Method for multi-laser build consistency verification for a flying additive manufacturing apparatus

Abstract

The application provides a multi-laser forming consistency verification method for a flight additive manufacturing device, and the method comprises: in a static typical position of a flight gantry, verifying the consistency of a metallographic structure and tensile test bar mechanical properties; in a dynamic typical position of the flight gantry, verifying the consistency of the metallographic structure and the tensile test bar mechanical properties; and in the dynamic typical position of the flight gantry, verifying the consistency of a feature size. According to the technical scheme of the application, the consistency of the metallographic structure, the tensile test bar mechanical properties and the feature size is verified in the static typical position of the flight gantry and the dynamic typical position of the flight gantry. The method is suitable for a flight additive manufacturing device with a more complex structure, realizes effective verification of the consistency of multi-laser forming of a super-large format, has high verification efficiency, and can meet the accuracy requirement of verification.

Description

Technical Field

[0001] This invention relates to the field of aero-additive manufacturing technology, and in particular to a method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment. Background Technology

[0002] Selective Laser Melting (SLM) is a novel manufacturing process that uses a high-energy laser beam to selectively melt pre-laid metal powder along a specific scanning path, accumulating layer by layer to form a part. Because this technology is unaffected by the complexity of the part and offers low manufacturing costs and short cycles, it can rapidly achieve high-performance, lightweight manufacturing of complex parts, and has therefore been widely used in aerospace, shipbuilding, and automotive industries. Traditional large-size SLM equipment uses a fixed galvanometer structure, resulting in a large single-beam coverage area and a lack of redundancy among multiple lasers. Further increasing the forming chamber size to achieve the forming of ultra-large parts presents challenges such as poor wind field uniformity, numerous laser overlap areas, poor equipment stability, and low forming efficiency, making it difficult to manufacture ultra-large parts.

[0003] Flying additive manufacturing equipment integrates a large number of scanning galvanometers onto a gantry, forming a flying optical module that moves sequentially across the forming area, achieving "printing while moving." Since the airflow range of this type of equipment only covers 1-2 rows of galvanometers, it only needs to consider the overlap between adjacent lasers and the overall overlap between different gantry lines. Furthermore, significantly increasing the number of lasers can reduce the coverage area of ​​a single beam and increase the overlap area between adjacent lasers, achieving redundant design and improving production efficiency. Therefore, it is the most promising technical approach to solving the problem of forming and manufacturing ultra-large-sized parts. However, compared to traditional SLM equipment, flying additive manufacturing equipment significantly increases the number of lasers, with typical equipment containing up to 52 lasers. The equipment structure is more complex, and the forming consistency of multiple lasers has a significant impact on the printing effect. Therefore, how to effectively verify the forming consistency of ultra-large-format multi-laser systems is a major technical challenge before flying additive manufacturing equipment can be put into practical use.

[0004] Before SLM equipment is put into actual product production, verifying the consistency of multi-laser forming is a common and necessary step. Multi-laser consistency determines the consistency of forming quality and microstructure properties of parts at different locations on the fabrication plane. For traditional fixed-mirror SLM equipment, the differences in microstructure and properties between different laser coverage areas are generally verified by printing metallographic blocks and tensile test bars at various fixed feature positions on the fabrication plane in a single pass. However, unlike traditional equipment, the laser beam areas of in-flight additive manufacturing equipment are diverse and randomly positioned. The traditional fixed-position single-pass printing verification method cannot comprehensively and accurately reflect the consistency of light output from different optical units during gantry flight. Summary of the Invention

[0005] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0006] This invention provides a method for verifying the consistency of multi-laser forming in an additive manufacturing equipment. The method includes: S1, verifying the consistency of metallographic structure and tensile test bar mechanical properties at typical static positions of the flying gantry; S2, verifying the consistency of metallographic structure and tensile test bar mechanical properties at typical dynamic positions of the flying gantry; and S3, verifying the consistency of feature size at typical dynamic positions of the flying gantry.

