Standard feature classification method for aircraft structure
By using standard feature classification methods, the skeleton elements of parts are identified and decomposed, decorative features are eliminated, and a set of structural features is generated. This solves the problems of lack of reusability and high difficulty in data exchange in part modeling methods, and realizes the reusability and rapid analysis capability of part modeling methods.
Patent Information
- Application Number
- CN202511976958.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-25
- Publication Date
- 2026-03-06
AI Technical Summary
In existing CAD systems, the part modeling methods are not reusable, which makes data exchange difficult and makes it impossible to quickly analyze the load-bearing capacity, process difficulty and manufacturing cost of parts. In addition, different designers use different modeling methods, which hinders data exchange between CAD systems and other CAX information systems.
Using a standard feature classification method, the part is divided into multiple regions by identifying and decomposing the skeleton elements of the part, identifying and eliminating decorative features, generating a set of structural features and a set of decorative features, and then organizing and reorganizing the data through a CAD system to achieve standardization of feature data, supporting data exchange and automated feature recognition between CAD, CAM, and CAE.
It achieves reusability of part modeling methods, improves data exchange efficiency, supports rapid analysis of part load-bearing capacity, process difficulty and manufacturing cost, simplifies data exchange between different systems, and is suitable for additive manufacturing part design.
Smart Images
Figure CN121614949A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of structural CAD modeling, and specifically relates to a standard feature classification method for aircraft structures. Background Technology
[0002] General-purpose CAD systems offer an unlimited number of methods for digital modeling parts, but different designers use different methods, making these methods unreusable. This also increases the difficulty for other CAX information systems to identify the modeling process, hindering data exchange between CAD and other CAX systems. It prevents the extraction of design data change information and the rapid analysis and evaluation of part load-bearing capacity, technological complexity, and manufacturing costs. Furthermore, the inconsistent methods and order of implementing various structural geometric features during part design result in unreusable modeling methods and inconsistent feature representations. Other CAX information systems face high difficulty in identifying the modeling process, have inefficient data exchange, and cannot quickly analyze and evaluate part load-bearing capacity, technological complexity, and manufacturing costs. Summary of the Invention
[0003] To address the aforementioned problems, this application provides a standard feature classification method for aircraft structures, including:
[0004] Step 1: Select the part object and divide the part into multiple preset part regions according to the skeleton elements of the part, wherein the skeleton elements include rib plane, stringer plane, leading edge plane and trailing edge plane.
[0005] Step 2: Identify the decorative features of the divided parts, and decompose the decorative features of the parts from the structural features to obtain the set of structural features and the set of decorative features of the parts;
[0006] Step 3: Based on the structural feature parameters, decompose the set of structural features into multiple types of structural features; based on the modification feature parameters, decompose the set of modification features into multiple types of modification features.
[0007] Step 4: Organize and record the feature data of all structural features and all modification features;
[0008] Step 5: Regenerate the entity based on the feature data, including all structural features and all modification features;
[0009] Step 6: When the spatial points of the entity correspond perfectly with the original part, output the feature data of all structural features and all decorative features; otherwise, identify the structural features or decorative features that differ, determine the feature data to be adjusted, and return to Step 4.
[0010] Preferably, the specific steps for obtaining the set of structural features of the part in step 2 include:
[0011] Step 21: Identify the decorative features of the divided parts;
[0012] Step 22: Remove the decorative features of the part from the structural features;
[0013] Step 23: If the part is entirely composed of structural features, skip to step 3; otherwise, skip to step 21.
[0014] Preferably, in step 22, the modification feature elimination specifically includes: using artificial intelligence technology to eliminate the transition region between features that have spatial intersection.
[0015] Preferably, the skeleton elements include rib planes, stringer planes, leading edge planes, and trailing edge planes.
[0016] Preferably, the structural feature refers to the basic unit constituting the part, which has only a unique value assigned to a parameter in a single dimension, including structural feature type, size parameter, and positioning parameter; the modification feature refers to a local modification performed on the structural feature or a transition part between multiple structural features, including modification object, modification feature type, modification size parameter, and modification feature positioning.
[0017] Preferably, the structural feature types adopt a hierarchical identification method, including top-level feature types and sub-type feature types; wherein, the vertical rib feature includes L-shaped vertical ribs and T-shaped vertical ribs, and the curved plate feature includes flat plate and curved plate sub-types.
[0018] Preferably, the removal of the modification features includes using artificial intelligence technology to identify and separate transition areas, such as ramps and fillets, so that the part is restored to a set of basic structural features, thereby eliminating the influence of the modification features.
[0019] Preferably, the feature decomposition includes:
[0020] For a set of structural features, decomposition is performed based on feature type and parameter differences, where regions with different parameters under the same feature type are decomposed into different structural features;
[0021] For the set of modified features, decompose them according to the modified object and parameters.
