Feature component for verifying stress accumulation of flight printing equipment and verification method

Abstract

The invention provides a feature assembly for verifying stress accumulation of flight printing equipment and a verification method. The feature assembly for verifying the stress accumulation of the flight printing equipment comprises a plurality of feature parts which are sequentially arranged in the direction perpendicular to the movement direction of a gantry; any characteristic piece comprises a main body frame and a stress amplification part, the main body frame spans a double-gantry working area boundary line in the gantry movement direction and spans the breadth, and the main body frame is a thin-wall rectangular frame; the stress amplification part is located in the center area of the main body frame and is of a thin-wall grid structure. According to the method, stress accumulation at the junction of the two gantries is concerned, connection of grids and the like is designed in the lap joint area, the stress accumulation degree is verified through grid forming and lap joint precision, and stress accumulation of the flight printing equipment can be effectively and reliably verified.

Description

Technical Field

[0001] This invention belongs to the field of laser selective melting additive manufacturing technology, and particularly relates to a feature component and verification method for stress accumulation verification of flying printing equipment. Background Technology

[0002] Selective Laser Melting (SLM) is an advanced additive manufacturing method used to produce high-precision metal parts. Traditional SLM technology typically uses a single laser for printing, and its print size is limited by laser power and scanning range. To achieve the printing of larger parts, flying SLM technology has emerged. It significantly improves printing efficiency and print size by using multiple lasers and scanning galvanometers arranged on a movable gantry to work collaboratively and moving the printing process.

[0003] Stress accumulation is a critical issue in SLM (Surface Mount Technology) technology. During SLM additive manufacturing, the high energy of the laser beam causes rapid localized heating and cooling, creating temperature gradients and generating thermal stress. This thermal stress is the most direct source of stress in the SLM process, and residual stress can lead to defects such as deformation and cracks in the parts. Accurately verifying the stress accumulation during the printing process is a crucial and essential technical step before putting flying lithography equipment into actual product production. Stress accumulation directly affects the dimensional accuracy, geometric integrity, and final performance of printed parts; inconsistencies in its distribution and accumulation can significantly impact the overall quality and reliability of the parts.

[0004] For traditional fixed-mirror SLM equipment, stress accumulation is typically evaluated indirectly by printing standard test blocks at specific locations on the printing surface and then measuring the stress after stress release or conducting stress tests in specific areas. Verification of stress accumulation is relatively simple for traditional SLM equipment because the print size is small and the stress distribution is relatively uniform. This verification method primarily focuses on the macroscopic stress performance of the statically printed area.

[0005] However, for flying SLM devices, the use of multiple lasers leads to the coupling of multiple physical fields (such as thermal, mechanical, and electromagnetic fields) during printing, resulting in complex stress accumulation problems. Furthermore, unlike traditional devices, flying printers are characterized by random laser beam positions, complex trajectories, and dynamically changing printing paths. During printing, the gantry system, print head, and the part being formed continuously accumulate stress. At the junction of two gantry sections, printing stress may cause misalignment, excessive component deformation, and other problems. Therefore, traditional methods based on static fixed positions or single measurements after printing are insufficient to comprehensively and accurately capture and assess the dynamic and variable stress accumulation during flying printing, especially the differences in stress transmission and accumulation between different printing stages, different printing areas, and between moving parts of the device and the printed part. This limitation of the verification method makes it impossible to effectively predict and control stress concentration, deformation, or even printing failures that may occur during continuous, high-speed, and large-scale printing with flying printers. Therefore, it is necessary to develop an effective method to verify the stress accumulation of flight printing equipment, which is crucial for ensuring the quality and reliability of printed parts, taking into account the unique structure and dynamic printing characteristics of flight printing equipment. Summary of the Invention

[0006] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0007] According to one aspect of the present invention, a feature component for stress accumulation verification of a flight printing device is provided. The feature component for stress accumulation verification of a flight printing device includes: a plurality of feature members arranged sequentially along a direction perpendicular to the gantry movement direction; each feature member includes a main frame and a stress amplification part, the main frame spans the boundary line of the double gantry working area along the gantry movement direction and is arranged across the width, the main frame being a thin-walled rectangular frame; the stress amplification part is located in the central region of the main frame and is a thin-walled mesh structure.

[0008] Furthermore, the feature components are used for stress accumulation verification in flight printing equipment with a forming area ≥1500mm.

[0009] Furthermore, the stress amplification section has stress concentration grooves symmetrically arranged on both sides of the boundary line.

[0010] Furthermore, the stress concentration groove has a V-shaped notch.

[0011] Furthermore, the network structure of the stress amplification section adopts an orthogonal, honeycomb, or random mesh structure.

[0012] According to another aspect of the present invention, a method for verifying stress accumulation in a flight printing device is provided, which verifies stress accumulation in the flight printing device by flight SLM printing of the feature components described above.

