A method for expressing a spatial position of a part

Abstract

The application discloses a part space position expression method, first acquires a part set T and a structural part set V, obtains a bounding box set of the structural part set according to the structural part set, then performs dimension reduction on the bounding box set and the structural part set, obtains a dimension reduction plane, subsequently projects the part set, the structural part set and the bounding box set on the dimension reduction plane for clustering analysis, and finally outputs a part space position expression result according to a clustering analysis result; compared with the prior art, firstly, the application processes each part and structural part in a unified and standardized method, and outputs a corresponding space position expression result, on the one hand, the application avoids the difference of position expression results caused by personal experience and understanding difference, realizes the unity and standardization of space position expression, and improves the accuracy of position expression; on the other hand, the above method can be completed by a computer, which not only has a simple operation method, but also effectively improves the efficiency of space position output.

Description

Technical Field

[0001] This application relates to the field of testing equipment technology, specifically to a method for expressing the spatial position of a part. Background Technology

[0002] In the aerospace manufacturing industry, due to the numerous assembly processes and complex technology involved in component assembly, assembly outlines (AO) are typically used to guide the completion of production tasks. The assembly location of parts is one of the key areas that process engineers focus on in the AO.

[0003] Due to the complexity of the internal structure of aircraft fuselages, and the fact that the internal structures of different series and models of aircraft fuselages are almost entirely dissimilar, in the existing technology, during the AO (Automatic Animation) compilation stage, process engineers manually input the position information into a file after observing the 3D digital model. For a large number of parts with similar assembly processes and spatial positions, process engineers can only count the number of parts, grade, and other information, organize the content, and then manually input it into a file.

[0004] The above-mentioned operation method is not only inefficient, but also inaccurate in expressing the position of parts due to the lack of standardization in manual input and the different understandings of assembly positions by different process personnel. Summary of the Invention

[0005] The main purpose of this application is to provide a method for expressing the spatial position of a part, which aims to solve the defect of inaccurate expression of part position in the prior art.

[0006] This application achieves the above objectives through the following technical solutions:

[0007] A method for representing the spatial position of a part includes the following steps:

[0008] Obtain the set of parts T and the set of structural components V;

[0009] Obtain the bounding box set of the structural components based on the set of structural components;

[0010] Dimension reduction is performed based on the bounding box set and the structural component set to obtain the dimension reduction plane;

[0011] The set of parts, the set of structural components, and the set of bounding boxes are projected onto the dimension-reduced surface for cluster analysis.

[0012] The spatial location representation of the parts is output based on the cluster analysis results.

[0013] Optionally, obtaining the bounding box set of the structural components based on the set of structural components includes the following steps:

[0014] The bounding boxes B1, B2, ..., B1 of each structural component in the structural component set are obtained using a computer in the aircraft's global coordinate system. t , where t represents the number of structural components;

[0015] From the enclosure box B i Select the first vertex and the second vertex from among the vertices, where the first vertex is the point with the smallest coordinates among all vertices, and the second vertex is the point with the largest coordinates among all vertices;

[0016] Calculate the bounding box size B based on the coordinates of the first vertex and the second vertex. i (a i b i c i ), where i represents the structural component number;

[0017] Repeat from the bounding box B i The process involves selecting the first and second vertices from each vertex until all bounding box dimensions are obtained. These bounding box dimensions are then aggregated to form a bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B...}. t (a t b t c t )}.

[0018] Optionally, the formula for calculating the bounding box size Bi (ai, bi, ci) is a i =|x i1 -x i2 |,b i =|y i1 -y i2 |,c i =|z i1 -z i2 |;where x i1 y i1 z i1 Let x be the coordinates of the first vertex. i2 y i2 z i2 The coordinates of the second vertex are given.

[0019] Optionally, dimensionality reduction is performed based on the bounding box set and the structural component set to obtain a dimensionality reduction plane, including the following steps:

[0020] According to the enclosing box size B i (a i b i c i Select the calibration structural component from the set of structural components;

[0021] Based on the bounding box set, a dimension reduction plane is selected from each face of the calibration structure in the three-dimensional direction.

