model step by step using the K stage scenario working condition information, the K stage stress cloud diagrams and K stage deformation vector diagrams are extracted from the assembly structure model, with the stamping component structure model as the stamping influence range constraint.

[0053] A2333: The transient stress cloud map is obtained by integrating the regional stress extrema by comparing the stress cloud maps of the K stages.

[0054] A2334: The transient deformation vector diagram is obtained by performing regional deformation extremum integration by comparing the K stage deformation vector diagrams.

[0055] In one embodiment, the assembly integration of the aerospace stamping component information and multiple related component information is performed based on the component assembly features to obtain an assembly structure model. Step A220 of the method provided by this invention includes:

[0056] A221: Using the information of the aerospace stamping component, a geometric simplification model is performed to obtain the structural model of the stamping component.

[0057] A222: Extract structural features and material features of multiple associated components from the information of the multiple associated components.

[0058] A223: The structural features and material features of the multiple associated components are used as search conditions for network modeling and scheduling to obtain multiple transmission component structural models.

[0059] A224: Based on the assembly features of the components, perform assembly fitting of the stamping component structural model and multiple transmission component structural models to obtain the assembly structural model.

[0060] Specifically, in this embodiment, local data is first retrieved based on the unique identifier of the aerospace metal part to obtain the aerospace stamping part information, which represents detailed information about the aerospace stamping part. The aerospace stamping part information includes, but is not limited to, geometric parameters, material properties, and design drawings, providing basic data for subsequent finite element mechanical analysis.

[0061] Geometric simplification modeling is performed using information from aerospace stamping components to extract key features and remove non-key features, thereby obtaining the structural model of the stamping component. Specifically, key features, such as transmission teeth, sealing grooves, and thin-walled areas, can be extracted from the 3D model of the aerospace stamping component, while non-key features such as chamfers and small holes are removed. Through geometric simplification modeling, the complexity of the model can be reduced, improving the efficiency and accuracy of subsequent finite element analysis.

[0062] It should be understood that features such as transmission tooth profile and sealing groove contribute more than 95% to the mechanical response, while secondary features such as chamfers / holes have less than 1% impact 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%, shorten the solution time, and does not affect the accuracy of high stress areas (such as thin-walled areas) (error < 5%).

[0063] It should be understood that the purpose of retaining chamfers in physical manufacturing is to avoid sharp angles from causing injury, and the purpose of adding small holes is to reduce weight or for wiring. Based on this, this embodiment obtains various structural features for non-mechanical purposes as multiple sample non-critical features by interacting with aerospace metal component manufacturers. Similarly, based on whether the component structural features affect the component's mechanical properties, the same method is used to obtain multiple sample mechanically related structural features as key features for modeling, which are used for reference to simplify modeling.

[0064] The geometric simplification modeling described herein essentially involves simplifying a complex geometric model while preserving the original mechanical properties of the component. Specifically, the modeling focus is on removing non-critical features with minimal impact on mechanical properties, such as chamfers and small holes, while retaining critical features that significantly influence the component's mechanical properties and stress conditions, such as transmission gears, sealing grooves, and thin-walled areas. This geometric simplification modeling effectively reduces model complexity while ensuring that the model accurately reflects the actual mechanical state of the component after subsequent integration of operating conditions and performance information.

[0065] Extract and acquire all necessary information related to aerospace metal parts from multiple associated component information, specifically including the structural features and material features of multiple associated components of the multiple associated transmission components.

[0066] By accessing network data, multiple sample transmission component finite element models that match the structural features and material features of the multiple related components mentioned above are obtained from the database or data storage system. These models serve as the structural models of the multiple related transmission components, providing necessary data support for subsequent assembly fitting.

[0067] Specifically, in this embodiment, the load is divided into static scenario working condition information and dynamic scenario working condition information according to the application scenario working condition information, and static load and dynamic load are applied to the assembly structure model respectively.

