Batch material description loading method and system
By creating a coordinate system based on the machining method in modular part design, automatically calculating the part envelope and loading material description information, the problems of large measurement error and low automation in the prior art are solved, and efficient and accurate material description loading is achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AVIC XAC COMMERCIAL AIRCRAFT CO LTD
- Filing Date
- 2025-12-27
- Publication Date
- 2026-05-12
AI Technical Summary
In modular part design, manually adding material description information is a huge workload. Existing technologies have large measurement errors and low automation, resulting in insufficient design efficiency and accuracy.
Based on the part processing method, a coordinate system is created by relying on the part surface. The part envelope is automatically calculated and material description information is loaded. It is applicable to machining, sheet metal, profiles and composite materials. A high-precision coordinate system that fits the part surface is established through the adaptive establishment of the rectangular coordinate system, so as to realize automatic loading.
It significantly improves design efficiency and accuracy, reduces human error, and is suitable for batch loading in single or modular designs, especially sheet metal, machined and composite parts.
Smart Images
Figure CN122020763A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aircraft digital structure design and manufacturing technology, specifically relating to a method and system for automatically creating a coordinate system based on processing methods and part surface features, and then batch loading part material description information. Background Technology
[0002] In modular part design, a single module contains several to hundreds of parts. Once the part model design in the module is completed, based on the MBD part dataset, designers need to manually add information such as material description (including material specifications, raw material size, etc.), processing method (including sheet metal, machining, composite materials, sewing, etc.), model attributes, and engineering annotations for each part in the module. Especially when developing new machines, the workload of manually adding this information in batches is enormous.
[0003] Among the information that needs to be added, model attributes and engineering annotations can be automatically added by calling and assigning values through the built-in attributes and methods of CATIA VBA. However, obtaining material description information requires automatic measurement and calculation of the model. How to measure and calculate is not obvious. This patent provides a method to establish a coordinate system based on the surface of the part according to the processing method, thereby determining the envelope of the part model, and finally loading the part material description information in batches in the module.
[0004] Specifically, it can be described as follows: Based on the part processing method and the part surface, the one-dimensional to three-dimensional (length, width, height) envelope of the measured object conforming to the processing is obtained by measurement and calculation. It should be noted that the envelope conforming to the processing provided by this patent is not the smallest cube envelope of the part, but rather the envelope conforming to the process and logic of manually loading material description. The specific method is as follows: Based on the part processing method, a suitable rectangular coordinate system is automatically established on the part surface. Based on this coordinate system, the envelope of the part is obtained, and the material description information is obtained, thereby saving workload and avoiding human error.
[0005] Patent CN111783217 mentions an automatic method for obtaining the blank dimensions of machined parts based on CATIA VBA. This patent is applicable to machined parts. The blank dimension coordinate system is obtained based on the inertia axis. Since all surfaces (machined surfaces) of aerospace parts are generally not parallel to the inertia axis, the measured blank dimensions have a large error and may also cause inaccurate material specifications to be selected.
[0006] The purpose of this application is to provide a method for obtaining part envelope and automatically loading part material information based on processing methods and relying on the coordinate system created by the part surface. It is applicable to sheet metal, machined, and composite material parts in single or module-based batch loading. In modular design, it can quickly load part and template information. Since sheet metal is subdivided into plate sheet metal and profile sheet metal in processing methods, and the material addition mode of composite materials and sewing parts is the same, that is, no measurement and calculation are required, and the material is directly called from the material library, this solution only describes the acquisition of material description information under four processing methods: machining, plate, profile, and composite materials. Summary of the Invention
[0007] This invention addresses the problems of large measurement errors and low automation in existing technologies by proposing a method and system for batch loading material descriptions based on the machining method and part surface to create a coordinate system. This method can adaptively create a high-precision coordinate system that fits the part surface according to the part machining method, thereby automatically calculating the part envelope dimensions that conform to engineering logic and batch loading material descriptions, significantly improving design efficiency and accuracy.
[0008] The technical solution of this invention is implemented as follows: In a first aspect, the present invention provides a batch material description loading method, which includes the following steps: In each part of the module, a coordinate system for the part surface is automatically created based on its machining method; The part envelope is obtained based on the coordinate system, and the length, width, and height information of the part are calculated. Material description information is automatically loaded based on the envelope information; The processing methods include machining, sheet metal processing, profile processing, and composite material processing.
[0009] As a further technical solution of the present invention: the coordinate system for creating the surface of the part is a rectangular coordinate system, and only two directions need to be determined during creation, and the third direction is automatically calculated.