[0022] Optionally, the calibration structural component satisfies L = max(a j ,b j ,c j S = min(a) j ,b j ,c j ),and Furthermore, the names of the calibrated structural components contain the target keywords; where a j b j c j These represent the dimensional parameters of the calibration structural components in each of the three dimensions, and j represents the number of the calibration structural component; the target keywords include beam, frame, and floor.

[0023] Optionally, in conjunction with the bounding box set, selecting a dimension-reducing plane from the planes of symmetry of the calibrated structure includes the following steps:

[0024] In the calibration structure, a symmetry plane is selected as an alternative dimension reduction plane from each of the three-dimensional planes.

[0025] Based on the set of bounding boxes, calculate the area of ​​each bounding box in each of the candidate dimension-reduced planes;

[0026] The dimensionality reduction plane is selected from among the candidate dimensionality reduction planes according to the dimensionality reduction plane selection formula; wherein the expression of the dimensionality reduction plane selection formula is: ∑S 0t >∑S 1t And ∑S 0t >∑S 2t , where 0 represents the number of the dimension reduction plane, 1 and 2 represent the numbers of the remaining candidate dimension reduction planes respectively, and t represents the number of the structural component.

[0027] Optionally, the set of parts, the set of structural components, and the set of bounding boxes are projected onto the reduced-dimensional surface for cluster analysis, including the following steps:

[0028] Retrieve the reduced-dimensional plane;

[0029] Project the three-dimensional center points of each part in the part set onto the reduced-dimensional plane to obtain the part projection coordinate set;

[0030] Project the three-dimensional center point of each structural component in the set of structural components onto the reduced-dimensional plane to obtain the set of projected coordinates of the structural components;

[0031] Project the first and second vertex coordinates of each bounding box onto the reduced-dimensional plane to obtain the bounding box vertex projection coordinate set.

[0032] Project each of the bounding box dimensions onto the dimension-reduced plane to obtain a set of bounding box dimension projections;

[0033] Several random initial center points are determined based on the dimensions of each component in the structural component set;

[0034] Calculate the initial distance between the projected coordinates of each part and each of the aforementioned random initial center points;

[0035] The parts are grouped according to the initial distance, and several calculation center points are obtained based on the grouping results.

[0036] Optionally, the number of random initial center points satisfies Where V q V represents a structural component whose dimension in the m direction is not less than its dimension in the n direction. p This represents a structural component whose dimension in the m-direction is smaller than its dimension in the n-direction, where m and n represent the analysis directions of the dimension reduction plane, and x represents the structural component V. q The number of components, y represents the structural component V. p The number of.

[0037] Optionally, the parts are grouped according to the initial distance, and several calculated center points are obtained based on the grouping results, including the following steps:

[0038] Retrieve the initial distances of any part;

[0039] The minimum value is extracted from each of the initial distances as the minimum initial distance of the part;

[0040] The parts are assigned to a set of random initial center points corresponding to the minimum initial distance;

[0041] Repeat the steps to retrieve the initial distances of any part until all parts are grouped.

[0042] Calculate the mean point of the projected coordinates of each part in the same set, and use the mean point as the calculation center point. Repeat the above calculation until all calculation center points are obtained.

[0043] Optionally, the spatial location representation of the parts can be output based on the cluster analysis results, including the following steps:

[0044] Retrieve any calculation center point and its associated part sample;

[0045] Search within the bounding box size projection set for the structural member closest to the calculated center point as a reference structural member;

[0046] The spatial position expression result is output using the reference structural component as the directional reference.

[0047] Repeat the steps of retrieving any calculation center point and its associated part sample until the spatial position representation of all parts is obtained.

[0048] Compared with the prior art, this application has the following beneficial effects:

[0049] This application first obtains a set of parts T and a set of structural components V. Based on the set of structural components, it obtains a set of bounding boxes for the structural components. Then, it performs dimensionality reduction on the set of bounding boxes and the set of structural components to obtain a dimensionality reduction plane. Subsequently, it projects the set of parts, the set of structural components, and the set of bounding boxes onto the dimensionality reduction plane for cluster analysis. Finally, it outputs the spatial location representation of the parts based on the cluster analysis results.