[0022] Preferably, the parameter identification includes identifying cross-sectional dimension parameters based on the cross-sectional type for the vertical reinforcement features; for example, for a T-shaped girder, identifying the height h, web thickness t, and flange widths a, b, and c, wherein the height h ranges from 20 to 50 mm, the web thickness t ranges from 0.5 to 5 mm, and the flange widths a, b, and c range from 5 to 15 mm.
[0023] Preferably, the data record includes generating a feature identification code, a parameter group, and a hierarchical relationship table, wherein the feature identification code uniquely identifies each feature, the parameter group includes size parameters and positioning parameters, and the hierarchical relationship table records the parent-child relationships between features.
[0024] Preferably, the entity reconstruction includes combining parts using the identified feature information and performing geometric comparison through a CAD system to verify the consistency between the reconstructed entity and the original parts, with the tolerance range controlled within ±0.1mm.
[0025] Preferably, the method further includes CAX system integration: importing the decomposed feature information into the CAX system to realize data exchange and automated feature recognition between CAD, CAM, and CAE, thereby supporting rapid analysis of the load-bearing capacity, process difficulty, and manufacturing cost of parts. The CAX system integration includes generating a standardized feature library so that different parts can share the feature representation under the same standard, realizing the reusability of part modeling methods.
[0026] Preferably, the method is applicable to additive manufacturing part design, providing basic elements through a standardized feature library to support rapid part iteration and optimization.
[0027] Preferably, the typical aircraft structure processed by the method includes wing stiffened panels, fuselage frames and door structures, wherein the stiffened panels are decomposed into curved plate features and T-shaped stringer features. For the stiffened panels, the decomposed structural features include multiple curved plate features and T-shaped stringer features, each feature having an independent set of parameters and positioning information. Attached Figure Description
[0028] Figure 1 This is the execution flow of the present invention;
[0029] Figure 2 This is a schematic diagram of a typical stiffened wing panel structure as an example;
[0030] Figure 3 Decompose the hierarchical structure of a typical wing-stiffened panel structure as an example;
[0031] Figure 4 Here are the cross-sectional geometric parameters of the T-shaped stringer used as an example;
[0032] Figure 5 This is a summary of structural features obtained after decomposing a typical wing-stiffened panel structure as an example. Detailed Implementation
[0033] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some embodiments of this application, not all embodiments. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. To solve the above problems, this application provides a standard feature classification method for aircraft structures, including:
[0034] Step 1: Select the part object and divide the part into multiple preset part regions according to the skeleton elements of the part, wherein the skeleton elements include rib plane, stringer plane, leading edge plane and trailing edge plane.
[0035] Step 2: Identify the decorative features of the divided parts, and decompose the decorative features of the parts from the structural features to obtain the set of structural features and the set of decorative features of the parts;
[0036] Step 3: Based on the structural feature parameters, decompose the set of structural features into multiple types of structural features; based on the modification feature parameters, decompose the set of modification features into multiple types of modification features.
[0037] Step 4: Organize and record the feature data of all structural features and all modification features;
[0038] Step 5: Regenerate the entity based on the feature data, including all structural features and all modification features;
[0039] Step 6: When the spatial points of the entity correspond perfectly with the original part, output the feature data of all structural features and all decorative features; otherwise, identify the structural features or decorative features that differ, determine the feature data to be adjusted, and return to Step 4.
[0040] Design features include, but are not limited to, global parameters, structural features, and decorative features;
[0041] Design features are described by a unique feature identifier (attribute name) and several design parameters;
[0042] By classifying parts with differences (including spatial location) using the method described above, a unique set of feature identification codes and design parameter sets can be obtained;
[0043] Based on the features and parameter sets obtained from the decomposition, the original part can be restored.
[0044] Preferably, the specific steps for obtaining the set of structural features of the part in step 2 include:
[0045] Step 21: Identify the decorative features of the divided parts;
[0046] Step 22: Remove the decorative features of the part from the structural features;
[0047] Step 23: If the part is entirely composed of structural features, skip to step 3; otherwise, skip to step 21.
[0048] Preferably, in step 22, the modification feature elimination specifically includes: using artificial intelligence technology to eliminate the transition region between features that have spatial intersection.
[0049] The wall panel in the example ( Figure 2 There are three thickness zones based on the load conditions, and they are reinforced with stringers. When decomposing the part area, select the front and rear edge planes and the rib plane (the stringer plane in the skeleton cannot be selected as the boundary of the zone because it would cause the separation of individual structural features).
[0050] For each partition, the operation is performed according to the method of the present invention, and the steps of removing modifications, feature recognition, and parameter recognition are performed in sequence.