[0068] For example, the extraction of static scene operating condition information includes: extracting the first load condition (extracting the load conditions of the aerospace metal parts under static conditions, such as transmission torque, centrifugal force, etc.), extracting the first environmental condition (extracting the environmental conditions of the aerospace metal parts under static conditions, such as temperature, humidity, pressure, etc.), and extracting the first usage condition (extracting the usage conditions of the aerospace metal parts under static conditions, such as rotational speed, operating frequency, operating time, etc.). The data structure obtained from the extraction of static scene operating condition information is similar to that, and will not be described in detail here.

[0069] Furthermore, the dynamic scenario load information is divided into K stages. Each stage represents a specific phase of the dynamic load, with parameters such as amplitude and frequency gradually increasing. This staged approach can more accurately simulate dynamic changes in actual operating conditions.

[0070] Based on the extracted static scene condition information, static loads are applied to the assembly structure model. After applying the static loads, using the stamping component structure model as the stamping influence range constraint, static stress cloud maps and static deformation vector maps are extracted from the assembly structure model. The static stress cloud map shows the stress distribution of the assembly structure model under static loads, and the static deformation vector map shows the deformation of the assembly structure model under static loads. These maps provide basic data under static conditions for subsequent process mechanics feature partitioning.

[0071] Using the K-stage scenario working condition information, dynamic loads are applied to the assembly structure model step by step. At each stage, after applying the corresponding dynamic load, the stamping component structure model is used as the stamping influence range constraint. Stage stress cloud diagrams and stage deformation vector diagrams are extracted from the assembly structure model, ultimately yielding K-stage stress cloud diagrams and K-stage deformation vector diagrams.

[0072] The stress values ​​of the same region in different stages are compared among the stress cloud maps of K stages, and the maximum value is taken as the transient stress value of that region. This method ensures that the transient stress cloud map reflects the maximum stress distribution of the assembled structural model under dynamic loads. The transient stress cloud map is obtained by integrating the regional stress extrema of the K stage stress cloud maps using this method.

[0073] Similarly, the deformation values ​​of each region at different stages are compared, and the maximum value is taken as the transient deformation value of that region. By comparing the deformation vector maps of the K stages, the regional deformation extreme values ​​are integrated to obtain the transient deformation vector map.

[0074] The stress values ​​in the transient stress cloud map are superimposed with the stress values ​​in the static stress cloud map, or the maximum value is taken, to obtain the corrected stress cloud map that more accurately reflects the stress distribution. The corrected stress cloud map integrates the stress information of aerospace metal parts under static and dynamic conditions.

[0075] Similarly, the deformation values ​​in the transient deformation vector map are superimposed with or the maximum value is taken from the static deformation vector map to obtain a more accurate modified deformation vector map that reflects the deformation. This modified deformation vector map integrates deformation information of aerospace metal parts under both static and dynamic conditions, along with a modified stress cloud. Figure 1 This constitutes the aforementioned mechanical response diagram, providing comprehensive basic data for subsequent process mechanical characteristic partitioning.

[0076] Furthermore, this embodiment presets a grid scale to segment the mechanical response map. The grid scale can be set according to actual needs, for example, to 0.1 mm or less, to ensure sufficient accuracy of the segmented blocks. The preset grid scale provides the basis for subsequent block segmentation and threshold traversal.

[0077] The modified stress cloud map is divided into multiple small grid regions using the aforementioned gridding scale, with each grid region serving as a modified stress block, resulting in a total of multiple modified stress blocks.

[0078] The yield stress threshold is set to a certain proportion of the material's yield strength. Then, each modified stress block is traversed, and blocks with stress values ​​exceeding the threshold are marked as high stress areas. The distribution of high stress areas includes W modified stress blocks.

[0079] Using the same method, the modified deformation vector map is segmented based on the gridded scale to obtain multiple modified deformation vector blocks.

[0080] A significant deformation threshold is set when the deformation exceeds a certain range (for example, based on the ductility of aluminum alloy skin and stamping process requirements, the significant deformation threshold is set to 15%, and its effectiveness in suppressing cracks is verified through the fatigue test of Airbus A320 skin). 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 zones. The distribution of high deformation zones includes M modified deformation vector blocks. It should be understood that in this embodiment, W and M are unspecified positive integers.

