Multi-laser forming consistency verification method for flight additive manufacturing equipment

Abstract

The invention provides a multi-laser forming consistency verification method for flight additive manufacturing equipment, which comprises the following steps of: verifying the consistency of a metallographic structure and the mechanical property of a tensile test bar at a static typical position of a flight gantry; verifying the consistency of the metallographic structure and the mechanical property of the tensile test bar at the dynamic typical position of the flying gantry; and carrying out feature part size consistency verification at the dynamic typical position of the flying gantry. According to the technical scheme, the consistency verification of the metallographic structure, the tensile test bar mechanical property and the characteristic piece size is carried out according to the flying gantry static typical position and the flying gantry dynamic typical position. The method is suitable for flight additive manufacturing equipment with a more complex structure, effective verification of the ultra-large format multi-laser forming consistency is achieved, the verification efficiency is high, and the verification accuracy requirement can be met.

Description

Technical Field

[0001] The present invention relates to the technical field of in-flight additive manufacturing, and in particular to a multi-laser forming consistency verification method for in-flight additive manufacturing equipment. Background Art

[0002] Selective Laser Melting (SLM) is a new manufacturing process that uses a high-energy laser beam to selectively melt pre-laid metal powder according to a certain scanning path, and accumulates it layer by layer to achieve part forming. Since this technology is not affected by the complexity of the parts, has low manufacturing costs and short cycles, and can quickly achieve high-performance lightweight manufacturing of complex parts, it has been widely used in aerospace, shipbuilding, automotive and other fields. Traditional large-size SLM equipment uses a fixed galvanometer structure, a large single-light coverage area, and no redundant design between multiple lasers. If the size of the forming chamber is to be further increased to achieve the forming of oversized parts, it will face problems such as poor wind field uniformity, multiple laser overlap areas, poor equipment stability, and low forming efficiency, making it difficult to achieve the forming and manufacturing of oversized parts.

[0003] The flying additive manufacturing equipment integrates a large number of scanning galvanometers on the gantry and forms a flying optical module, which moves sequentially on the forming surface to achieve "printing while moving". Since the wind field range of this type of equipment only covers 1 to 2 rows of galvanometers, it is only necessary to consider the overlap of two adjacent lasers and the overall overlap between different gantries. In addition, a significant increase in the number of lasers can reduce the single light coverage area, increase the overlapping area between adjacent lasers, achieve redundant design, and improve production efficiency. Therefore, it is the most promising technical approach to solve the problem of forming and manufacturing of oversized parts. However, compared with traditional SLM equipment, the number of lasers in flying additive manufacturing equipment has increased significantly. The number of lasers in a typical equipment can be as high as 52, and the equipment structure is more complex. The forming consistency of multiple lasers has a significant impact on the printing effect. Therefore, how to effectively verify the consistency of ultra-large format multi-laser forming is the main technical problem faced by flying additive manufacturing equipment before it is put into practical use.

[0004] Before the SLM equipment is put into actual product production, it is a common and necessary step to verify the multi-laser forming consistency of the equipment. Multi-laser consistency determines the consistency of the forming quality and organizational performance of the parts at different positions on the format. For traditional SLM equipment with a fixed galvanometer structure, the organizational and performance differences between different laser coverage areas of the equipment are generally verified by printing metallographic test blocks and tensile test bars at each fixed characteristic position on the format. However, unlike traditional equipment, the laser light area of ​​the flying additive manufacturing equipment has the characteristics of multiple types and random positions. The traditional fixed-position single printing verification method is difficult to fully and accurately reflect the light consistency of different optical units during the gantry flight process. Summary of the invention

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

[0006] The present invention provides a multi-laser forming consistency verification method for a flying additive manufacturing device, the multi-laser forming consistency verification method comprising: S1, verifying the consistency of metallographic structure and mechanical properties of a tensile test rod at a typical static position of a flying gantry; S2, verifying the consistency of metallographic structure and mechanical properties of a tensile test rod at a typical dynamic position of the flying gantry; S3, verifying the consistency of characteristic part dimensions at a typical dynamic position of the flying gantry.