[0010] As a further technical solution of the present invention: when the machining method is machining, the specific steps for creating the coordinate system include: Obtain the maximum and minimum values in the X, Y, and Z directions in the part's own coordinate system; Based on the type of extreme values, the coordinate system can be established in the following three cases: a) At least one of the three directions has an extreme value that is a surface; b) There is a face in only one direction, and at least one of the other directions is faceless; c) There are no faces in any of the three directions.
[0011] As a further technical solution of the present invention: In case a), the extreme value surface is extended into an infinite surface, and the distance between the extreme value and the infinite surface is measured to obtain the envelope size of the part.
[0012] As a further technical solution of the present invention: in case b), it includes: Identify the extreme surfaces and denote them as surface set A; In the centroid coordinate system of the surface, facet A and facet B are obtained by offset cutting; Based on whether the extreme value type after cutting is a line or a point, construct a coordinate system and calculate the envelope size by projection.
[0013] As a further technical solution of the present invention: in case c), it includes: Obtain the coordinate system of the part's center of gravity; Extract the surface of the part and intersect it with the coordinate system direction to obtain the extreme points; Construct a "2-line coordinate system" based on the angle between the normals at the extreme points, and recalculate the envelope size by projecting the extreme values.
[0014] As a further technical solution of the present invention: when the processing method is a sheet metal, it includes: Automatically unfolds sheet metal parts; Use the coordinate system establishment method for machined parts to perform measurement calculations; After the calculation is completed, the part will be automatically folded back to its original state.
[0015] As a further technical solution of the present invention: when the processing method is a profile, it includes: Extract the surface of the part and calculate the length A by taking the extreme value along the major axis of the centroid coordinate system; Cut the surface of the part along the YOZ plane and calculate the segment lengths B and C respectively; By determining whether B+CA≤5mm holds true, we decide whether to continue segmenting until the condition is met, and then call the machining method to calculate the total length.
[0016] As a further technical solution of the present invention: when the processing method is a composite material, the material information in the material library is directly called for loading.
[0017] Secondly, the present invention provides a material description batch loading system for implementing the above method, comprising: The coordinate system creation module is used to automatically create a coordinate system based on the part's machining method and surface features. An envelope calculation module is used to calculate the envelope dimensions of the part based on the coordinate system. The material loading module is used to automatically load material description information based on the envelope size. The system is applicable to four processing methods: machining, sheet metal, profiles, and composite materials.
[0018] Compared with the prior art, the beneficial effects of the present invention are as follows: 1) Automatically create a coordinate system in the part geometry set based on the part machining method; 2) The created coordinate system relies on the part surface, which can maximize the consistency between the part envelope and the part surface, conforming to the process and logic of manually loading material description; 3) The part envelope is automatically calculated based on this coordinate system; 4) Applicable to loading of materials such as machined, sheet metal, and composite materials; 5) When machining, establish a coordinate system based on the surface of the part, and be as accurate as possible; 6) When working with sheet metal, the system automatically measures and calculates the sheet metal after it is unfolded, which is quite accurate; 7) When dealing with profile parts, comparing and dividing the parts along their long axis provides greater accuracy; 8) When the part is made of composite material, apply the load directly; 9) After the measurement and calculation are completed, the steps are automatically deleted without affecting the part geometry or geometric set, i.e., without changing the state of the part. 10) It can automatically add material description information to all parts in a module, either based on a single part or based on a module; 11) This allows designers to focus more on design rather than loading generic information.
[0019] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description
[0020] Figure 1 This is a schematic diagram of the model structure tree of the module and the material description information to be loaded in an embodiment of the present invention.
[0021] Figure 2 This is a flowchart illustrating the automatic loading of material descriptions for machined parts in an embodiment of the present invention.
[0022] Figure 3 This is a flowchart illustrating the automatic loading of material descriptions for sheet metal parts in an embodiment of the present invention.
[0023] Figure 4 This is a flowchart illustrating the automatic loading of material descriptions for profile components in an embodiment of the present invention.
[0024] Figure 5 This is a flowchart illustrating the automatic loading of composite material descriptions in an embodiment of the present invention.
[0025] Explanation of the numbering in the diagram: 1: Model structure tree; 2: Material description; 3: Processing method; 4: Material specifications; 5: Fabric dimensions. Detailed Implementation
[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the present invention... All other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.
[0027] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.
[0028] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited from each other.
[0029] The following is in conjunction with the appendix Figure 1-5 The embodiments of the present invention will be described in detail below.