[0081] This embodiment, through finite element mechanical analysis of aerospace metal parts, can accurately evaluate their mechanical properties under different working conditions, identify key areas including high-stress and high-deformation zones, and achieve the technical effect of providing basic information for subsequent precision forming stamping control analysis. A300: By running the process rule library, the stamping feature backtracking identification is performed on the process mechanical feature partitions of the aerospace metal parts in the stamping component structure model to obtain the stamping process feature partitions.

[0082] In one embodiment, by running a process rule base, the stamping feature partitions of the stamping component structure model of the aerospace metal part are identified by backtracking the stamping features to obtain the stamping process feature partitions. Step A300 of the method provided by this invention includes:

[0083] A310: Interactively obtain multiple sample stamping process types with various sample stamping shape characteristics.

[0084] A320: Maps and stores multiple sample stamping process types based on the various sample stamping shape features, thus completing the construction of the process rule library.

[0085] A330: Using the W modified stress blocks in the high stress zone distribution as local shape acquisition guides, and tracing back the local stamping structure of the stamping component structural model, W high stress-related stamping shapes are obtained.

[0086] A340: By traversing the process rule library and comparing the stamping shape features of the W high-stress associated stamping shapes, W high-stress stamping process types are obtained.

[0087] A350: By analogy, the M high-deformation stamping process types of the M modified deformation vector blocks are obtained.

[0088] A360: 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, thus obtaining the stamping process feature partitioning.

[0089] Specifically, in this embodiment, stamping process types corresponding to different stamping shape features are collected. For example, hole-punching process, slot-slotting process, boss-bossing process, recess-recessing process, bending-bending process, and stretching-stretching process are collected as various sample stamping process types for the various sample stamping shape features.

[0090] By mapping and storing the various sample stamping shape features and various sample stamping process types, the construction of the process rule base is completed. It should be understood that the process rule base stores various stamping shape features and their corresponding stamping process types, providing data support for subsequent stamping feature backtracking and identification.

[0091] Based on W modified stress blocks in the high-stress zone distribution, local shape acquisition is performed on the stamping component structural model. For example, if a modified stress block is located around a hole, then the hole is a high-stress-related stamping shape. In this way, the W modified stress blocks are used as local shape acquisition guides, and by tracing back the local stamping structure of the stamping component structural model, W high-stress-related stamping shapes are obtained.

[0092] The W high-stress associated stamping shapes are compared with the sample stamping shape features in the process rule library. For example, if a high-stress associated stamping shape is a hole, the comparison can determine 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 to compare their stamping shape features, resulting in W high-stress stamping process types.

[0093] A similar method to that used for high-stress zone distribution is employed to process the M modified deformation vector blocks. For example, if a modified deformation vector block is located in a bending region, then that bending region represents a high-deformation associated stamping shape. By comparing with the process rule library, the corresponding stamping process type can be determined to be a bending process, thus obtaining the M high-deformation stamping process types.

[0094] 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, thus obtaining the stamping process feature partitioning.

[0095] This embodiment uses a process rule base to perform stamping feature backtracking identification on the process mechanical feature partitions of the stamped component structure model of the aerospace metal parts, thereby obtaining stamping process feature partitions. This provides important basic data for subsequent stamping process optimization and ensures the high precision and high reliability of the stamping process.

[0096] A400: Based on the partitioned stamping priority rule, perform process priority analysis on the stamping process feature partitions and output the partitioned stamping process sequence.

[0097] Specifically, it should be understood that the partitioned stamping priority rules refer to the execution priority of various stamping processes. Based on these rules, the execution order of different stamping processes can be determined.

[0098] In this embodiment, based on the W modified stress blocks in the high-stress zone distribution and combined with the high-stress stamping process type, the stamping sequence of each block is determined. The hierarchy refers to placing the same stamping process in a sorting level; for example, all punching processes are placed in the first level, all grooving processes in the second level, and so on. Multiple modified stress blocks within the same hierarchy have no specific order because they employ the same stamping process. In this way, the first stamping process hierarchy sequence is generated.