[0007] By applying the technical solution of the present invention, a method for verifying the consistency of multi-laser forming for flight additive manufacturing equipment is provided. The method verifies the consistency of metallographic structure, mechanical properties of tensile test bars and dimensions of characteristic parts for the static typical position and dynamic typical position of the flight gantry. The method is suitable for flight additive manufacturing equipment with more complex structures, and realizes effective verification of the consistency of ultra-large-format multi-laser forming. The verification efficiency is high and the verification accuracy requirements can be met. Compared with the prior art, the device can solve the technical problem that the traditional fixed-position single-print verification method in the prior art cannot accurately and effectively verify the consistency of multi-laser forming of flight additive manufacturing equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0009] Figure 1 A schematic diagram showing the arrangement of metallographic test blocks and tensile test bars in typical static positions of a flying gantry provided according to a specific embodiment of the present invention is shown;

[0010] Figure 2 It shows a schematic diagram of the longitudinal cross-section structure of an unfused characteristic metallographic test block provided according to a specific embodiment of the present invention;

[0011] Figure 3 A schematic diagram showing the arrangement of metallographic test blocks and tensile test bars in typical dynamic positions of a flying gantry provided according to a specific embodiment of the present invention is shown;

[0012] Figure 4 A schematic diagram showing an arrangement of characteristic parts for dynamic typical position and dimension verification of a flying gantry according to a specific embodiment of the present invention is shown;

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

[0014] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0015] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0016] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to actual proportional relationships. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. 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 multi-laser forming consistency verification method for a flight additive manufacturing device is provided, the method comprising:

[0018] Verify the consistency of metallographic structure and mechanical properties of tensile test bars at typical static positions of the flight gantry;

[0019] Verify the consistency of metallographic structure and mechanical properties of tensile test bars at typical dynamic positions of the flight gantry;

[0020] Verify the consistency of characteristic parts dimensions at typical dynamic positions of the flight gantry.

[0021] By applying this configuration, a multi-laser forming consistency verification method for flight additive manufacturing equipment is provided. This method verifies the consistency of metallographic structure, mechanical properties of tensile test bars and characteristic part dimensions for the typical static and dynamic positions of the flight gantry. This method is suitable for flight additive manufacturing equipment with more complex structures, and realizes effective verification of ultra-large-scale multi-laser forming consistency, with high verification efficiency and meeting the verification accuracy requirements.

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

[0023] The specific steps include:

[0024] S11, determine the static typical position arrangement of the unfused characteristic metallographic test block and the tensile test bar according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement.

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

[0026] The number of unfused feature metallographic test blocks, tensile horizontal bars, and tensile vertical bars in any set of test pieces can be adjusted according to the forming format size of the in-flight additive manufacturing equipment, the coverage size of each scanning galvanometer, and the size of the test piece.

[0027] Among them, the relative positions of the unfused characteristic metallographic test blocks, the tensile horizontal bars and the tensile vertical bars in each group of test pieces can be kept consistent to eliminate the differences caused by position changes.

[0028] S12, setting process parameters, keeping the gantry stationary, and using the flying additive manufacturing equipment to print, to obtain the printed unfused characteristic metallographic test block and tensile test bar corresponding to the static typical position.

[0029] As a specific embodiment of the present invention, in this step, the unfused characteristic metallographic test block can be scanned in layers. By adjusting the printing program, the flying additive manufacturing device can perform different powder spreading printing on different spacing layers of the unfused characteristic metallographic test block from bottom to top, so as to obtain different degrees of unfused effects. The unfused characteristic metallographic test block is distributed with several spacing layers along the height direction of the test block, as shown in the attached figure. Figure 2 As shown, the interlayers of the unfused characteristic metallographic test block are, from bottom to top, interlayer 1, interlayer 2, interlayer 3 and interlayer 4. The above-mentioned arrangement of the interlayer is only an example, but is not limited thereto.

[0030] S13, pre-processing the printed unfused characteristic metallographic test block and tensile test bar.

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

[0032] S14, the longitudinal section sampling metallographic structure analysis is carried out on the pre-treated unfused characteristic metallographic test block, and the room temperature tensile mechanical property test is carried out on the tensile test bar. The unfused structure characteristics and mechanical property characteristics of different layer thicknesses of the test pieces (including metallographic test blocks and tensile test bars) formed by laser forming of each optical unit are compared, and the consistency of the metallographic structure at the static typical position and the mechanical properties of the tensile test bar is verified.