[0050] Solving for the position information of parts in three-dimensional space is quite difficult. This solution designs a dimensionality reduction method based on the external dimensions of the skeleton structure to reduce the three-dimensional space to two-dimensional space. Then, cluster analysis is performed on each part in the two-dimensional space to realize the spatial position expression of each part, which effectively reduces the complexity of expressing the spatial position information of parts.

[0051] Compared with existing technologies, this application firstly processes each part and structural component using a unified and standardized method and outputs the corresponding spatial position expression results. On the one hand, it avoids the differences in position expression results caused by differences in personal experience and understanding, realizes the unification and standardization of spatial position expression, and improves the accuracy of position expression. On the other hand, the above method can be completed by computer, which is not only simple to operate, but also effectively improves the efficiency of spatial position output. Attached Figure Description

[0052] Figure 1 This is a flowchart of a method for expressing the spatial position of a part provided in Embodiment 1 of this application.

[0053] The purpose, features, and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0054] 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 a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0055] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0056] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0057] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions. Taking "robot coordinate system and / or m" as an example, it includes the robot coordinate system solution, the m solution, or a solution where both the robot coordinate system and m are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0058] Example 1

[0059] Reference Figure 1 This embodiment, as an optional implementation of this application, discloses a method for expressing the spatial position of a part, including the following steps:

[0060] S1. Obtain the set of parts T and the set of structural components V;

[0061] Retrieve the 3D assembly model containing all parts and structural components, and obtain the part set T and the structural component set V from the 3D assembly model respectively;

[0062] It should be noted that structural components refer to the skeleton parts of a product, which are usually characterized by large size and many details. Parts, on the other hand, refer to small internal components such as clamps and nameplates that are not part of the skeleton structure; they are generally smaller in size and simpler in shape.

[0063] S2. Obtain the bounding box set of the structural components based on the set of structural components;

[0064] S21. Obtain the bounding boxes B1, B2, ..., B1, B2, ..., B2 of each structural component in the structural component set in the aircraft global coordinate system using a computer. t , where t represents the number of structural components;

[0065] Using the API interface of the CAD software, obtain the bounding boxes B1, B2, ..., B of each structural component in the set of structural components in the aircraft global coordinate system. t , where t represents the number of structural components;

[0066] S22, from the surrounding box B i Select the first vertex and the second vertex from among the vertices, where the first vertex is the point with the smallest coordinates among all vertices, and the second vertex is the point with the largest coordinates among all vertices;

[0067] From each of the aforementioned bounding boxes B1, B2, ..., B t Choose any bounding box B i , where i represents the number of the structural component;

[0068] From the enclosure box B i Select the first vertex and the second vertex from among the vertices, where the first vertex is the point with the smallest coordinates among all vertices, and the second vertex is the point with the largest coordinates among all vertices;

[0069] S23. Calculate the bounding box size B based on the coordinates of the first vertex and the second vertex. i (a i b i c i ), where i represents the structural component number;

[0070] Obtain the coordinates (x, y) of the first vertex respectively i1 y i1 z i1 ) and the coordinates of the second vertex (x) i2 y i2 z i2 Substitute the above coordinates into the bounding box size B. i (a i b i c i The bounding box size B is calculated using the formula. i (a i b i c i The expression for the calculation formula is a. i =|x i1 -x i2 |,bi =|y i1 -y i2 |,c i =|z i1 -z i2 |

[0071] S24, Repeat from the bounding box B i The process involves selecting the first and second vertices from each vertex until all bounding box dimensions are obtained. These bounding box dimensions are then aggregated to form a bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B...}. t (a t b t c t )}.

[0072] Repeat step S22 until all bounding box dimensions are obtained. Collect all bounding box dimensions and establish a bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B...}. t (a t b t c t )}.

[0073] S3. Perform dimensionality reduction based on the bounding box set and the structural component set to obtain the dimensionality reduction plane;

[0074] S31, according to the enclosing box size B i (a i b i c i Select the calibration structural component from the set of structural components;

[0075] Retrieve the bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B...} obtained in step S24. t (a t b t c t Select the bounding box size B of any structural component. i (a i b i c i Substitute its parameters into the judgment formula. If it satisfies the judgment formula, obtain the name of each structural component and determine whether its name contains the target keyword. If the above conditions are met, the structural component is selected as the calibration structural component; otherwise, it cannot be used as the calibration structural component.