[0099] Based on the M modified deformation vector blocks in the high-deformation zone distribution, and combined with the high-deformation stamping process type, the stamping sequence of each block is determined. The hierarchy refers to placing the same stamping process in a sorting level; for example, all bending processes are placed in the first level, all drawing processes in the second level, and so on. Multiple modified deformation vector blocks within the same hierarchy have no specific order because they employ the same stamping process. Ultimately, the first stamping process hierarchy sequence and the second stamping process hierarchy sequence together constitute the partitioned stamping process sequence.

[0100] A500: Using the partitioned stamping process sequence as a constraint, perform process parameter analysis on the stamping process feature partitions and output the partitioned stamping control sequence.

[0101] In one embodiment, the method step A500 provided by the present invention includes:

[0102] A510: Based on the partitioned stamping priority rule and W high-stress stamping process types, perform process priority analysis on the W modified stress blocks and output the first stamping process level sequence.

[0103] A520: Similarly, based on the M high-deformation stamping process types, process priority analysis is performed on the M modified deformation vector blocks to output a second stamping process hierarchy sequence, wherein the first stamping process hierarchy sequence and the second stamping process hierarchy sequence constitute the partitioned stamping process sequence.

[0104] A530: Using the W modified stress blocks as local parameter acquisition guides, the W high-stress related structural parameters are obtained by backtracking the local structural parameters of the stamping component structural model.

[0105] A540: Using the W high-stress stamping process types as constraints, process parameters are matched for the W high-stress associated structural parameters to obtain W first-zone stamping control parameters.

[0106] A550: The first stamping control sequence is obtained by combining the W first-partition stamping control parameters according to the first stamping process hierarchy sequence.

[0107] A560: And so on, to obtain the second stamping control sequence.

[0108] A570: Concatenate the first stamping control sequence and the second stamping control sequence, and output the partitioned stamping control sequence.

[0109] The method for obtaining the partitioned stamping process sequence has been described in detail in step A400 of this embodiment, so it will not be repeated here.

[0110] Furthermore, in this embodiment, based on the W modified stress blocks in the high stress zone distribution, the local structural parameters of the stamping component structural model are backtracked to extract structural parameters related to high stress, such as geometric dimensions and material properties, to obtain the W high stress-related structural parameters.

[0111] Furthermore, based on the high-stress stamping process type, process parameters are matched for the high-stress related structural parameters to determine key parameters in the stamping process, such as stamping force, die clearance, and stamping speed, thereby obtaining the W first-zone stamping control parameters.

[0112] According to the first stamping process hierarchy sequence, the W first zone stamping control parameters are combined in sequence. For two or more first zone stamping control parameters at the same level, they are sorted according to the stamping intensity, with the parameter with the greater stamping intensity placed first. In this way, the rationality and efficiency of the stamping process can be ensured, and the first stamping control sequence is finally generated.

[0113] Using a method similar to the first stamping control sequence, the M second-zone stamping control parameters are combined sequentially according to the second stamping process hierarchy sequence to generate the second stamping control sequence.

[0114] The end of the first stamping control sequence is connected to the beginning of the second stamping control sequence in sequence to complete the splicing of the partitioned stamping control sequence.

[0115] This embodiment uses the partitioned stamping process sequence as a constraint and combines it with process parameter analysis to generate a precise 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 aerospace metal parts.

[0116] Furthermore, this implementation is universal and applicable to the precision forming of any aerospace metal parts. Specifically, this implementation collects data through unique identifiers, extracts extreme scenario features, and forms general working condition information to provide comprehensive support for analysis and optimization. Using finite element mechanical analysis, combined with component assembly features and multi-variable load application, a mechanical response diagram is generated, and key areas are screened out through process mechanical thresholds to form process mechanical feature partitions. Based on the process rule library, the process mechanical feature partitions are combined with the stamping component structural model to retrospectively identify stamping process feature partitions, and a partitioned stamping process sequence is generated through process priority analysis. Then, process parameter analysis is performed to output the partitioned stamping control sequence.