[0033] Furthermore, in the present invention, after completing the verification of the consistency of the metallographic structure and the mechanical properties of the tensile test bar at the static typical position of the flying gantry, the verification of the consistency of the metallographic structure and the mechanical properties of the tensile test bar is carried out at the dynamic typical position of the flying gantry.

[0034] The specific steps include:

[0035] S21, determine the dynamic typical position arrangement of the unfused characteristic metallographic test block and the tensile test rod according to the forming format size, flying gantry structure and scanning galvanometer arrangement of the flying additive manufacturing equipment.

[0036] For the flying additive manufacturing equipment with double flying gantry structure, N scanning galvanometers are arranged on a single gantry, and the scanning area is selected as the entire forming format. A first specimen group is arranged at each end position of the corresponding coverage range during the movement of each scanning galvanometer with the flying gantry. The first specimen group includes 1 unfused characteristic metallographic specimen block, 1 tensile horizontal bar and 1 tensile vertical bar. A total of 4N first specimen groups are arranged in the entire scanning area. A second specimen group is arranged at each end position of the splicing line formed by splicing any two adjacent scanning galvanometers in a single gantry. The second specimen group includes 1 unfused characteristic metallographic specimen block and 1 tensile horizontal bar. A total of 4(N-1) second specimen groups are arranged in the entire scanning area. A third specimen group is arranged at each position of the boundary line formed by splicing any two scanning galvanometers opposite to each other between the two gantries. The third specimen group includes 1 unfused characteristic metallographic specimen block and 1 tensile horizontal bar. A total of N third specimen groups are arranged in the entire scanning area. Each laser beam scans the test pieces within its respective coverage range. During the scanning process, the gantry moves normally, so that each group of test pieces can reflect the light emission characteristics of the corresponding optical unit in a dynamic typical position.

[0037] S22, setting process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain the printed unfused characteristic metallographic test block and tensile test rod corresponding to the dynamic typical position.

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

[0039] S23, pre-processing the printed unfused characteristic metallographic test block and tensile test bar.

[0040] The preprocessing step in this step is similar to the preprocessing operation in the above step S13, and will not be repeated here.

[0041] S24, the longitudinal section sampling metallographic structure analysis of the pre-treated unfused characteristic metallographic specimens, the room temperature tensile mechanical properties test of the tensile horizontal and vertical bars, the unfused structure characteristics and mechanical properties characteristics of the specimens with different layer thicknesses formed by laser forming of each optical unit are compared, and the consistency of the metallographic structure at the dynamic typical position and the mechanical properties of the tensile test bar is verified.

[0042] Furthermore, in the present invention, after completing the verification of the consistency of the metallographic structure and the mechanical properties of the tensile test bar at the dynamic typical position of the flying gantry, the consistency verification of the dimensions of the characteristic parts is carried out at the dynamic typical position of the flying gantry.

[0043] S31, determining the dynamic typical position arrangement of the size characteristic parts according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement.

[0044] For the flying additive manufacturing equipment with double flying gantry structure and N scanning galvanometers arranged on a single gantry, the scanning area is selected as the entire forming format, and one dimension feature is arranged at each end position of the corresponding coverage range of each scanning galvanometer during the movement of the flying gantry, with a total of 4N dimension feature parts; one dimension feature is arranged at each end position of the splicing line formed by splicing any two adjacent scanning galvanometers in a single gantry, with a total of 4(N-1) dimension feature parts; one dimension feature is arranged at each end position of the intersection line formed by splicing any two opposite scanning galvanometers between the two gantries, with a total of N dimension feature parts; 9N-4 dimension feature parts are arranged in the entire scanning area. Each laser beam scans the feature parts in their respective coverage ranges, and the gantry moves normally during the scanning process, so that each feature part can reflect the light emission characteristics of the corresponding optical unit in the dynamic typical position.

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

[0046] S32, setting process parameters, the gantry moves normally, and printing is performed using a flying additive manufacturing device to obtain a printed dimensional feature part corresponding to a dynamic typical position.

[0047] S33, pre-processing the printed dimension feature parts.