[0007] This invention provides a method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment. This method verifies the consistency of metallographic structure, tensile test bar mechanical properties, and feature dimensions at typical static and dynamic positions of the aero-gantry. This method is applicable to aero-additive manufacturing equipment with more complex structures, achieving effective verification of the consistency of ultra-large-format multi-laser forming. It boasts high verification efficiency and meets the accuracy requirements. Compared with existing technologies, this device solves the technical problem that traditional fixed-position single-print verification methods cannot accurately and effectively verify the consistency of multi-laser forming in aero-additive manufacturing equipment. Attached Figure Description

[0008] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0009] Figure 1 This diagram illustrates the arrangement of metallographic specimens and tensile test bars at typical static positions of a flying gantry according to a specific embodiment of the present invention.

[0010] Figure 2 A schematic diagram of the longitudinal section structure of an unfused metallographic specimen according to a specific embodiment of the present invention is shown;

[0011] Figure 3 This diagram illustrates the arrangement of metallographic specimens and tensile test bars at typical dynamic positions of a flying gantry according to a specific embodiment of the present invention.

[0012] Figure 4 This diagram illustrates the arrangement of dynamic typical position size verification features of a flying gantry according to a specific embodiment of the present invention.

[0013] Figure 5 A schematic diagram of the external structure of a dimension verification feature provided according to a specific embodiment of the present invention is shown. Detailed Implementation

[0014] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. 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 them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0015] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0016] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the accompanying drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values.

[0017] like Figures 1 to 5 As shown, according to a specific embodiment of the present invention, a method for verifying the consistency of multi-laser forming in an airborne additive manufacturing equipment is provided, the method comprising:

[0018] The consistency between the metallographic structure and the mechanical properties of the tensile test bar was verified at typical static positions of the flying gantry.

[0019] The consistency between the metallographic structure and the mechanical properties of the tensile test bar was verified at typical dynamic positions of the flying gantry.

[0020] Verify the consistency of feature dimensions at typical dynamic positions of the flying gantry.

[0021] This configuration provides a method for verifying the consistency of multi-laser forming in flight additive manufacturing equipment. The method verifies the consistency of metallographic structure, tensile test bar mechanical properties, and feature dimensions at typical static and dynamic positions of the flight gantry. This method is applicable to more complex flight additive manufacturing equipment, achieving effective verification of the consistency of ultra-large format multi-laser forming, with high verification efficiency and the ability to meet verification accuracy requirements.

[0022] Furthermore, in this invention, the consistency between the metallographic structure and the mechanical properties of the tensile test bar is first verified at a typical static position of the flying gantry.

[0023] Specifically, the following steps are included:

[0024] S11. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of the scanning galvanometers, determine the static typical position arrangement of the unfused characteristic metallographic specimens and tensile test bars.

[0025] For a dual-flying gantry structure, a flying additive manufacturing equipment with N scanning galvanometers arranged on a single gantry is used. The scanning area is selected as a fixed position in the middle of the coverage area of ​​each of the two flying gantry when they are working simultaneously. Within the coverage area of ​​each scanning galvanometer, a set of specimens consisting of M unfused characteristic metallographic blocks, M tensile horizontal bars, and M tensile vertical bars is arranged. A total of 2N sets of specimens are arranged in the entire scanning area. Each set of specimens can reflect the light emission characteristics of the corresponding optical unit in a static typical position. Subsequently, a corresponding single-beam laser is used for scanning, and the gantry does not move during the scanning process. M and N are both positive integers.

[0026] The number of unfused feature metallographic specimens, tensile crossbars, and tensile vertical bars in any set of specimens can be adjusted according to the forming area size of the in-flight additive manufacturing equipment, the coverage area size of each scanning galvanometer, and the size of the specimen.

[0027] In each group of specimens, the relative positions of the unfused metallographic blocks, tensile crossbars, and tensile vertical bars can be kept consistent to eliminate the differences caused by positional variations.

[0028] S12, set process parameters, keep the gantry stationary, and use the flying additive manufacturing equipment to print, and obtain the printed unfused feature metallographic block and tensile test bar corresponding to the static typical position.

[0029] In a specific embodiment of the present invention, in this step, the unfused metallographic specimen can be scanned layer by layer. By adjusting the printing program, the aero-additive manufacturing equipment can perform different powder-spreading printing on different spacer layers of the unfused metallographic specimen from bottom to top, thereby obtaining different degrees of unfused effect. The unfused metallographic specimen has several spacer layers distributed along its height direction, as shown in the attached figure. Figure 2 As shown, the spacers in the unfused metallographic specimen, from bottom to top, are spacer layer 1, spacer layer 2, spacer layer 3, and spacer layer 4. The above arrangement of spacers is only one example and is not limited to this.