[0117] Steps A100-A500 in this embodiment cover the complete process from data acquisition to production. Each step adopts a general and scalable method and technology. Whether it is a simple or complex aerospace metal part, it can achieve precision forming control by appropriate adjustment and optimization, effectively improving production efficiency and processing accuracy.

[0118] A600: After scheduling the stamping sheet metal, the aerospace metal parts are mass-produced using the partitioned stamping control sequence.

[0119] Specifically, in this embodiment, the stamping equipment is parameter-set and process-controlled according to the partitioned stamping control sequence. After the stamping sheet is scheduled, the stamping equipment is run using the partitioned stamping control sequence to carry out the mass production of the aerospace metal parts.

[0120] For example, the comparison table of improved precision of manufactured parts after processing in this embodiment is as follows:

[0121]

[0122] This embodiment achieves precise control over the stamping and forming of aerospace metal parts, thereby improving the production quality and efficiency of aerospace metal parts while ensuring high precision and reliability of the stamping process.

[0123] Example 2, based on the same inventive concept as the precision forming control method for manufacturing aerospace metal parts in the foregoing examples, such as... Figure 2 As shown, this application provides a precision forming control system for manufacturing aerospace metal parts, wherein the system includes:

[0124] The working condition feature acquisition unit 11 is used to acquire the working conditions of the aerospace metal parts in the application scenario and obtain the working condition features of the application scenario.

[0125] The mechanical analysis execution unit 12 is used to perform finite element mechanical analysis on the aerospace metal parts according to the working conditions of the application scenario, and obtain the process mechanical feature partitions.

[0126] The stamping feature backtracking unit 13 is used to perform stamping feature backtracking identification on the process mechanical feature partition of the stamping component structure model of the aerospace metal part by running the process rule library, so as to obtain the stamping process feature partition.

[0127] The process execution analysis unit 14 is used to perform process priority analysis on the stamping process feature partitions based on the partition stamping priority rules, and output the partition stamping process sequence.

[0128] The process parameter analysis unit 15 is used to perform process parameter analysis on the stamping process feature partitions with the partitioned stamping process sequence as a constraint, and output the partitioned stamping control sequence.

[0129] The stamping control execution unit 16 is used to perform mass production of the aerospace metal parts by using the partitioned stamping control sequence after scheduling the stamping sheet.

[0130] In one embodiment, the working condition feature acquisition unit 11 is further configured to:

[0131] Application scenario data is collected based on the unique identifier of the aerospace metal component to obtain multiple historical application scenario records, including load condition records, environmental condition records, and usage condition records. Extreme scenario features are extracted from these historical application scenario records to obtain application scenario operating condition information. Transmission components are called based on the component assembly characteristics of the aerospace metal component to obtain multiple component codes for multiple associated transmission components. Network data is called using these component codes to obtain information about multiple associated components. The application scenario operating condition information and the information about multiple associated components constitute the application scenario operating condition features.

[0132] In one embodiment, the mechanical analysis execution unit 12 is further configured to:

[0133] Local data is retrieved based on the unique identifier of the aerospace metal part to obtain aerospace stamping component information; the aerospace stamping component information and information of multiple related components are integrated according to the component assembly characteristics to obtain an assembly structure model; after applying multiple loads to the assembly structure model based on the application scenario working condition information, the mechanical response map is extracted from the assembly structure model with the stamping component structure model as the stamping influence range constraint; the mechanical response map is traversed using process mechanical thresholds to filter and output the process mechanical feature partitions.

[0134] In one embodiment, the mechanical analysis execution unit 12 is further configured to:

[0135] Static and dynamic scene operating condition information is extracted from the application scenario operating condition information. After applying static loads to the assembly structure model based on the static scene operating condition information, static stress cloud diagrams and static deformation vector diagrams are extracted from the assembly structure model, using the stamping component structure model as the stamping influence range constraint. After applying dynamic loads to the assembly structure model based on the dynamic scene operating condition information, transient stress cloud diagrams and transient deformation vector diagrams are extracted from the assembly structure model, using the stamping component structure model as the stamping influence range constraint. The transient stress cloud diagrams are used to compensate the static stress cloud diagrams to obtain corrected stress cloud diagrams. The transient deformation vector diagrams are used to compensate the static deformation vector diagrams to obtain corrected deformation vector diagrams. The corrected deformation vector diagrams and corrected stress cloud diagrams constitute the mechanical response diagram.