[0048] As a specific embodiment of the present invention, after the printing of the flying additive manufacturing device is completed, the substrate with the dimensional feature is taken out from the flying additive manufacturing device, and the surface metal powder is cleaned until no metal powder remains on the surface; wire cutting is used to separate the dimensional feature and the substrate.

[0049] S34, analyzing the external dimensional features of the pre-processed dimensional feature parts, comparing the external dimensional features of the dimensional feature parts obtained by laser forming of each optical unit, and verifying the dimensional consistency of the dynamic typical position feature parts.

[0050] As a specific embodiment of the present invention, a three-dimensional scanning device may be used to analyze the external dimension characteristics of the dimension characteristic part.

[0051] The present invention provides a multi-laser forming consistency verification method based on the structural characteristics of flying additive manufacturing equipment. This method is aimed at flying additive manufacturing equipment with more complex structures, and realizes effective verification of ultra-large-scale multi-laser forming consistency. The verification efficiency is high and can meet the verification accuracy requirements.

[0052] In order to further understand the present invention, the following Figures 1 to 5 The multi-laser forming consistency verification method for flight additive manufacturing equipment of the present invention is described in detail.

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

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

[0055] S11, according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement, determine the static typical position arrangement of the unfused characteristic metallographic test block and the tensile test bar in the model processing software.

[0056] Taking the flying additive manufacturing equipment with a forming format size of 1.5m×1.5m, 52 lasers, a double flying gantry structure, and 26 scanning galvanometers arranged on a single gantry as an example, the static typical position arrangement of the unfused characteristic metallographic test block and the tensile test bar is shown in the attached figure. Figure 1 As shown, the scanning area is selected as a fixed position in the middle of the respective coverage ranges of the two flying gantries when working simultaneously. A group of test pieces consisting of 3 unfused characteristic metallographic test pieces, 3 tensile horizontal bars and 3 tensile vertical bars are arranged within the coverage range of each scanning galvanometer. A total of 52 groups of test pieces are arranged in the entire scanning area, and the corresponding single-beam laser is used to scan them separately. The gantry does not move during the scanning process, so that each group of test pieces can reflect the light output characteristics of the corresponding optical unit in a static typical position.

[0057] S12, selecting appropriate process parameters, keeping the gantry stationary, and using the corresponding flying additive manufacturing equipment to print and obtain the printed unfused characteristic metallographic test block and tensile test bar blank corresponding to the static typical position.

[0058] Among them, the longitudinal section structure of the unfused characteristic metallographic test block is shown in the attached Figure 2 As shown, four spacer layers are evenly distributed at different heights of the test block, namely, spacer layer 1, spacer layer 2, spacer layer 3, and spacer layer 4 from bottom to top. By adjusting the printing program, the equipment can print one layer of powder without gloss at the spacer layer 1 position of the unfused characteristic metallographic test block, print two layers of powder without gloss at the spacer layer 2 position, print three layers of powder without gloss at the spacer layer 3 position, and print four layers of powder without gloss at the spacer layer 4 position, so as to obtain different degrees of unfused effects. The above-mentioned different powder printing methods for different spacer layers are only an example listed, but are not limited to this.

[0059] S13, after printing is completed, the substrate with the unfused characteristic metallographic test block and the tensile test bar blank is taken out from the flight additive manufacturing equipment, and the surface metal powder is cleaned until no metal powder remains on the surface; the unfused characteristic metallographic test block, the tensile test bar blank and the substrate are separated by wire cutting; the separated unfused characteristic metallographic test block and the tensile test bar are subjected to hot isostatic pressing and solution treatment.

[0060] S14, the longitudinal section sampling metallographic structure analysis is carried out on the pre-treated unfused characteristic metallographic test block, and the room temperature tensile mechanical property test is carried out on the tensile horizontal bar and the vertical bar. The unfused structure characteristics and mechanical property characteristics of the different layer thicknesses of the test pieces obtained by laser forming of each optical unit are compared, and the consistency of the metallographic structure at the static typical position and the mechanical properties of the tensile test bar is verified.

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

[0062] S21, according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement, determine the dynamic typical position arrangement of the unfused characteristic metallographic test block and the tensile test rod in the model processing software.