[0030] S13, pre-process the printed unfused metallographic specimen and tensile test bar.

[0031] As a specific embodiment of the present invention, after the printing is completed by the flight additive manufacturing equipment, the substrate with unfused metallographic specimens and tensile test bars is taken out from the flight additive manufacturing equipment, and the surface metal powder is cleaned until there is no metal powder residue on the surface; the unfused metallographic specimens, tensile test bars and substrate are separated by wire cutting; the separated unfused metallographic specimens and tensile test bars are subjected to hot isostatic pressing and solution treatment.

[0032] S14. The metallographic structure of the pretreated unfused metallographic specimen was analyzed by sampling the longitudinal section. The tensile test bar was tested for room temperature tensile mechanical properties. The unfused microstructure and mechanical properties of specimens (including metallographic specimens and tensile test bars) with different layer thicknesses were compared with those of the specimens (including metallographic specimens and tensile test bars) obtained by laser forming of each optical unit. The consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical static positions was verified.

[0033] Furthermore, in this invention, after verifying the consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical static positions of the flying gantry, the consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical dynamic positions of the flying gantry is verified.

[0034] Specifically, the following steps are included:

[0035] S21. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the dynamic typical position arrangement of the unfused characteristic metallographic specimens and tensile test bars.

[0036] For a dual-flying gantry structure, a flying additive manufacturing equipment with N scanning galvanometers arranged on a single gantry has its scanning area selected as the entire forming area. At each end of the coverage area corresponding to each scanning galvanometer as it moves with the flying gantry, a first specimen group is arranged. Each first specimen group includes one unfused metallographic specimen, one tensile crossbar, and one tensile vertical bar. A total of 4N first specimen groups are arranged within the entire scanning area. At each end of the splicing line formed by the interlocking of any two adjacent scanning galvanometers within a single gantry, a second specimen group is arranged. Each second specimen group includes one unfused metallographic specimen and one tensile crossbar. A total of 4(N-1) second specimen groups are arranged within the entire scanning area. At each boundary line formed by the interlocking of any two opposing scanning galvanometers between the two gantry structures, a third specimen group is arranged. Each third specimen group includes one unfused metallographic specimen and one tensile crossbar. A total of N third specimen groups are arranged within the entire scanning area. Each laser beam scans the specimens within its respective coverage area. During the scanning process, the gantry moves normally, enabling each group of specimens to reflect the light output characteristics of the corresponding optical unit at a typical dynamic position.

[0037] S22, set process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain printed unfused metallographic specimens and tensile test bars corresponding to typical dynamic positions.

[0038] As a specific embodiment of the present invention, similar to S12, in step S22, the unfused characteristic metallographic specimen can also be scanned by a layer, which will not be described in detail here.

[0039] S23, pre-treatment is performed on the printed unfused metallographic specimen and tensile test bar.

[0040] The preprocessing steps in this step are similar to the preprocessing operations in step S13 above, and will not be described again here.

[0041] S24. The metallographic structure of the pretreated unfused metallographic specimen was analyzed by sampling the longitudinal section. The room temperature tensile mechanical properties of the horizontal and vertical bars were tested. The unfused microstructure and mechanical properties of the specimens with different layer thicknesses obtained by laser forming of each optical unit were compared to verify the consistency between the metallographic structure and the mechanical properties of the tensile specimens at typical dynamic locations.

[0042] Furthermore, in this invention, after verifying the consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical dynamic positions of the flying gantry, the consistency of the feature dimensions is verified at the typical dynamic positions of the flying gantry.

[0043] S31. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the dynamic typical position arrangement of the dimensional features.

[0044] For a dual-flying gantry structure, a flying additive manufacturing equipment with N scanning galvanometers arranged on a single gantry has the entire forming area selected for scanning. One dimensional feature is placed at each end of the coverage area corresponding to each scanning galvanometer as it moves with the flying gantry, for a total of 4N dimensional features. One dimensional feature is placed at each end of the splicing line formed by the splicing of any two adjacent scanning galvanometers within a single gantry, for a total of 4(N-1) dimensional features. One dimensional feature is placed at each end of the boundary line formed by the splicing of any two opposing scanning galvanometers between the two gantry structures, for a total of N dimensional features. A total of 9N-4 dimensional features are arranged within the entire scanning area. Each laser beam scans the features within its respective coverage area. During the scanning process, the gantry moves normally, allowing each feature to reflect the light output characteristics of the corresponding optical unit at a dynamic typical position.