[0076] Repeat the above steps, substituting the bounding box dimensions of each structural component into the determination formula for determination, thereby obtaining all calibrated structural components;

[0077] The formula for determining the outcome is L = max(a) j ,b j ,c j S = min(a) j ,b j ,c j ),and Where a j b j c j These represent the dimensional parameters of the calibrated structural components in each of the three dimensions; the target keywords include beam, frame, and floor.

[0078] To effectively represent the spatial position of parts, frame, beam, and base plate structural components that support the main structure should be selected as references. These structural components are usually distributed along the length of the aircraft. Connecting frames and these structural components are the most instructive references for the position of parts. The maximum / minimum size of these structural components is usually less than 0.4.

[0079] S32. Combining the bounding box set, select a dimension reduction plane from each face of the calibration structure in the three-dimensional direction.

[0080] S321. Select a symmetry plane as an alternative dimension reduction plane from each of the three-dimensional planes of the calibration structural component.

[0081] Based on common knowledge, in a three-dimensional coordinate system, only the XY, XZ, and YZ planes can be selected as candidate dimensionality reduction planes.

[0082] Because aircraft structures are axially symmetrical, the YZ plane is rarely used as a cross-section for part placement planning. Therefore, there are two options for dimensionality reduction analysis: the XZ plane and the XY plane. Of course, it should be noted that if the YZ plane is also a symmetry plane of the aircraft structure, it can also be used as an alternative dimensionality reduction plane. If the XZ plane and XY plane are not symmetry planes of the aircraft structure, they cannot be used as alternative dimensionality reduction planes.

[0083] S322. Calculate the area of ​​each bounding box in each of the candidate dimension-reduced planes according to the bounding box set.

[0084] Retrieve the bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B} t (a t b t c t )}, calculate the projected area of ​​each bounding box in the selected candidate dimension-reduced plane, that is, for bounding box B i (a i b i c iFor example, its projected area in the XZ plane is a. i *c i The projected area in the XY plane is a i *b i It should be noted that if the YZ plane is also considered as an alternative dimension reduction plane, then its projected area is b. i *c i ;

[0085] The same method was used to calculate the projected area of ​​each bounding box in the candidate dimension-reduced plane;

[0086] S323. Select a dimension reduction plane from among the candidate dimension reduction planes according to the dimension reduction plane selection formula; wherein the expression of the dimension reduction plane selection formula is: ∑S 0t >∑S 1t And ∑S 0t >∑S 2t , where 0 represents the number of the dimension reduction plane, 1 and 2 represent the numbers of the remaining candidate dimension reduction planes respectively, and t represents the number of the structural component;

[0087] Based on the projected area of ​​each bounding box in the candidate dimension reduction plane calculated in step S322, the sum of all projected areas in each candidate dimension reduction plane is calculated; at the same time, a dimension reduction plane is selected from each candidate dimension reduction plane according to the dimension reduction plane selection formula.

[0088] The expression for the formula for selecting the dimensionality reduction plane is: ∑S 0t >∑S 1t And ∑S 0t >∑S 2t , where 0 represents the number of the dimension reduction plane, 1 and 2 represent the numbers of the remaining candidate dimension reduction planes respectively, and t represents the number of the structural component;

[0089] That is, the candidate dimensionality reduction plane that satisfies the above formula is the dimensionality reduction plane. If there are only two candidate dimensionality reduction planes, the one with the larger sum of areas is selected as the dimensionality reduction plane. If there are three candidate dimensionality reduction planes, the one with the largest sum of areas is selected as the dimensionality reduction plane.

[0090] S4. Project the set of parts, the set of structural components, and the set of bounding boxes onto the reduced-dimensional surface and perform cluster analysis.

[0091] Cluster analysis is an unsupervised method that divides samples in a dataset into multiple classes, making samples in the same class similar to each other. In the technical solution described in this application, cluster analysis can obtain sample points corresponding to multiple parts that are close to each other. These sample points enhance the generalization ability of spatial location representation and effectively reduce the complexity of representing the spatial location of parts.