[0136] In one embodiment, the mechanical analysis execution unit 12 is further configured to:

[0137] A preset grid scale is used to segment the modified stress cloud map, resulting in multiple modified stress blocks. The yield stress threshold from the process mechanics threshold is used to traverse the multiple modified stress blocks, and a high-stress area distribution is obtained, wherein the high-stress area distribution includes W modified stress blocks. The modified deformation vector map is segmented using the grid scale, resulting in multiple modified deformation vector blocks. The significant deformation threshold from the process mechanics threshold is used to traverse the multiple modified deformation vector blocks, and a high-deformation area distribution is obtained, wherein the high-deformation area distribution includes M modified deformation vector blocks. The high-stress area distribution and the high-deformation area distribution constitute the process mechanics feature partition.

[0138] In one embodiment, the stamping feature backtracking unit 13 is further configured to:

[0139] Multiple sample stamping process types with various sample stamping shape features are obtained interactively; the multiple sample stamping process types with various sample stamping shape features are mapped and stored to complete the construction of the process rule base; the W modified stress blocks in the high stress area distribution are used as local shape acquisition guides, and the local stamping structure of the stamping part structure model is traced back to obtain W high stress associated stamping shapes; the W high stress associated stamping shapes are traversed through the process rule base to compare stamping shape features to obtain W high stress stamping process types; and so on, M high deformation stamping process types with 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 partitioning.

[0140] In one embodiment, the process parameter analysis unit 15 is further configured to:

[0141] Based on the partitioned stamping priority rules and W high-stress stamping process types, process priority analysis is performed on the W modified stress blocks to output a first stamping process hierarchy sequence. Similarly, process priority analysis is performed on the M modified deformation vector blocks according to the M high-deformation stamping process types to output a second stamping process hierarchy sequence. The first and second stamping process hierarchy sequences constitute the partitioned stamping process sequence. Using the W modified stress blocks as local parameter acquisition guides, backtracking on the local structural parameters of the stamped component structural model yields 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 hierarchy sequence to obtain a first stamping control sequence. This process is repeated to obtain a second stamping control sequence. The first and second stamping control sequences are then concatenated to output the partitioned stamping control sequence.

[0142] In one embodiment, the mechanical analysis execution unit 12 is further configured to:

[0143] The dynamic scene working condition information is evenly distributed to obtain K stages of scene working condition information. After applying dynamic loads to the assembly structure model step by step using the K stages of scene working condition information, the K stages of stress cloud diagrams and K stages of deformation vector diagrams are extracted from the assembly structure model, with the stamping component structure model as the stamping influence range constraint. The transient stress cloud diagram is obtained by performing regional stress extremum integration by comparing the K stages of stress cloud diagrams. The transient deformation vector diagram is obtained by performing regional deformation extremum integration by comparing the K stages of deformation vector diagrams.

[0144] In one embodiment, the mechanical analysis execution unit 12 is further configured to:

[0145] The 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 for network modeling and scheduling to obtain multiple transmission component structural models; the assembly fitting of the stamping component structural model and multiple transmission component structural models is performed according to the component assembly features to obtain the assembly structural model.

[0146] In summary, any of the methods or steps described above can be stored as computer instructions or programs in various types of computer memory, and the computer instructions or programs can be recognized by various types of computer processors to implement any of the above methods or steps.

[0147] 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 principle of the present invention shall fall within the patent protection scope of the present invention.

Claims

1. A precision forming control method for manufacturing aerospace metal parts, characterized in that, The method includes: The application scenario operating conditions of aerospace metal parts are collected to obtain the characteristics of the application scenario operating conditions. Finite element mechanical analysis was performed on the aerospace metal parts based on the operating conditions of the application scenario to obtain the process mechanical feature partitions. By running the process rule library, the stamping feature backtracking identification is performed on the process mechanical feature partition of the stamping component structure model of the aerospace metal part to obtain the stamping process feature partition; Based on the partitioned stamping priority rule, process priority analysis is performed on the stamping process feature partitions, and the partitioned stamping process sequence is output. Using the partitioned stamping process sequence as a constraint, process parameter analysis is performed on the stamping process feature partitions, and a partitioned stamping control sequence is output. After scheduling the stamping plates, the aerospace metal parts are mass-produced using the partitioned stamping control sequence.