[0030] Example 1: Automatic loading of material descriptions for machined parts See Figure 2 Taking machined parts as an example, the automatic loading process for their material descriptions is as follows: S11: Loop to a part under model structure tree 1, and select "machining" as its processing method 3 through the interactive interface.
[0031] S12: Enter the coordinate system creation and measurement process.
[0032] A101: In the part's own coordinate system, use CATIA's hybridShapeFactory.AddNewExtremum method to obtain the six extreme values of the part's geometry in the X, Y, and Z directions.
[0033] A102: Use the GetGeometricalFeatureType method to determine the type of extrema. Assume this example belongs to case aa (at least one extremum in each of the three directions is a surface).
[0034] A103.1: Record the extreme surfaces and use the AddNewPlaneOffset method to extend these finite surfaces into infinite surfaces.
[0035] A103.2: Use the GetMeasurable and GetMinimumDistance methods to measure the distance between the extreme values in each direction and the corresponding infinite surface. This distance is the envelope dimension of the part's length, width, and height.
[0036] S13: Automatically load the calculated raw material size 5 (e.g., 150x100x50mm) and the material specification 4 (e.g., aluminum plate 7075) matched from the material library into the material description 2 attribute of the model structure tree 1.
[0037] Example 2: Automatic Loading of Material Descriptions for Sheet Metal Parts See Figure 3 Taking sheet metal parts as an example: S11: Select processing method 3 as "sheet material".
[0038] S12: B101: Ensure the part is created using the aerospace sheet metal module.
[0039] B102: Execute the CATIA.StartCommand "Fold / Unfold" command to unfold the part into a flat state.
[0040] B103: Call the machining part envelope measurement process (A101 to A103.2) described in Example 1 to measure the part in the unfolded state.
[0041] B104: Execute the fold command again to restore the part to its original state.
[0042] S13: Load the measured unfolded dimensions as the raw material dimension 5.
[0043] Example 3: Automatic Loading of Profile Material Description See Figure 4 Taking profile parts as an example: S11: Select processing method 3 as "profile".
[0044] S12: C101: Extract the surface of the part and obtain its centroid coordinate system, with the major axis in the X direction. Calculate the extreme projection difference in the X direction to obtain the initial length Aaa.
[0045] C102: Use the YOZ face to cut the part extraction surface, which is divided into two parts, A and B.
[0046] C103: Calculate the lengths Baa and Caa of parts A and B respectively.
[0047] C104: Calculate (Baa + Caa - Aaa). If the difference is greater than 5mm, repeat steps C102-C104 for parts A and B, recursively dividing them until the difference meets the requirement of ≤5mm.
[0048] C105: For each segment after final division, call the machining method to calculate its length and sum them to obtain the total length of the profile.
[0049] S13: Load the total length as the main dimension of the fabric size 5.
[0050] Example 4: Automatic Loading of Material Descriptions for Composite Components See Figure 5 Taking composite material parts as an example: S11: Select processing method 3 as "composite materials".
[0051] S12: D101: Since the blank size of composite materials (such as carbon fiber prepreg) is usually not determined by the geometric model, the system does not perform geometric measurements, but directly pops up the material library interface for designers to select.
[0052] S13: Load the selected material grade and specifications into the Material Specification 4 attribute.
[0053] Example 5 This invention discloses a method for batch loading material descriptions based on a coordinate system created by a processing method and the surface of a part. In each part of the module, a coordinate system is automatically created sequentially based on the processing method of the part and the surface of the part. Based on the coordinate system, the part envelope is then created, the length, width, and height information of the part are calculated, and the material description information is automatically loaded.
[0054] The processing methods include machining, sheet metal processing, profile processing, and composite material processing. When the processing method of a part is selected and determined, a coordinate system is automatically calculated and created based on CATIA VBA.
[0055] The coordinate system is a rectangular coordinate system. When creating it, only two directions of the coordinate system need to be obtained, and the third direction is automatically calculated.
[0056] When the machining method is machining, the coordinate system is established based on the surface of the part. Specifically, the coordinate system is established by taking the maximum and minimum values (a total of 6 extreme values) along the three directions of the part's own coordinate system, and considering three cases: a. There is a surface among the extreme values, and at least one extreme value of the part is a surface in each of the three directions; b. There is a surface at the extreme value of one of the three directions, but there is no surface at the extreme value of at least one of the other two directions.
[0057] c. None of the three directions have an extreme value of a surface.