[0092] S41. Retrieve the dimension reduction plane;

[0093] S42. Project the three-dimensional center points of each part in the part set onto the reduced-dimensional plane to obtain the part projection coordinate set;

[0094] The coordinates of the three-dimensional center point of each part are calculated by computer, and then each three-dimensional center point is projected onto the dimension-reduced plane.

[0095] If the coordinates of the three-dimensional center point of a certain part are calculated to be (x1, y1, z1), and the selected dimension reduction plane is the XY plane, then the projected coordinates are (x1, y1).

[0096] Calculate the three-dimensional center of each part separately and project them all to obtain the set of projected coordinates of the parts;

[0097] S43. Project the three-dimensional center point of each structural component in the set of structural components onto the reduced-dimensional plane to obtain the set of projected coordinates of the structural components;

[0098] Perform projection according to the method described in step S42 to obtain the set of projection coordinates of the structural components;

[0099] S44. Project the first and second vertex coordinates of each bounding box onto the reduced-dimensional plane to obtain the set of bounding box vertex projection coordinates.

[0100] Perform projection according to the method described in step S42 to obtain the set of bounding box vertex projection coordinates;

[0101] S45. Project each of the bounding box dimensions onto the dimension-reduced plane to obtain a set of bounding box dimension projections;

[0102] The bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B...} obtained in step S24 t (a t b t c t Choose any one of the following box sizes, B: i (a i b i c i Assuming the selected dimension reduction plane is the XY plane, the size of the projected bounding box is (a i b i );

[0103] By repeating the above steps to obtain the bounding box dimensions of all projections, a set of bounding box dimension projections can be established.

[0104] S46. Determine several random initial center points based on the dimensions of each component in the structural component set;

[0105] Retrieve the bounding box size projection set obtained in step S45, and analyze the size parameters in the two analysis directions of the dimension reduction plane (e.g., if the XY plane is selected, then the X and Y directions are its two analysis directions); classify each structural component according to the size parameters and count the number of each type of structural component, and finally calculate the number of random initial center points;

[0106] The number of random initial center points satisfies Where V q V represents a structural component whose dimension in the m direction is not less than its dimension in the n direction. p This represents a structural component whose dimension in the m-direction is smaller than its dimension in the n-direction, where m and n represent the analysis directions of the dimension reduction plane, and x represents the structural component V. q The number of components, y represents the structural component V. p The number of;

[0107] S47. Calculate the initial distance between the projected coordinates of each part and each of the random initial center points;

[0108] Obtain the set of part projection coordinates calculated in step S42, and generate a corresponding number of random initial center points by computer based on the number of random initial center points calculated in step S46.

[0109] Based on the distance calculation formula, the initial distance between the projected coordinates of each part and each of the random initial center points is calculated.

[0110] It should be noted that if the parts involved are D1, D2, ..., D n The initial random center points are E1, E2, ..., E k The calculated part D1 involves initial distances including D1E1, D1E2, ..., D1E k Similarly, the initial distances of other parts can be obtained; where D1E1 represents the initial distance between part D1 and the random initial center point E1;

[0111] S48. Group the parts according to the initial distance, and obtain several calculation center points based on the grouping results;

[0112] S481. Retrieve the initial distances of any part;

[0113] S482. Extract the minimum value from each of the initial distances as the minimum initial distance of the part;

[0114] If retrieving part D1 involves initial distances D1E1, D1E2, ..., D1E k The minimum initial distance is selected from the above initial distances, such as D1E. kMinimum initial distance;

[0115] S483. Divide the parts into a set of random initial center points corresponding to the minimum initial distance, and calculate the mean point of the projected coordinates of each part in the same set as the new center point of the set.

[0116] The minimum initial distance of all parts can be obtained based on the division result in step S482. Based on the minimum initial distance, each part corresponding to the same random initial center point is divided into the same set, and the set also includes the random initial center point.

[0117] If the minimum initial distance is D1E k D2E2, D3E2, D4E k D5E3, ..., D n E k Then parts D1, D4, ..., D n and random initial center point E k They are grouped into the same set;

[0118] S484. Repeat the steps to retrieve the initial distances of any part until all parts are grouped.