[0051] Ultimately, it can be obtained Figure 3 The hierarchical relationship and the summary information after decomposition can be found in [link to documentation]. Figure 5 :
[0052] Preferably, the skeleton elements include rib planes, stringer planes, leading edge planes, and trailing edge planes.
[0053] Preferably, the structural feature refers to the basic unit constituting the part, which has only a unique value assigned to a parameter in a single dimension, including structural feature type, size parameter, and positioning parameter; the modification feature refers to a local modification performed on the structural feature or a transition part between multiple structural features, including modification object, modification feature type, modification size parameter, and modification feature positioning.
[0054] Preferably, the structural feature types adopt a hierarchical identification method, including top-level feature types and sub-type feature types; wherein, the vertical rib feature includes L-shaped vertical ribs and T-shaped vertical ribs, and the curved plate feature includes flat plate and curved plate sub-types.
[0055] Preferably, the removal of the modification features includes using artificial intelligence technology to identify and separate transition areas, such as ramps and fillets, so that the part is restored to a set of basic structural features, thereby eliminating the influence of the modification features.
[0056] Preferably, the feature decomposition includes:
[0057] For a set of structural features, decomposition is performed based on feature type and parameter differences, where regions with different parameters under the same feature type are decomposed into different structural features;
[0058] For the set of modified features, decompose them according to the modified object and parameters.
[0059] Preferably, the parameter identification includes identifying cross-sectional dimension parameters based on the cross-sectional type for the vertical reinforcement features; for example, for a T-shaped girder, identifying the height h, web thickness t, and flange widths a, b, and c, wherein the height h ranges from 20 to 50 mm, the web thickness t ranges from 0.5 to 5 mm, and the flange widths a, b, and c range from 5 to 15 mm.
[0060] Preferably, the data record includes generating a feature identification code, a parameter group, and a hierarchical relationship table, wherein the feature identification code uniquely identifies each feature, the parameter group includes size parameters and positioning parameters, and the hierarchical relationship table records the parent-child relationships between features.
[0061] Preferably, the entity reconstruction includes combining parts using the identified feature information and performing geometric comparison through a CAD system to verify the consistency between the reconstructed entity and the original parts, with the tolerance range controlled within ±0.1mm.
[0062] Preferably, the method further includes CAX system integration: importing the decomposed feature information into the CAX system to realize data exchange and automated feature recognition between CAD, CAM, and CAE, thereby supporting rapid analysis of the load-bearing capacity, process difficulty, and manufacturing cost of parts. The CAX system integration includes generating a standardized feature library so that different parts can share the feature representation under the same standard, realizing the reusability of part modeling methods.
[0063] Preferably, the method is applicable to additive manufacturing part design, providing basic elements through a standardized feature library to support rapid part iteration and optimization.
[0064] Preferably, the typical aircraft structure processed by the method includes wing stiffened panels, fuselage frames and door structures, wherein the stiffened panels are decomposed into curved plate features and T-shaped stringer features. For the stiffened panels, the decomposed structural features include multiple curved plate features and T-shaped stringer features, each feature having an independent set of parameters and positioning information.
[0065] This also includes part-level global parameters: these are parameters that are common to multiple structural or decorative features in a part, such as ramp angle, bottom corner radius, corner radius, and hole chamfer size.
[0066] Structural features refer to the basic units that make up a part, each with a unique value assigned to a parameter in a single dimension. These include the following attributes: structural feature type, dimensional parameters, and positioning parameters. Structural feature types can be hierarchically identified; for example, under the vertical rib feature, there are L-shaped vertical ribs, T-shaped vertical ribs, etc.
[0067] Modification features refer to local modifications made to a structural feature, such as positioning holes or reinforcing bosses; or transitional areas between multiple structural features, such as ramps or fillets. Modification features include, but are not limited to, the following attributes: modification object, modification feature type, modification size parameters, and modification feature positioning.
[0068] For each part partition, AI technology is used to modify and eliminate transition areas between features that have spatial intersection, so that the part is restored to a set composed of basic structural features.
[0069] It should be added that: in step 1, the results of region division vary depending on the input, but this does not affect the final decomposition of the feature structure, but only affects the numbering of the underlying structural features.
[0070] Identify the structural feature types of parts. Among them, different parameter areas under the same feature type of part should be divided into different structural features, rather than the same feature parameter being labeled in a multi-dimensional form (for example, the different thickness areas in a stiffened wall panel should be decomposed into curved plate 1 / thickness a, curved plate 2 / thickness b, etc., instead of curved plate / thickness 1:a).