[0045] As a specific embodiment of the present invention, the external structure of the dimensional feature is as shown in the attached figure. Figure 5 As shown, it is an equilateral triangular thin-walled feature cylinder with rounded corners. The specific dimensions can be determined according to the forming area size of the actual flight additive manufacturing equipment, the coverage range of the scanning galvanometer, and the dimensional verification requirements.

[0046] S32, set the process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain printed dimensional features corresponding to the dynamic typical position.

[0047] S33, preprocesses the printed dimensional features.

[0048] As a specific embodiment of the present invention, after the printing is completed by the flight additive manufacturing equipment, the substrate with dimensional features is removed from the flight additive manufacturing equipment, and the surface metal powder is cleaned until there is no metal powder residue on the surface; the dimensional features are separated from the substrate by wire cutting.

[0049] S34. Analyze the external dimensional characteristics of the pre-processed dimensional features, compare the external dimensional characteristics of the dimensional features obtained by laser forming of each optical unit, and verify the consistency of the dimensions of the dynamic typical position features.

[0050] As a specific embodiment of the present invention, a three-dimensional scanning device can be used to analyze the external dimensional features of the dimensional feature parts.

[0051] This invention provides a method for verifying the consistency of multi-laser forming, taking into account the structural characteristics of aero-additive manufacturing equipment. This method is designed for aero-additive manufacturing equipment with more complex structures, and achieves effective verification of the consistency of ultra-large-format multi-laser forming. It has high verification efficiency and can meet the verification accuracy requirements.

[0052] To gain a further understanding of the present invention, the following description is provided in conjunction with... Figures 1 to 5 The present invention provides a detailed description of the multi-laser forming consistency verification method for aero-additive manufacturing equipment.

[0053] In this embodiment, the multi-laser forming consistency verification method for flight additive manufacturing equipment specifically includes the following steps.

[0054] S1, verify the consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical static positions of the flying gantry:

[0055] S11. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the static typical position arrangement of the unfused feature metallographic specimens and tensile test bars in the model processing software.

[0056] Taking a flying additive manufacturing equipment with a forming area of ​​1.5m × 1.5m, 52 lasers, a dual flying gantry structure, and 26 scanning galvanometers arranged on each gantry as an example, the typical static position arrangement of its unfused feature metallographic specimens and tensile test bars is shown in the attached figure. Figure 1 As shown, the scanning area is a fixed position in the middle of the coverage area of ​​each of the two flying gantry when they are working simultaneously. Within the coverage area of ​​each scanning galvanometer, a set of specimens consisting of 3 unfused characteristic metallographic specimens, 3 tensile horizontal bars and 3 tensile vertical bars are arranged. A total of 52 sets of specimens are arranged in the entire scanning area, and each specimen is scanned individually using a corresponding single laser beam. The gantry does not move during the scanning process, so that each set of specimens can reflect the light output characteristics of the corresponding optical unit in a static typical position.

[0057] S12, Select appropriate process parameters, keep the gantry stationary, and use the corresponding flying additive manufacturing equipment to print the unfused feature metallographic specimen and tensile test bar blank corresponding to the static typical position.

[0058] The longitudinal section structure of the unfused metallographic specimen is shown in the attached figure. Figure 2 As shown, four spacer layers are evenly distributed at different heights on the test block, from bottom to top: spacer layer 1, spacer layer 2, spacer layer 3, and spacer layer 4. By adjusting the printing program, the equipment can continuously print one layer of powder without light at spacer layer 1, two layers at spacer layer 2, three layers at spacer layer 3, and four layers at spacer layer 4, thus obtaining different degrees of incomplete fusion effects. The above-mentioned different powder-spreading printing methods for different spacer layers are only one example, but are not limited to this.

[0059] S13, After printing, the substrate with unfused metallographic specimens and tensile test bar blanks is taken out from the flight additive manufacturing equipment, and the surface metal powder is cleaned until there is no metal powder residue on the surface; the unfused metallographic specimens, tensile test bar blanks and substrates are separated by wire cutting; the separated unfused metallographic specimens and tensile test bars are subjected to hot isostatic pressing and solution treatment.