2. The precision forming control method for manufacturing aerospace metal parts as described in claim 1, characterized in that, The method for collecting application scenario operating condition data of aerospace metal parts to obtain application scenario operating condition characteristics includes: Application scenario data is collected based on the unique identifier of the aerospace metal parts to obtain multiple historical application scenario records, including load condition records, environmental condition records, and usage condition records. By extracting extreme scenario features from the multiple historical application scenario records, application scenario operating condition information is obtained. Based on the component assembly characteristics of the aerospace metal parts, the transmission components are called up to obtain multiple component codes of multiple associated transmission components; By using the codes of the multiple components to perform network data retrieval, information on multiple associated components can be obtained; The application scenario operating condition information and the information of multiple related components constitute the application scenario operating condition characteristics.

3. The precision forming control method for manufacturing aerospace metal parts as described in claim 2, characterized in that, Based on the operating conditions of the application scenario, a finite element mechanical analysis is performed on the aerospace metal parts to obtain process mechanical characteristic partitions. The method includes: Local data is retrieved based on the unique identifier of the aerospace metal part to obtain information on aerospace stamping components; Based on the assembly characteristics of the components, the information of the aerospace stamping components and the information of multiple related components are integrated to obtain an assembly structure model; After applying multiple loads to the assembly structure model based on the application scenario working condition information, and using the stamping component structure model as the stamping influence range constraint, the mechanical response diagram is extracted from the assembly structure model. The mechanical response map is traversed using a process mechanical threshold, and the process mechanical feature partitions are filtered and output.

4. The precision forming control method for manufacturing aerospace metal parts as described in claim 3, characterized in that, After applying multiple loads to the assembly structure model based on the application scenario working condition information, and using the stamping component structure model as the stamping influence range constraint, a mechanical response diagram is extracted from the assembly structure model. The method includes: Extract static and dynamic scene operating condition information from the application scenario operating condition information; After applying static loads to the assembly structure model based on static scene working condition information, the static stress cloud map and static deformation vector map are extracted from the assembly structure model, using the stamping component structure model as the stamping influence range constraint. After applying dynamic loads to the assembly structure model based on 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. The static stress cloud diagram is compensated by the transient stress cloud diagram to obtain the corrected stress cloud diagram; The transient deformation vector diagram is used 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.

5. The precision forming control method for manufacturing aerospace metal parts as described in claim 4, characterized in that, The method involves traversing the mechanical response map using a process mechanical threshold and filtering out the process mechanical feature partitions. Preset grid scale; The modified stress cloud map is divided using the aforementioned gridding scale to obtain multiple modified stress blocks; The yield stress threshold in the process mechanics threshold is used to traverse the multiple modified stress blocks to filter out the high stress zone distribution, wherein the high stress zone distribution includes W modified stress blocks; The modified deformation vector image is divided using the aforementioned gridding scale to obtain multiple modified deformation vector blocks; The significant deformation threshold in the process mechanics threshold is used to traverse the multiple modified deformation vector blocks to filter out the high deformation region distribution, wherein the high deformation region distribution includes M modified deformation vector blocks, and the high stress region distribution and the high deformation region distribution constitute the process mechanics feature partition.

6. The precision forming control method for manufacturing aerospace metal parts as described in claim 5, characterized in that, By running a process rule base, the stamping feature partitions of the aerospace metal parts are identified by backtracking the process mechanical feature partitions in the stamping component structure model, thereby obtaining the stamping process feature partitions. The method includes: Interactively obtain multiple sample stamping process types with various sample stamping shape characteristics; The process rule base is constructed by mapping and storing the various sample stamping shape features of the various samples and various sample stamping process types. Using the W modified stress blocks in the high stress zone distribution as local shape acquisition guides, and tracing back the local stamping structure of the stamping component structural model, W high stress-related stamping shapes are obtained. The W high-stress associated stamping shapes are traversed through the process rule library to compare stamping shape features, resulting in W high-stress stamping process types. By analogy, the 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, thus obtaining the stamping process feature partitioning.