[0071] Identify part parameters. Different parameters are identified based on the feature type. For example, curved / flat features have thickness characteristics; vertical ribs have different cross-sectional dimension parameters depending on the cross-section type (e.g., T-shaped stringers). Figure 4 )wait.
[0072] Reassembly and verification. Use the various feature information identified above to assemble the parts and verify whether they are consistent with the original parts.
[0073] Data processing. After confirming that the feature decomposition is correct, the data is processed to obtain all feature information of the part.
[0074] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A method of classifying standard features of an aircraft structure, characterized in that, The method comprises the following steps: Step 1: selecting a part object, dividing the part into a plurality of preset part regions according to the skeleton elements possessed by the part, wherein the skeleton elements comprise rib planes, stringer planes, leading edge planes and trailing edge planes; Step 2: identifying the modification features of the divided part, and separating the modification features of the part from the structural features to obtain a structural feature set and a modification feature set of the part; Step 3: separating the structural feature set into a plurality of structural feature categories according to structural feature parameters, and separating the modification feature set into a plurality of modification feature categories according to modification feature parameters; Step 4: recording and sorting the feature data of all structural features and all modification features; Step 5: regenerating entities from all structural features and all modification features according to the feature data; Step 6: when the spatial points of the entities completely correspond to the original part, outputting the feature data of all structural features and all modification features, otherwise determining the structural features or modification features with differences, adjusting the feature data, and returning to step 4.
2. The method of claim 1, wherein, The specific steps for obtaining the structural feature set of the part in step 2 comprise: Step 21: identifying the modification features of the divided part; Step 22: eliminating the modification features of the part from the structural features; Step 23: when the part is completely composed of structural features, jumping to step 3, otherwise jumping to step 21.
3. The method of claim 2, wherein, In step 22, the elimination of the modification features specifically comprises: using artificial intelligence technology to eliminate the transition regions between features with spatial intersections.
4. The method of claim 1, wherein, The skeleton elements comprise rib planes, stringer planes, leading edge planes and trailing edge planes.
5. The method of claim 1, wherein, The structural features refer to basic units constituting the part, which have only one assignment in a single dimension parameter, and comprise structural feature types, size parameters and positioning parameters; the modification features refer to local modifications on the structural features or transition parts between a plurality of structural features, and comprise modification objects, modification feature types, modification size parameters and modification feature positioning.
6. The method of claim 1, wherein, The structural feature types adopt a hierarchical identification manner, comprising top-level feature types and sub-class feature types; wherein the stringer features comprise L-shaped stringers and T-shaped stringers, and the curved plate features comprise flat plates and curved plate sub-classes.
7. The method of claim 1, wherein, The elimination of the modification features comprises using artificial intelligence technology to identify and separate transition regions such as slopes and fillets, so as to restore the part to a set composed of basic structural features, thereby eliminating the influence of the modification features.
8. The method of claim 1, wherein, The feature separation comprises: For the structural feature set, the separation is performed according to the feature types and parameter differences, wherein different parameter regions under the same feature type are separated into different structural features; For the modification feature set, the separation is performed according to the modification objects and parameters.
9. The method of claim 1, wherein, The parameter identification comprises, for the stringer features, identifying the cross-sectional size parameters according to the cross-sectional types; for example, for a T-shaped stringer, identifying height h, web thickness t, and edge strip width a, b and c parameters, wherein the height h ranges from 20 to 50 mm, the web thickness t ranges from 0.5 to 5 mm, and the edge strip width a, b and c ranges from 5 to 15 mm.
10. The method of claim 1, wherein, The data record includes a feature identification code, a parameter group, and a hierarchical relationship table, wherein the feature identification code uniquely identifies each feature, the parameter group includes size parameters and positioning parameters, and the hierarchical relationship table records the parent-child relationship between features.
11. The method of claim 1, wherein, The entity reorganization includes part combination using the identified feature information, geometric comparison through a CAD system, verification of the consistency of the reorganized entity and the original part, and tolerance range control within ±0.1 mm.
12. The method of claim 1, wherein, The method further includes CAX system integration: importing the decomposed feature information into a CAX system to realize data exchange and automatic feature recognition among CAD, CAM, and CAE, thereby supporting rapid analysis of the load-carrying capacity, process difficulty, and manufacturing cost of the part.
13. The method of claim 1, wherein, The method is suitable for additive manufacturing part design, provides basic elements through a standardized feature library, and supports rapid iteration and optimization of the part.
14. The method of claim 1, wherein, The typical aircraft structures processed by the method include wing skin stiffened panels, fuselage frames, and door structures, wherein the stiffened panels are decomposed into curved panel features and T-shaped stringer features, and for the stiffened panels, the decomposed structural features include multiple curved panel features and T-shaped stringer features, each feature having independent parameter groups and positioning information.