[0060] S14. The metallographic structure of the pretreated unfused metallographic specimen was analyzed by sampling the longitudinal section. The room temperature tensile mechanical properties of the horizontal and vertical bars were tested. The unfused microstructure and mechanical properties of the specimens with different layer thicknesses obtained by laser forming of each optical unit were compared to verify the consistency between the metallographic structure at the static typical position and the mechanical properties of the tensile specimen.

[0061] S2, at typical dynamic positions of the flying gantry, verify the consistency between the metallographic structure and the mechanical properties of the tensile test specimens:

[0062] S21. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the dynamic typical position arrangement of the unfused feature metallographic specimens and tensile test bars in the model processing software.

[0063] Taking a flying additive manufacturing equipment with a forming area of ​​1.5m × 1.5m, 52 lasers, a dual flying gantry structure, and 26 scanning galvanometers arranged on each gantry as an example, the dynamic typical positional arrangement of its unfused feature metallographic specimens and tensile test bars is shown in the attached figure. Figure 3 As shown, the scanning area is the entire forming area. At each end of the coverage area corresponding to the movement of each scanning galvanometer with the flying gantry, a first specimen group is arranged. Each first specimen group includes one unfused metallographic specimen, one tensile crossbar, and one tensile vertical bar, totaling 104 first specimen groups across the entire scanning area. At each end of the splicing line formed by the interlocking of any two adjacent scanning galvanometers within a single gantry, a second specimen group is arranged. Each second specimen group includes one unfused metallographic specimen and one tensile crossbar, totaling 100 second specimen groups across the entire scanning area. Two opposing scanning galvanometers form a row between two gantry structures. At the boundary line formed by the interlocking of two scanning galvanometers in each row, a third specimen group is arranged. Each third specimen group includes one unfused metallographic specimen and one tensile crossbar, totaling 52 third specimen groups across the entire scanning area. Each laser beam scans the specimens within its respective coverage area. During the scanning process, the gantry moves normally, enabling each group of specimens to reflect the light output characteristics of the corresponding optical unit at a typical dynamic position.

[0064] S22, select appropriate process parameters, the gantry moves normally during the scanning process, and the corresponding flying additive manufacturing equipment is used to print the unfused feature metallographic specimen and tensile test bar blank corresponding to the dynamic typical position.

[0065] The longitudinal section structure of the unfused metallographic specimen is shown in the attached figure. Figure 2 As shown, four spacer layers are evenly distributed at different heights on the test block, from bottom to top: spacer layer 1, spacer layer 2, spacer layer 3, and spacer layer 4. By adjusting the printing program, the equipment can continuously print one layer of powder without light at spacer layer 1, two layers at spacer layer 2, three layers at spacer layer 3, and four layers at spacer layer 4, thus obtaining different degrees of incomplete fusion effects. The above-mentioned different powder-spreading printing methods for different spacer layers are only one example, but are not limited to this.

[0066] S23. After printing, the substrate with unfused metallographic specimens and tensile test bar blanks is removed from the flight additive manufacturing equipment. The surface metal powder is cleaned until there is no metal powder residue on the surface. The unfused metallographic specimens, tensile test bar blanks and substrates are separated by wire cutting. The separated unfused metallographic specimens and tensile test bars are subjected to hot isostatic pressing and solution treatment.

[0067] S24. The metallographic structure of the pretreated unfused metallographic specimen was analyzed by sampling the longitudinal section. The room temperature tensile mechanical properties of the horizontal and vertical bars were tested. The unfused microstructure and mechanical properties of the specimens with different layer thicknesses obtained by laser forming of each optical unit were compared to verify the consistency between the metallographic structure and the mechanical properties of the tensile specimens at typical dynamic locations.

[0068] S3, verify the consistency of feature dimensions at typical dynamic positions of the flying gantry:

[0069] S31. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the dynamic typical position arrangement of the dimensional features in the model processing software.