[0058] When the part coordinate system is as described in section a, since the part coordinate system coincides with the normal of the part surface, the surface in the extreme value is expanded into an infinite surface, and the distance between the extreme value and the infinite surface is measured to obtain the envelope size of the part.
[0059] When the part coordinate system is as described in b, after identifying all surfaces in the extreme values, it is denoted as surface set A. In the barycentric coordinate system of each surface in surface set A (for ease of description, the X direction of the barycentric coordinate system of the extreme surface is denoted as the normal of the extreme surface), the XZ and XY surfaces in the barycentric coordinate system are offset by 0.5mm in each of the positive and negative directions. Using the cutting method, the extreme surfaces are offset by ±XY and ±XZ respectively, and then cut to form two small surfaces, denoted as small surface A and small surface B. The maximum and minimum values in the Y direction are taken for small surface A, and the maximum and minimum values in the Z direction are taken for small surface B, resulting in a total of 4 extreme values. At this time, there are two cases: I. If there is a line among the four extreme values, it means that the edge of the part coincides with the centroid coordinate system of the surface. Then, the maximum and minimum values of the part geometry in three directions are directly taken using the centroid coordinate system of the surface. At the same time, through projection calculation, the coordinates of the extreme points are projected onto the centroid coordinate system of the surface to determine the envelope size.
[0060] II. If there is no line among the four extreme values and there is only a point, then take the maximum and minimum values in the Z direction of surface A to form two straight lines. Take the maximum and minimum values in the Y direction of the two straight lines respectively. Then connect the two maximum values or the two minimum values to form the C curve of the part. The same applies to surface B. Use the C curve and the normal of the extreme value surface to construct the surface coordinate system.
[0061] When the part coordinate system is as described in c, the centroid coordinate system of the part geometry is obtained. The centroid coordinate system intersects with the shape extraction surface of the part geometry in the X, Y, and Z directions. The extreme values of the intersection directions are taken for the results after the intersection to obtain the points located on the surface of the part. Using the points and the shape extraction surface of the part geometry, the normals of the shape surface are established (theoretically 6). The angle between the straight lines is determined. Two lines with an angle of about 90 degrees are taken to establish the part geometric coordinate system, named "2-line coordinate system". The extreme values of the part are re-taken in the 2-line coordinate system. Through projection calculation, the coordinates of the extreme points are projected onto the 2-line coordinate system of the surface to determine the envelope size.
[0062] When the processing method is sheet metal, the geometry of the part must be established by the sheet metal module. The feature is that the part is automatically unfolded before measurement, the coordinate system establishment method of machining is called and the measurement calculation is performed, and the part state is restored by sheet metal folding after the measurement calculation is completed.
[0063] When the processing method is profiles, the coordinate system can be divided into two cases: aa. There is a surface among the extreme values, and at least one extreme value of the part is a surface in each of the three directions; bb. At least one direction in the extreme values has no surface.
[0064] When the coordinate system of the part surface is as described in section aa, since the coordinate system of the part coincides with the normal of the part surface, the method of establishing a coordinate system and performing measurement calculations as described in section a of the machined parts can be used.
[0065] When the coordinate system of the part surface is as described in bb, the part surface is extracted, and the centroid coordinate system of the part surface is used. At this time, the major axis of the centroid coordinate system is the X direction of the coordinate system. The maximum and minimum values in the X direction are taken along the centroid coordinate system, and the extreme difference in the X direction is calculated by projection, denoted as A. At the same time, the part surface is cut along the Y0Z plane to obtain two segments of the part surface, denoted as m segments and n segments. The centroid coordinate systems of m segments and n segments are taken respectively. At the same time, the extreme values in the X direction of their respective centroid coordinate systems are taken, and the extreme difference in the X direction is calculated by projection, denoted as B and C respectively. B+CA<=5mm is used as the length judgment criterion. If it is not satisfied, the m and n segments of the part surface are repeatedly divided, and the difference is calculated with the total length obtained by the previous step, until the requirement of less than or equal to 5mm is met. At this time, the method of establishing the coordinate system by machining is called to calculate the length of each segment of the part surface in the last step and sum them up, and output to the model structure tree.
[0066] When the processing method is composite materials, you can directly select materials from the material library.
[0067] Example 6 Referring to the attached figures, this application provides a method for batch loading material description 2 based on a coordinate system created from the processing method and the surface of the part. For ease of description, four parts are set in the module of the model structure tree 1, and the processing methods 3 are machining, sheet metal, profile, and composite material, respectively. When loading the material specifications 4 and the raw material size 5 in the material description 2, the method specifically includes steps S11, S12, and S13.