7. The precision forming control method for manufacturing aerospace metal parts as described in claim 6, characterized in that, The method includes: Based on the partitioned stamping priority rule and W high-stress stamping process types, process priority analysis is performed on the W modified stress blocks to output the first stamping process level sequence. Similarly, based on the M high-deformation stamping process types, process priority analysis is performed on the M modified deformation vector blocks to output a second stamping process hierarchy sequence, wherein the first stamping process hierarchy sequence and the second stamping process hierarchy sequence constitute the partitioned stamping process sequence. Using the W modified stress blocks as local parameter acquisition guides, and by tracing back the local structural parameters of the stamping component structural model, W high-stress related structural parameters are obtained. Using the W high-stress stamping process types as constraints, process parameters are matched for the W high-stress associated structural parameters to obtain W first-zone stamping control parameters; The first stamping control sequence is obtained by combining the W first-partition stamping control parameters according to the first stamping process hierarchy sequence; By analogy, the second stamping control sequence is obtained; The first stamping control sequence and the second stamping control sequence are spliced ​​together to output the partitioned stamping control sequence.

8. The precision forming control method for manufacturing aerospace metal parts as described in claim 4, characterized in that, After applying dynamic loads to the assembly structure model based on dynamic scene working condition information, and using the stamping component structure model as the stamping influence range constraint, the transient stress cloud map and transient deformation vector map are extracted from the assembly structure model. The method includes: The dynamic scene condition information is evenly divided to obtain K stages of scene condition information; After applying dynamic loads to the assembly structure model step by step using the K stage scenario working condition information, and using the stamping component structure model as the stamping influence range constraint, K stage stress cloud diagrams and K stage deformation vector diagrams are extracted from the assembly structure model. The transient stress cloud map is obtained by integrating the regional stress extrema by comparing the stress cloud maps of the K stages; The transient deformation vector map is obtained by performing regional deformation extremum integration by comparing the K stage deformation vector maps.

9. The precision forming control method for manufacturing aerospace metal parts as described in claim 3, characterized in that, Based on the assembly characteristics of the components, the assembly and integration of the aerospace stamping component information and information of multiple related components are performed to obtain an assembly structure model. The method includes: The information on the aerospace stamping component is used to perform geometric simplification modeling to obtain the structural model of the stamping component; Extract structural features and material features of multiple associated components from the information of the multiple associated components; The structural features and material features of the multiple associated components are used as search conditions for network modeling and scheduling to obtain multiple transmission component structural models. Based on the assembly characteristics of the components, the assembly fitting of the stamping component structural model and multiple transmission component structural models is performed to obtain the assembly structural model.

10. A precision forming control system for manufacturing aerospace metal parts, characterized in that, The steps for implementing the method according to any one of claims 1 to 9 include: The working condition feature acquisition unit is used to acquire the working condition of aerospace metal parts in application scenarios and obtain the working condition features of the application scenarios. The mechanical analysis execution unit is used to perform finite element mechanical analysis on the aerospace metal parts according to the working condition characteristics of the application scenario, and obtain the process mechanical characteristic partitioning. The stamping feature backtracking unit is used to perform stamping feature backtracking identification on the process mechanical feature partition of the aerospace metal part by running the process rule library and the stamping component structure model, so as to obtain the stamping process feature partition; The process execution analysis unit is used to perform process priority analysis on the stamping process feature partitions based on the partitioned stamping priority rules, and output the partitioned stamping process sequence. The process parameter analysis unit is used to perform process parameter analysis on the stamping process feature partitions with the partitioned stamping process sequence as a constraint, and output the partitioned stamping control sequence. The stamping control execution unit is used to perform mass production of the aerospace metal parts using the partitioned stamping control sequence after scheduling the stamping sheet.

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