[0013] Furthermore, the stress accumulation verification method for flight printing equipment specifically includes: Step 1: Taking into account the characteristics of sequential forming in flight printing, design the feature components described above for stress accumulation verification of the flight printing equipment. Step two: Use in-flight SLM to print the feature components designed in step one; Step 3: Quantify the stress accumulation effect in the interface area during dual-gantry collaborative printing, evaluate the impact of stress accumulation on the geometric accuracy and micro-connection quality of the component, and complete the verification of the stress accumulation degree of the feature component.

[0014] Furthermore, the mesh structure of the stress amplification section adopts an orthogonal, honeycomb, or random mesh topology.

[0015] Furthermore, 316L stainless steel was used for printing the verification documents.

[0016] Furthermore, the evaluation parameters include: the maximum deformation in the interface area, the dimensional accuracy of the stress amplification section, and macroscopically visible cracks and delamination defects.

[0017] This invention provides a feature component and verification method for verifying stress accumulation in flight printing equipment. By setting multiple feature components, including a main frame and a stress amplification section, the method comprehensively covers the gantry movement direction, amplifies the degree of stress accumulation, and also focuses on stress accumulation at the junction of two gantry sections. By using flight SLM printing with this feature component, the stress accumulation of the printing equipment can be effectively and reliably verified. Compared with existing technologies, this invention solves the technical problem that conventional stress accumulation verification methods for printing equipment are not applicable to flight printing. Attached Figure Description

[0018] 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.

[0019] Figure 1 A schematic diagram showing the shape and arrangement of feature components for stress accumulation verification of a flight printing device according to a specific embodiment of the present invention is provided. Detailed Implementation

[0020] 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.

[0021] 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.

[0022] 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.

[0023] like Figure 1 As shown, according to a specific embodiment of the present invention, a feature component for stress accumulation verification of a flight printing device is provided. The feature component includes several feature elements arranged sequentially along the direction perpendicular to the gantry movement direction. Each feature element includes a main frame and a stress amplification part. The main frame spans the boundary line of the double gantry working area along the gantry movement direction and is arranged across the width of the frame. The main frame is a thin-walled rectangular frame. The stress amplification part is located in the central area of ​​the main frame and is a thin-walled mesh structure.

[0024] This configuration provides a feature component for verifying stress accumulation in flight printing equipment. By setting multiple features, including the main frame and stress amplification sections, it comprehensively covers the gantry movement direction, amplifies the degree of stress accumulation, and also focuses on stress accumulation at the junction of two gantry sections, where stress amplification sections are also included. By using flight SLM printing with this feature component, the stress accumulation of the printing equipment can be effectively and reliably verified.

[0025] Furthermore, in this invention, this feature component can be used for stress accumulation verification in flight printing equipment with a forming area ≥1500mm. As a specific embodiment of this invention, the main frame dimensions can be set to 1500mm × 300mm × 50mm, with a wall thickness of 2mm, and the stress amplification section dimensions can be set to 20mm × 20mm, with a grid line width of 1mm. The above dimension settings are merely an example and are not limited to; adjustments can be made based on actual flight printing parameters.

[0026] Furthermore, in this invention, to further amplify the degree of stress accumulation, stress concentration grooves can be symmetrically arranged on both sides of the boundary line in the stress amplification section. As a specific embodiment of this invention, the stress concentration grooves can be V-shaped notches with a depth of 0.5 mm. The above-mentioned dimensional settings are merely one example and are not limited thereto; adjustments can be made based on actual flight printing parameters.

[0027] Furthermore, in this invention, the network structure of the stress amplification section can be an orthogonal, honeycomb, or random mesh structure.

[0028] Due to the characteristics of sequential forming in flight printing, problems such as overlapping misalignment and excessive component deformation may occur at the junction of two gantry due to printing stress. The feature component of this invention spans the forming area and sets up a grid connection in the overlapping area, which effectively amplifies the stress accumulation. At the same time, it can be observed whether the grid forming accuracy meets the requirements.

[0029] According to another aspect of the present invention, a method for verifying stress accumulation in a flight printing device is provided, wherein the method verifies stress accumulation in the flight printing device by flight SLM printing of the feature components described above.

[0030] Due to the sequential forming characteristics of flight printing, problems such as misalignment and excessive deformation of components may occur at the junction of two gantry due to printing stress. This invention uses flight SLM to print the feature parts of the above design and verifies the stress accumulation level through mesh forming and overlap accuracy.

[0031] Specifically, the stress accumulation verification method for this flight printing device includes the following steps: Step 1: Taking into account the characteristics of sequential forming in flight printing, design the feature components described above for stress accumulation verification of the flight printing equipment.

[0032] The number of feature parts and their specific design parameters can be adjusted according to the actual flight printing parameters.

[0033] The mesh structure of the stress amplification section can be designed with three mesh topologies: orthogonal, honeycomb, and random. Stress accumulation verification is performed on each of the three mesh structures to compare the connection reliability.