[0068] S11 Select Processing Method Using a loop, loop to a certain part under model structure tree 1, and determine the processing method by interactive selection. a) When the interactively selected processing method is machining, the step starts from A101. b) When the interactively selected processing method is sheet metal, the step starts from B101. c) When the interactively selected processing method is profile, the step starts from C101. d) When the interactively selected processing method is composite material, the step starts from D101.
[0069] S12 establishes a coordinate system based on the surface of the part and automatically measures and calculates based on the coordinate system.
[0070] a) The selected processing method is machining: A101 takes the maximum and minimum values of the part geometry in the X, Y, and Z directions in the part's own coordinate system and uses the AddNewExtremum method of hybridShapeFactory to obtain 6 extreme values.
[0071] A102 uses the GetGeometricalFeatureType method of hybridShapeFactory to determine the type of extrema, mainly point, line, and surface. It is divided into three cases: aa) At least one of the three directions X, Y, and Z is a surface, and the steps start from A103.1; bb) There is a surface in one of the three directions X, Y, and Z, but at least one of the other two directions does not have a surface, and the steps start from A103.11; cc) There is no surface in the three directions X, Y, and Z, and the steps start from A103.111.
[0072] aa) There is at least one extreme value in each of the three directions X, Y, and Z.
[0073] A103.1 records the extreme values in the X, Y, and Z directions in sequence into hybridShapePlaneOffset(1 To 6). At the same time, when the extreme value is a surface, the AddNewPlaneOffset method is used to expand the extreme surface (finite surface) into an infinite surface (note that if it is not expanded, it may cause measurement errors).
[0074] In A103.2, the coordinate system of the part surface is the same as the normal of the extended infinite surface. Using the GetMeasurable and GetMinimumDistance methods, the distance between the extreme values of the X, Y, and Z directions and the infinite surface is obtained, which is the cube envelope size.
[0075] bb) There is a face in one of the three directions X, Y, and Z, but at least one of the other two directions does not have a face.
[0076] A103.11 Since most of the surfaces of the parts are irregular, such as those containing rounded corners, the general idea is to use a cutting method to cut off the irregular parts of the surface in the centroid coordinate system of the surface. Since the normal of the surface is one direction of the coordinate system, the extreme values of the two directions are taken for the cut surface. If the extreme value is a straight line, a coordinate system is created based on the straight line. If it is a point, a coordinate system is established using three points.
[0077] A103.12 uses GetCOG to obtain the centroid coordinate system of the surface, uses the AddNewPointCoord method to establish the centroid point, and uses the GetPrincipalAxes method to establish the centroid coordinate system at the centroid point of the plane. At this time, the normal of the surface in the centroid coordinate system is the normal of the surface. Assuming that the normal of the surface is the X direction, the AddNewPlaneOffset method is used to offset the XZ surface and the XY surface by ±0.5mm each. After offsetting, the extreme surface is cut.
[0078] A103.13, after offsetting the extreme surface using ±XY and ±XZ respectively, it is cut to form two small surfaces, denoted as surface A and surface B. Using the AddNewExtremum method, the maximum and minimum values in the Y direction are taken for surface A, and the maximum and minimum values in the Z direction are taken for surface B, resulting in a total of 4 extreme values. At this point, there are two cases: if there is a line in the extreme value, the extreme value is directly measured using the centroid coordinate system just established; if there is a point, the maximum and minimum values in the Z direction and the maximum value in the Y direction are taken for the cut surface respectively, and a coordinate system "surface coordinate system" is established.
[0079] A103.14 Based on the surface coordinate system, take the extreme points of the volume and perform projection calculations in the coordinate system.
[0080] There is no face in the X, Y, and Z directions.
[0081] A103.111 Establish a centroid coordinate system at the centroid point of the part.
[0082] A103.112 uses the AddNewExtract method to extract the part geometry, uses the AddNewIntersection method to make the three directions of the barycentric coordinate system intersect with the part surface, and uses the AddNewExtremum method to take the extreme values of the intersection in the barycentric coordinate system, converting it into 6 points.
[0083] A103.113 uses the AddNewLineNormal method to obtain the normals of the part's shape at 6 points.
[0084] A103.114 uses a nested loop and GetAngleBetween to determine the intersection of the six normals.
[0085] A103.115 Using the two intersecting straight lines, a coordinate system is established using the catAxisSystemAxisByCoordinates method, and named "Part Surface Coordinate System".