[0063] Taking the flying additive manufacturing equipment with a forming format size of 1.5m×1.5m, 52 lasers, a double flying gantry structure, and 26 scanning galvanometers arranged on a single gantry as an example, the dynamic typical position arrangement of the unfused characteristic metallographic test block and the tensile test bar is shown in the attached figure. Figure 3 As shown, the scanning area is selected as the entire forming format. A first specimen group is arranged at each end of the corresponding coverage range during the movement of each scanning galvanometer with the flying gantry. The first specimen group includes 1 unfused characteristic metallographic specimen, 1 tensile horizontal bar and 1 tensile vertical bar. A total of 104 first specimen groups are arranged in the entire scanning area. A second specimen group is arranged at each end of the splicing line formed by splicing any two adjacent scanning galvanometers in a single gantry. The second specimen group includes 1 unfused characteristic metallographic specimen and 1 tensile horizontal bar. A total of 100 second specimen groups are arranged in the entire scanning area. Two scanning galvanometers facing each other between the two gantries form a row. A third specimen group is arranged at each boundary line formed by splicing two scanning galvanometers in each row. The third specimen group includes 1 unfused characteristic metallographic specimen and 1 tensile horizontal bar. A total of 52 third specimen groups are arranged in the entire scanning area. Each laser beam scans the test pieces within its respective coverage range. During the scanning process, the gantry moves normally, so that each group of test pieces can reflect the light emission characteristics of the corresponding optical unit in a dynamic typical position.

[0064] S22, selecting appropriate process parameters, the gantry moves normally during the scanning process, and using the corresponding flying additive manufacturing equipment to print and obtain the printed unfused characteristic metallographic test block and tensile test bar blank corresponding to the dynamic typical position.

[0065] Among them, the longitudinal section structure of the unfused characteristic metallographic test block is shown in the attached Figure 2 As shown, four spacer layers are evenly distributed at different heights of the test block, namely, spacer layer 1, spacer layer 2, spacer layer 3, and spacer layer 4 from bottom to top. By adjusting the printing program, the equipment can print one layer of powder without gloss at the spacer layer 1 position of the unfused characteristic metallographic test block, print two layers of powder without gloss at the spacer layer 2 position, print three layers of powder without gloss at the spacer layer 3 position, and print four layers of powder without gloss at the spacer layer 4 position, so as to obtain different degrees of unfused effects. The above-mentioned different powder printing methods for different spacer layers are only an example listed, but are not limited to this.

[0066] S23, after printing is completed, the substrate with the unfused characteristic metallographic test block and the tensile test bar blank is taken out from the flight additive manufacturing equipment, and the surface metal powder is cleaned until no metal powder remains on the surface; the unfused characteristic metallographic test block, the tensile test bar blank and the substrate are separated by wire cutting; the separated unfused characteristic metallographic test block and the tensile test bar are subjected to hot isostatic pressing and solution treatment.

[0067] S24, the longitudinal section sampling metallographic structure analysis of the pre-treated unfused characteristic metallographic specimens, the room temperature tensile mechanical properties test of the tensile horizontal and vertical bars, the unfused structure characteristics and mechanical properties characteristics of the specimens with different layer thicknesses formed by laser forming of each optical unit are compared, and the consistency of the metallographic structure at the dynamic typical position and the mechanical properties of the tensile test bar is verified.

[0068] S3, verify the consistency of characteristic parts dimensions at the typical dynamic position of the flying gantry:

[0069] S31, determining the dynamic typical position arrangement of the dimension feature parts in the model processing software according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement.

[0070] Taking the flying additive manufacturing equipment with a forming format size of 1.5m×1.5m, 52 lasers, a double flying gantry structure, and 26 scanning galvanometers arranged on a single gantry as an example, the dynamic typical position arrangement of its size feature parts is shown in the attached figure. Figure 4As shown, the scanning area is selected as the entire forming format. In the process of each scanning galvanometer moving with the flying gantry, one size feature is arranged at each end of the corresponding coverage range, for a total of 104; in a single gantry, one size feature is arranged at each end of the splicing line formed by splicing any two adjacent scanning galvanometers, for a total of 100; two scanning galvanometers facing each other between the two gantries form a row, and one size feature is arranged at each intersection line formed by splicing two scanning galvanometers in each row, for a total of 52. Each laser beam scans the feature within its respective coverage range, and the gantry moves normally during the scanning process, so that each feature can reflect the light emission characteristics of the corresponding optical unit at a dynamic typical position.