[0119] S485. Calculate the mean point of the projected coordinates of each part in the same set, and use the mean point as the new calculation center point. Repeat the above calculation until the center point no longer changes.

[0120] The mean point of the projected coordinates of each part in the same set is calculated by computer, and the mean point is used as the calculation center point.

[0121] During assembly, parts are assembled onto structural components. It is necessary to pay attention to the spatial positional relationship between structural components and parts during assembly. This application uses cluster analysis technology to objectively and accurately construct the spatial positional relationship between structural components and parts, which is conducive to improving the accuracy of positional expression.

[0122] S5. Output the spatial location representation of the parts based on the cluster analysis results.

[0123] S51. Retrieve any calculation center point and its associated part sample;

[0124] S52. Search for the structural component closest to the calculated center point in the bounding box size projection set as a reference structural component;

[0125] Obtain the set of projected coordinates of the structural components calculated in step S43, and at the same time obtain each calculation center point calculated in step S485;

[0126] Calculate the distance between each structural component and each calculation center point, and select the structural component with the shortest distance from the center point as the reference structural component;

[0127] For example, for the calculation center point O1, the distances between each structural component and it are O1V1, O1V2, O1V3, ..., O1V1. r If structural component O1V3 is the smallest, then structural component V3 is selected as the reference structural component corresponding to the calculation center point O1; all parts in the same set as the calculation center point O1 use structural component V3 as the reference structure to output the spatial position expression result.

[0128] S53. Output the spatial position expression result using the reference structural component as the directional reference;

[0129] The general expression for spatial location is: part Di is located above / below / left / right of structural part Vi.

[0130] It should be noted that an aircraft coordinate system typically consists of three orthogonal axes, represented by the horizontal axis (X-axis), vertical axis (Y-axis), and vertical axis (Z-axis). Therefore, the general expression is: Part Di is located above / below / left / right / forward / backward of structural component Vi. The direction is determined by the components of the direction vector pointing from the structural component to the part on the coordinate axes, with the largest component used to describe the direction. The X-direction represents left / right, the Y-direction represents forward / backward, and the Z-direction represents up / down.

[0131] Based on the reduced-dimensional plane, the general formula is as follows: If the reduced-dimensional plane is the XY plane, then part Di is located in front of / back of / left of / right of structural component Vi, with the X direction representing left / right and the Y direction representing front / back. Similarly, if the reduced-dimensional plane is the YZ plane, part Di is located in front of / back of / above / below of structural component Vi, with the Y direction representing front / back and the Z direction representing up / down; if the reduced-dimensional plane is the XZ plane, part Di is located in the left of / right of / above / below of structural component Vi, with the X direction representing left / right and the Z direction representing up / down.

[0132] S54. Repeat the steps of retrieving any calculation center point and its corresponding part sample until the spatial position expression results of all parts are obtained.

[0133] Compared with existing technologies, this application firstly processes each part and structural component using a unified and standardized method and outputs the corresponding spatial position expression results. On the one hand, it avoids the differences in position expression results caused by differences in personal experience and understanding, realizes the unification and standardization of spatial position expression, and improves the accuracy of position expression. On the other hand, the above method can be completed by computer, which is not only simple to operate, but also effectively improves the efficiency of spatial position output.