[0086] A103.116 Use this coordinate system to establish the extreme values of the part and perform projection calculations.
[0087] b) The selected processing method is sheet metal: B101 was modeled using an aerospace sheet metal module.
[0088] B102 calls CATIA.StartCommand "Fold / Unfold" to unfold the part.
[0089] B103 calls the envelope measurement process for machined parts.
[0090] B104 calls CATIA.StartCommand "Fold / Unfold" to fold the part.
[0091] c) The selected processing method is profile: Since the profile part C101 is characterized by a slender structure, and the X direction of the part's centroid coordinate system is the long axis direction of the profile, the AddNewExtract method is used to extract the surface of the part, and the maximum and minimum values are taken along the X direction of the part's centroid coordinate system. The length of the part is calculated through projection calculation and denoted as Aaa.
[0092] C102 uses the YOZ plane, the centroid coordinate system of the part surface, to cut the extraction surface of the part into two parts, denoted as part A and part B.
[0093] C103 takes the centroid coordinate system of parts A and B and calculates the lengths Baa and Caa respectively.
[0094] Calculate Baa + Caa - Aaa using C104. Repeat the above operation until the difference is less than 5 mm.
[0095] C105 calls the step in A103 on the last result to determine the final part length.
[0096] d) The selected processing method is composite materials: Based on the characteristics of composite materials, D101 allows users to directly select materials from the material library interactively.
[0097] S13 loads the results into the model structure tree.
[0098] Thus, the objective of this invention has been achieved.
[0099] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A batch material description loading method, characterized in that, Includes the following steps: In each part of the module, a coordinate system for the part surface is automatically created based on its machining method; The part envelope is obtained based on the coordinate system, and the length, width, and height information of the part are calculated. Material description information is automatically loaded based on the envelope information; The processing methods include machining, sheet metal processing, profile processing, and composite material processing.
2. The batch material description loading method according to claim 1, characterized in that, The coordinate system for creating the part surface is a rectangular coordinate system. Only two directions need to be determined during creation, and the third direction is automatically calculated.
3. The batch material description loading method according to claim 1, characterized in that, When the machining method is machining, the specific steps for creating a coordinate system include: Obtain the maximum and minimum values in the X, Y, and Z directions in the part's own coordinate system; Based on the type of extreme values, the coordinate system can be established in the following three cases: a) At least one of the three directions has an extreme value that is a surface; b) There is a face in only one direction, and at least one of the other directions is faceless; c) There are no faces in any of the three directions.
4. The batch material description loading method according to claim 3, characterized in that, In case a), the extreme surface is extended to an infinite surface, and the distance between the extreme value and the infinite surface is measured to obtain the part envelope size.
5. The batch material description loading method according to claim 3, characterized in that, In case b), the following are included: Identify the extreme surfaces and denote them as surface set A; In the centroid coordinate system of the surface, facet A and facet B are obtained by offset cutting; Based on whether the extreme value type after cutting is a line or a point, construct a coordinate system and calculate the envelope size by projection.
6. The batch material description loading method according to claim 3, characterized in that, In case c), the following are included: Obtain the coordinate system of the part's center of gravity; Extract the surface of the part and intersect it with the coordinate system direction to obtain the extreme points; Construct a "2-line coordinate system" based on the angle between the normals at the extreme points, and recalculate the envelope size by projecting the extreme values.
7. The batch material description loading method according to claim 1, characterized in that, When the processing method involves sheet metal, it includes: Automatic unfolding of sheet metal parts; Use the coordinate system establishment method for machined parts to perform measurement calculations; After the calculation is completed, the part will be automatically folded back to its original state.
8. The batch material description loading method according to claim 1, characterized in that, When the processing method is profile, it includes: Extract the surface of the part and calculate the length A by taking the extreme value along the major axis of the centroid coordinate system; Cut the surface of the part along the YOZ plane and calculate the segment lengths B and C respectively; By determining whether B+CA≤5mm holds true, we decide whether to continue segmenting until the condition is met, and then call the machining method to calculate the total length.
9. The batch material description loading method according to claim 1, characterized in that, When the processing method is composite materials, the material information in the material library is directly called for loading.
10. A material description batch loading system for implementing the method of any one of claims 1-9, characterized in that, include: The coordinate system creation module is used to automatically create a coordinate system based on the part's machining method and surface features. An envelope calculation module is used to calculate the envelope dimensions of the part based on the coordinate system. The material loading module is used to automatically load material description information based on the envelope size; The system is applicable to four processing methods: machining, sheet metal, profiles, and composite materials.