[0071] Among them, the size characteristic parts and their appearance structures are as shown in the attached Figure 5 As shown, it is an equilateral triangular thin-walled feature cylinder with rounded corner features. The specific size is determined according to the forming format size of the actual flight additive manufacturing equipment, the coverage range of the scanning galvanometer and the size verification requirements.

[0072] S32, selecting appropriate process parameters, the gantry moves normally during the scanning process, and using the corresponding flying additive manufacturing equipment to print and obtain the printed dimensional feature parts corresponding to the dynamic typical position.

[0073] S33, after printing is completed, the substrate with the dimension feature is taken out from the flight additive manufacturing equipment, and the surface metal powder is cleaned until no metal powder remains on the surface; the dimension feature is separated from the substrate by wire cutting.

[0074] S34, using a three-dimensional scanning device to analyze the external dimensional features of the pre-processed dimensional feature parts, comparing the external dimensional features of the dimensional feature parts obtained by laser forming of each optical unit, and verifying the dimensional consistency of the dynamic typical position feature parts.

[0075] In summary, the present invention provides a method for verifying the consistency of multi-laser forming for flight additive manufacturing equipment, which verifies the consistency of metallographic structure, mechanical properties of tensile test bars and dimensions of characteristic parts for the static typical position of the flight gantry and the dynamic typical position of the flight gantry. This method is suitable for flight additive manufacturing equipment with more complex structures, and realizes effective verification of the consistency of ultra-large-format multi-laser forming. The verification efficiency is high and the verification accuracy requirements can be met. Compared with the prior art, this device can solve the technical problem that the traditional fixed-position single-print verification method in the prior art cannot accurately and effectively verify the consistency of multi-laser forming of flight additive manufacturing equipment.

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

[0077] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0078] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A multi-laser forming consistency verification method for flight additive manufacturing equipment, characterized in that: The multi-laser forming consistency verification method comprises: S1, verify the consistency of metallographic structure and mechanical properties of tensile test bars at the typical static position of the flight gantry; S2, verify the consistency of metallographic structure and mechanical properties of tensile test bars at the typical dynamic position of the flying gantry; S3, verify the consistency of characteristic part dimensions at the typical dynamic position of the flying gantry.

2. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 1, characterized in that: S1 specifically includes: S11, determining the static typical position arrangement of the unfused characteristic metallographic test block and the tensile test bar according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement; S12, setting process parameters, keeping the gantry stationary, and printing using the flying additive manufacturing equipment to obtain a printed unfused characteristic metallographic test block and a tensile test bar corresponding to a static typical position; S13, pre-processing the unfused characteristic metallographic test block and the tensile test bar printed in S12; S14, the longitudinal section sampling metallographic structure analysis of the unfused characteristic metallographic specimen after S13 pretreatment, the room temperature tensile mechanical property test of the tensile test bar, the unfused structure characteristics and mechanical property characteristics of the specimens with different layer thicknesses formed by laser forming of each optical unit are compared, and the consistency of the metallographic structure at the static typical position and the mechanical properties of the tensile test bar is verified.

3. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 2, characterized in that: S11 specifically includes: for a double flying gantry structure, a flying additive manufacturing device with N scanning galvanometers arranged on a single gantry, the scanning area is selected as a fixed position in the middle of the respective coverage ranges of the two flying gantries when working simultaneously, and a group of test pieces consisting of M unfused characteristic metallographic test blocks, M stretching horizontal bars and M stretching vertical bars are arranged within the coverage range of each scanning galvanometer. A total of 2N groups of test pieces are arranged in the entire scanning area, and each group of test pieces can reflect the light output characteristics of the corresponding optical unit in a static typical position; M and N are both positive integers.

4. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 1, characterized in that: S2 specifically includes: S21, determining the dynamic typical position arrangement of the unfused characteristic metallographic test block and the tensile test bar according to the forming format size, the flying gantry structure and the scanning galvanometer arrangement of the flying additive manufacturing equipment; S22, setting process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain the printed unfused characteristic metallographic test block and tensile test bar corresponding to the dynamic typical position; S23, pre-processing the unfused characteristic metallographic test block and the tensile test bar printed in S22; S24, the longitudinal section sampling metallographic structure analysis of the unfused characteristic metallographic specimen after S23 pretreatment, the room temperature tensile mechanical properties test of the tensile horizontal bar and the vertical bar, the unfused structure characteristics and mechanical properties characteristics of the specimens with different layer thicknesses obtained by laser forming of each optical unit are compared, and the consistency of the metallographic structure at the dynamic typical position and the mechanical properties of the tensile test bar is verified.

5. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 4, characterized in that: S21 specifically includes: for a double flying gantry structure, a flying additive manufacturing device with N scanning galvanometers arranged on a single gantry, the scanning area is selected as the entire forming format, and a first test piece group is arranged at each end position of the corresponding coverage range during the movement of each scanning galvanometer with the flying gantry, and the first test piece group includes 1 unfused characteristic metallographic test block, 1 tensile horizontal bar and 1 tensile vertical bar, and a total of 4N first test piece groups are arranged in the entire scanning area; between any two adjacent scanning galvanometers in a single gantry, A second specimen group is arranged at each end of the splicing line formed by the mutual splicing, the second specimen group includes 1 unfused characteristic metallographic specimen block and 1 tensile cross bar, and a total of 4 (N-1) second specimen groups are arranged in the entire scanning area; a third specimen group is arranged at each intersection position formed by the mutual splicing between any two scanning galvanometers opposite to each other between the two gantries, the third specimen group includes 1 unfused characteristic metallographic specimen block and 1 tensile cross bar, and a total of N third specimen groups are arranged in the entire scanning area; N is a positive integer.

6. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 2 or 4, characterized in that: In S12 and S22, the metallographic test block with unfused features is scanned in layers.

7. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 2 or 4, characterized in that: In S13 and S23, the pretreatment includes: after the flight additive manufacturing equipment completes printing, taking out the substrate with the unfused characteristic metallographic test block and the tensile test rod from the flight additive manufacturing equipment, cleaning the surface metal powder until no metal powder remains on the surface; using wire cutting to separate the unfused characteristic metallographic test block, the tensile test rod and the substrate; and performing hot isostatic pressing and solution treatment on the separated unfused characteristic metallographic test block and the tensile test rod.

8. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 1, characterized in that: S3 specifically includes: S31, determining a dynamic typical position arrangement of the size characteristic parts according to the forming format size of the flight additive manufacturing equipment, the flight gantry structure and the scanning galvanometer arrangement; S32, setting process parameters, the gantry moves normally, and printing is performed using the flying additive manufacturing equipment to obtain a printed dimensional feature part corresponding to a dynamic typical position; S33, pre-processing the dimension feature parts printed in S32; S34, analyzing the external dimensional features of the dimension feature parts preprocessed in S33, comparing the external dimensional features of the dimension feature parts obtained by laser forming of each optical unit, and verifying the dimensional consistency of the dynamic typical position feature parts.

9. The multi-laser forming consistency verification method for a flying additive manufacturing device according to claim 8, characterized in that: S31 specifically includes: for a double flying gantry structure, a flying additive manufacturing device with N scanning galvanometers arranged on a single gantry, the scanning area is selected as the entire forming format, and one size feature is arranged at each end of the corresponding coverage range of each scanning galvanometer during the movement of the flying gantry, for a total of 4N size feature parts; one size feature is arranged at each end of the splicing line formed by splicing any two adjacent scanning galvanometers in a single gantry, for a total of 4(N-1) size feature parts; one size feature is arranged at each end of the boundary line formed by splicing any two opposite scanning galvanometers between the two gantries, for a total of N size feature parts; a total of 9N-4 size feature parts are arranged in the entire scanning area.

10. The multi-laser forming consistency verification method for flight additive manufacturing equipment according to claim 8, characterized in that: S33 specifically includes: after the printing of the flying additive manufacturing equipment is completed, taking out the substrate with the size feature parts from the flying additive manufacturing equipment, cleaning the surface metal powder until no metal powder remains on the surface; and using wire cutting to separate the size feature parts from the substrate.

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