[0134] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A method for expressing the spatial position of a part, characterized in that, Includes the following steps: Obtain the set of parts T and the set of structural components V; Obtain the bounding box set of the structural components based on the set of structural components; Dimensionality reduction is performed based on the bounding box set and the structural component set to obtain the dimensionality reduction plane; including the following steps: based on the bounding box size B i (a) i b i c i ), select a calibration structure from the set of structure components; combine the bounding box set, select a dimension-reducing plane from each face of the calibration structure in the three-dimensional direction; the calibration structure satisfies L = max(a j ,b j ,c j S = min(a) j ,b j ,c j ),and <0.4, and the name of the calibrated structural component contains the target keyword; where a j b j c j Let represent the dimensional parameters of the calibration structural component in each three-dimensional direction, and j represent the number of the calibration structural component; the target keywords include beam, frame, and floor; the step of selecting a dimension reduction plane from each face of the calibration structural component in each three-dimensional direction, based on the bounding box set, includes the following steps: selecting a symmetry plane as a candidate dimension reduction plane from each face of the calibration structural component in each three-dimensional direction; calculating the area of ​​each bounding box in each candidate dimension reduction plane according to the bounding box set; and selecting a dimension reduction plane from each candidate dimension reduction plane according to the dimension reduction plane selection formula; wherein the expression of the dimension reduction plane selection formula is: and , where 0 represents the number of the dimension reduction plane, 1 and 2 represent the numbers of the remaining candidate dimension reduction planes respectively, and t represents the number of the structural component; Cluster analysis is performed by projecting the set of parts, the set of structural components, and the set of bounding boxes onto the reduced-dimensional plane. This includes the following steps: retrieving the reduced-dimensional plane; projecting the 3D center points of each part in the set of parts onto the reduced-dimensional plane to obtain a set of projected coordinates for the parts; projecting the 3D center points of each structural component in the set of structural components onto the reduced-dimensional plane to obtain a set of projected coordinates for the structural components; projecting the 3D center points of the first and second vertices of each bounding box onto the reduced-dimensional plane to obtain a set of projected coordinates for the bounding box vertices; projecting the dimensions of each bounding box onto the reduced-dimensional plane to obtain a set of projected dimensions for the bounding box; determining several random initial center points based on the dimensions of each component in the set of structural components; calculating the initial distance between the projected coordinates of each part and each of the random initial center points; grouping the parts according to the initial distances and obtaining several calculated center points based on the grouping results; the number of random initial center points satisfies the following condition. V q V represents a structural component whose dimension in the m direction is not less than its dimension in the n direction. p This represents a structural component whose dimension in the m-direction is smaller than its dimension in the n-direction, where m and n represent the analysis directions of the dimension reduction plane, and x represents the structural component V. q The number of components, y represents the structural component V. p The number of; The spatial location representation of the parts is output based on the cluster analysis results, including the following steps: retrieve any calculation center point and its corresponding part sample; search for the structural component closest to the calculation center point in the bounding box size projection set as a reference structural component; output the spatial location representation result with the reference structural component as the directional reference; repeat the step of retrieving any calculation center point and its corresponding part sample until the spatial location representation results of all parts are obtained.

2. The method for expressing the spatial position of a part according to claim 1, characterized in that, Obtaining the bounding box set of structural components based on the set of structural components includes the following steps: The bounding boxes B1, B2, ..., B1 of each structural component in the structural component set are obtained using a computer in the aircraft's global coordinate system. t , where t represents the number of structural components; From the enclosure box B i Select the first vertex and the second vertex from among the vertices, where the first vertex is the point with the smallest coordinates among all vertices, and the second vertex is the point with the largest coordinates among all vertices; Calculate the bounding box size B based on the coordinates of the first vertex and the second vertex. i (a) i b i c i ), where i represents the structural component number; Repeat from the bounding box B i The process involves selecting the first and second vertices from each vertex until all bounding box dimensions are obtained. These bounding box dimensions are then aggregated to form a bounding box set {B1(a1, b1, c1), B2(a2, b2, c2), ..., B...}. t (a) t b t c t )}.

3. The method for expressing the spatial position of a part according to claim 2, characterized in that, The formula for calculating the bounding box size Bi (ai, bi, ci) is as follows: , , ;where x i1 y i1 z i1 Let x be the coordinate of the first vertex. i2 y i2 z i2 The coordinates of the second vertex are given.

4. The method for expressing the spatial position of a part according to claim 1, characterized in that, The process of grouping the parts according to the initial distance and obtaining several calculated center points based on the grouping results includes the following steps: Retrieve the initial distances of any part; The minimum value is extracted from each of the initial distances as the minimum initial distance of the part; The parts are assigned to a set of random initial center points corresponding to the minimum initial distance; Repeat the steps to retrieve the initial distances of any part until all parts are grouped. Calculate the mean point of the projected coordinates of each part in the same set, and use the mean point as the calculation center point. Repeat the above calculation until all calculation center points are obtained.

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