[0034] Step two: Use flying SLM to print the feature components designed in step one.

[0035] In a specific embodiment of the present invention, 316L stainless steel, which has a high coefficient of thermal expansion and high stress sensitivity, can be used for printing verification parts. The process parameters for flight printing are adjusted based on the selected printing material. The printing process follows the flight printing sequence.

[0036] Step 3: Quantify the stress accumulation effect at the interface during dual-gantry collaborative printing, assess the impact of stress accumulation on the geometric accuracy and micro-connection quality of the component, and complete the verification of the stress accumulation degree of the feature component. The degree of stress accumulation is evaluated by verifying whether the component forming accuracy meets the requirements.

[0037] The evaluation parameters include: the maximum deformation of the interface zone, the dimensional accuracy of the stress amplification section, and macroscopic visible cracks and delamination defects.

[0038] If the maximum deformation in the boundary area is ≤0.1mm / m, the line width deviation of the grid connection structure is ≤±0.05mm, and there are no macroscopically visible cracks / delamination defects, then the forming accuracy of the component meets the requirements.

[0039] A coordinate measuring machine (CMM) can be used to perform full-size scanning deformation measurement of components, with a focus on cantilever deflection and frame flatness.

[0040] Industrial CT scanning can be used to verify the connection quality of the 3D reconstructed mesh, including porosity and incomplete fusion defect analysis.

[0041] In addition, metallographic sectioning can be used to observe the microstructure of the interface area, including the observation of grain orientation and molten pool interface.

[0042] The stress accumulation verification method for in-flight printing equipment of this invention focuses on stress accumulation at the junction of two gantry lines. It designs connections such as meshes in the overlap area and verifies the degree of stress accumulation through mesh formation and overlap accuracy. This invention provides a novel stress accumulation verification method to ensure the stable and reliable application of in-flight printing equipment in actual production.

[0043] In summary, this invention provides a feature component and verification method for verifying stress accumulation in flight printing equipment. By setting multiple feature components, including a main frame and a stress amplification section, it comprehensively covers the gantry movement direction, amplifies the degree of stress accumulation, and pays attention to the stress accumulation at the junction of two gantry sections by setting the stress amplification section. By using flight SLM printing with this feature component, the stress accumulation of the flight printing equipment can be effectively and reliably verified, which is crucial for ensuring the quality and reliability of printed parts.

[0044] 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 feature component for verifying stress accumulation in flight printing equipment, characterized in that, The feature components used for stress accumulation verification of the flight printing equipment include: several feature parts arranged sequentially along the direction perpendicular to the gantry movement; each feature part includes a main frame and a stress amplification part, the main frame spans the boundary line of the double gantry working area along the direction of gantry movement and is set across the width, the main frame is a thin-walled rectangular frame; the stress amplification part is located in the central area of ​​the main frame, the stress amplification part is a thin-walled mesh structure.

2. The feature component for stress accumulation verification of flight printing equipment according to claim 1, characterized in that, The feature components are used for stress accumulation verification of flight printing equipment with a forming area ≥1500mm.

3. The feature component for stress accumulation verification of flight printing equipment according to claim 1, characterized in that, The stress amplification section has stress concentration grooves symmetrically arranged on both sides of the boundary line.

4. The feature component for stress accumulation verification of flight printing equipment according to claim 3, characterized in that, The stress concentration groove has a V-shaped notch.

5. The feature component for stress accumulation verification of flight printing equipment according to claim 4, characterized in that, The network structure of the stress amplification section adopts an orthogonal, honeycomb, or random mesh structure.

6. A method for verifying stress accumulation in a flight printing device, characterized in that, The stress accumulation verification method for the flight printing device verifies the stress accumulation of the flight printing device by flight SLM printing the feature components as described in any one of claims 1 to 5.

7. The method for verifying stress accumulation in a flight printing device according to claim 6, characterized in that, The stress accumulation verification method for the flight printing device specifically includes: Step 1: Taking into account the characteristics of sequential forming in flight printing, design a feature component for stress accumulation verification of flight printing equipment as described in any one of claims 1 to 5; Step two: Use in-flight SLM to print the feature components designed in step one; Step 3: Quantify the stress accumulation effect in the interface area during dual-gantry collaborative printing, evaluate the impact of stress accumulation on the geometric accuracy and micro-connection quality of the component, and complete the verification of the stress accumulation degree of the feature component.

8. The method for verifying stress accumulation in a flight printing device according to claim 7, characterized in that, The mesh structure of the stress amplification section adopts an orthogonal, honeycomb, or random mesh topology.

9. The method for verifying stress accumulation in a flight printing device according to claim 7, characterized in that, Verification documents are printed using 316L stainless steel.

10. The method for verifying stress accumulation in a flight printing device according to claim 7, characterized in that, Evaluation parameters include: maximum deformation in the interface zone, dimensional accuracy of the stress amplification zone, and macroscopically visible cracks and delamination defects.

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