[0070] Taking a flying additive manufacturing equipment with a forming area of ​​1.5m × 1.5m, 52 lasers, a dual flying gantry structure, and 26 scanning galvanometers arranged on each gantry as an example, the typical dynamic positional arrangement of its dimensional features is shown in the attached figure. Figure 4As shown, the scanning area is the entire forming area. One dimensional feature is placed at each end of the coverage area corresponding to each scanning galvanometer as it moves with the flying gantry, for a total of 104 features. One dimensional feature is placed at each end of the splicing line formed by the splicing of any two adjacent scanning galvanometers within a single gantry, for a total of 100 features. Two opposing scanning galvanometers form a row between two gantry-gap structures, and one dimensional feature is placed at each boundary line formed by the splicing of two scanning galvanometers in each row, for a total of 52 features. Each laser beam scans the features within its respective coverage area. During the scanning process, the gantry moves normally, allowing each feature to reflect the light output characteristics of the corresponding optical unit at a dynamic typical position.

[0071] The external structure of the dimensional feature parts is shown in the attached figure. Figure 5 As shown, it is an equilateral triangular thin-walled feature cylinder with rounded corners. The specific dimensions are determined based on the forming area size of the actual flight additive manufacturing equipment, the coverage range of the scanning galvanometer, and the dimensional verification requirements.

[0072] S32, select appropriate process parameters, the gantry moves normally during the scanning process, and the corresponding flying additive manufacturing equipment is used to print the printed dimensional feature parts corresponding to the dynamic typical positions.

[0073] S33, after printing, remove the substrate with dimensional features from the in-flight additive manufacturing equipment, clean the surface metal powder until there is no metal powder residue on the surface; use wire cutting to separate the dimensional features from the substrate.

[0074] S34. The dimensional features of the pre-processed dimensional features are analyzed using a 3D scanning device. The dimensional features of the dimensional features obtained by laser forming of each optical unit are compared to verify the dimensional consistency of the dynamic typical position features.

[0075] In summary, this invention provides a method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment. This method verifies the consistency of metallographic structure, tensile test bar mechanical properties, and feature dimensions at typical static and dynamic positions of the aero-gantry. This method is applicable to aero-additive manufacturing equipment with more complex structures, achieving effective verification of the consistency of ultra-large-format multi-laser forming. It boasts high verification efficiency and meets the accuracy requirements. Compared with existing technologies, this device solves the technical problem that traditional fixed-position single-print verification methods cannot accurately and effectively verify the consistency of multi-laser forming in aero-additive manufacturing equipment.

[0076] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0077] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0078] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for verifying the consistency of multiple laser forming processes in aero-additive manufacturing equipment, characterized in that, The multi-laser forming consistency verification method includes: S1. Verify the consistency between metallographic structure and tensile test bar mechanical properties at typical static positions of the flying gantry. Specifically, based on the forming area size of the flying additive manufacturing equipment, the flying gantry structure, and the arrangement of scanning galvanometers, determine the arrangement of the unfused characteristic metallographic specimens and tensile test bars at typical static positions. This includes: for a dual-flying gantry structure, a flying additive manufacturing equipment with N scanning galvanometers arranged on a single gantry, selecting a fixed position in the middle of the coverage area of ​​each of the two flying gantry structures when they operate simultaneously. Within the coverage area of ​​each scanning galvanometer, arrange one set of specimens consisting of M unfused characteristic metallographic specimens, M tensile horizontal bars, and M tensile vertical bars. A total of 2N sets of specimens are arranged within the entire scanning area. Each set of specimens reflects the light emission characteristics of the corresponding optical unit at a typical static position; M and N are both positive integers. S2, verify the consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical dynamic positions of the flying gantry; specifically, based on the forming area size of the flying additive manufacturing equipment, the flying gantry structure, and the arrangement of scanning galvanometers, determine the arrangement of the typical dynamic positions of the unfused characteristic metallographic specimen and the tensile test bar. This includes: for a dual-flying gantry structure, for a flying additive manufacturing equipment with N scanning galvanometers arranged on a single gantry, the scanning area is selected as the entire forming area. At each end of the coverage area corresponding to the movement of each scanning galvanometer with the flying gantry, a first specimen group is arranged. The first specimen group includes one unfused characteristic metallographic specimen and one tensile test bar. A horizontal bar and a tensile vertical bar are used, with a total of 4N first specimen groups arranged throughout the entire scanning area. A second specimen group is arranged at each end of the splicing line formed by the splicing of any two adjacent scanning galvanometers within a single gantry. Each second specimen group includes one unfused metallographic specimen and one tensile horizontal bar, with a total of 4(N-1) second specimen groups arranged throughout the entire scanning area. A third specimen group is arranged at each end of the boundary line formed by the splicing of any two opposite scanning galvanometers between two gantry lines. Each third specimen group includes one unfused metallographic specimen and one tensile horizontal bar, with a total of N third specimen groups arranged throughout the entire scanning area; N is a positive integer. S3, verify the consistency of feature dimensions at typical dynamic positions of the flying gantry.

2. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 1, characterized in that, S1 specifically includes: S11. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of the scanning galvanometers, determine the static typical position arrangement of the unfused characteristic metallographic specimens and tensile test bars. S12, set process parameters, keep the gantry stationary, use the flying additive manufacturing equipment to print, and obtain the printed unfused feature metallographic specimen and tensile test bar corresponding to the static typical position; S13, pre-treatment of the unfused feature metallographic specimen and tensile test bar printed in S12; S14. The metallographic structure of the unfused metallographic specimen after S13 pretreatment was analyzed by sampling the longitudinal section. The tensile test bar was tested for room temperature tensile mechanical properties. The unfused microstructure and mechanical properties of specimens with different layer thicknesses obtained by laser forming of each optical unit were compared to verify the consistency between the metallographic structure and the mechanical properties of the tensile test bar at typical static positions.

3. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 2, characterized in that, S2 specifically includes: S21. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the dynamic typical position arrangement of the unfused characteristic metallographic specimens and tensile test bars. S22, set process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain printed unfused feature metallographic blocks and tensile test bars corresponding to dynamic typical positions; S23, pre-treatment of the unfused feature metallographic specimen and tensile test bar printed in S22; S24. The metallographic structure of the unfused metallographic specimen after S23 pretreatment was analyzed by sampling the longitudinal section. The room temperature tensile mechanical properties of the horizontal and vertical bars were tested. The unfused microstructure and mechanical properties of the specimens with different layer thicknesses obtained by laser forming of each optical unit were compared to verify the consistency between the metallographic structure and the mechanical properties of the tensile specimen at the dynamic typical position.

4. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 3, characterized in that, In S12 and S22, layer-by-layer scanning is performed on the unfused characteristic metallographic specimens.

5. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 3, characterized in that, In S13 and S23, the pretreatment includes: after printing in the air additive manufacturing equipment, removing the substrate with unfused metallographic specimens and tensile test bars from the air additive manufacturing equipment, cleaning the surface metal powder until no metal powder residue remains on the surface; separating the unfused metallographic specimens, tensile test bars and substrate using wire cutting; and performing hot isostatic pressing and solution treatment on the separated unfused metallographic specimens and tensile test bars.

6. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 1, characterized in that, S3 specifically includes: S31. Based on the forming area size of the flight additive manufacturing equipment, the flight gantry structure, and the arrangement of scanning galvanometers, determine the dynamic typical position arrangement of the dimensional features. S32, set process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain printed dimensional features corresponding to the dynamic typical position; S33, preprocessing the dimensional features printed in S32; S34 analyzes the external dimensional characteristics of the dimensional feature parts after preprocessing in S33, compares the external dimensional characteristics of the dimensional feature parts obtained by laser forming of each optical unit, and verifies the dimensional consistency of the dynamic typical position feature parts.

7. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 6, characterized in that, S31 specifically includes: for a dual-flying gantry structure, a flying additive manufacturing equipment with N scanning galvanometers arranged on a single gantry, the scanning area being the entire forming area, one dimensional feature at each end of the coverage area corresponding to each scanning galvanometer during the movement of the flying gantry, for a total of 4N dimensional features; one dimensional feature at each end of the splicing line formed by splicing any two adjacent scanning galvanometers within a single gantry, for a total of 4(N-1) dimensional features; one dimensional feature at each end of the boundary line formed by splicing any two opposite scanning galvanometers between the two gantry structures, for a total of N dimensional features; and a total of 9N-4 dimensional features arranged throughout the entire scanning area.

8. The method for verifying the consistency of multi-laser forming in aero-additive manufacturing equipment according to claim 6, characterized in that, S33 specifically includes: after printing in the air additive manufacturing equipment, removing the substrate with dimensional features from the air additive manufacturing equipment, cleaning the surface metal powder until no metal powder residue remains on the surface; and using wire cutting to separate the dimensional features from the substrate.

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