Structural optimization and rapid preparation method of aviation structural member

Abstract

The invention relates to the technical field of additive manufacturing and structural design, and discloses an aviation structural part structural optimization and rapid preparation method which comprises the steps that an optimization space is defined, a design space and a non-design space are defined for a to-be-optimized target structural part, and optimization analysis is conducted on the part of the design space; force and displacement are applied, displacement constraint and test load are applied to the target structural member, and the maximum rigidity of the target structural member is obtained through testing; optimization analysis: based on the maximum rigidity of the target structural member as an optimization target, carrying out optimization analysis on the target structural member to obtain an optimized structural member; result contrastive analysis: performing strength contrastive analysis on the target structural member and the optimized structural member, and judging whether the strength of the optimized structural member meets a preset requirement or not; exporting a digital model, and exporting an optimization model of which the strength of the optimized structural member meets a preset requirement; and additive preparation is conducted, and the optimized structural part is prepared based on the exported optimization model. And innovative design and low-cost rapid preparation of typical aviation parts can be realized.

Description

Technical Field

[0001] The present invention relates to structural optimization and preparation methods, and specifically to a method for structural optimization and rapid preparation of an aviation structural component, belonging to the technical fields of additive manufacturing and structural design. Background Art

[0002] With the rapid development of computer technology, structural optimization design has gradually become an important tool for structural innovative design. It can obtain a better model without relying on the initial configuration and the experience of engineers, and can determine the form of the internal material layout of the structure to ensure obtaining the optimal performance under certain constraints. In aviation equipment, innovative structures can be obtained based on structural optimization, making the structure of the product better or significantly improving the lightweight performance.

[0003] However, the configuration of structural optimization is complex, and it is very difficult to prepare using traditional processes. The traditional approach is to perform secondary design on the structure based on manufacturing experience to meet manufacturability and reduce manufacturing costs. Metal additive manufacturing technology realizes the preparation of structures by the way of point-by-point melting of materials - lap-by-lap of each layer - layer-by-layer accumulation, and can achieve low-cost and rapid preparation of highly complex structures, subverting the limitations of traditional manufacturing technology and solving the problem that product R & D is restricted by manufacturing. Therefore, combining structural optimization - advanced design technology with additive manufacturing - advanced manufacturing technology can achieve innovative design and low-cost rapid preparation of typical aviation components. Based on this, this patent provides a method for structural optimization and rapid preparation of a certain aviation structural component. Summary of the Invention

[0004] The purpose of the present invention is to provide a method for structural optimization and rapid preparation of an aviation structural component to optimize the traditional structure of the aviation structural component and achieve low-cost rapid preparation using metal additive manufacturing technology.

[0005] The purpose of the present invention can be achieved through the following technical solutions:

[0006] A method for structural optimization and rapid preparation of an aviation structural component includes the following steps:

[0007] Step 1: Define the optimization space, define the design space and non-design space for the target structural component to be optimized, and perform optimization analysis on the parts in the design space;

[0008] Step 2: Apply force and displacement, apply displacement constraints and test loads to the target structural component, and test to obtain the maximum stiffness of the target structural component;

[0009] Step 3: Optimization analysis, based on the maximum stiffness of the target structural component as the optimization goal, perform optimization analysis on the target structural component to obtain the optimized structural component;

[0010] Step 4: Result comparison and analysis. Compare the strength of the target structural member and the optimized structural member to determine whether the strength of the optimized structural member meets the preset requirements.

[0011] Step 5: Export the digital model. Export the optimized model whose strength of the optimized structural member meets the preset requirements.

[0012] Step 6: Additive manufacturing preparation. Prepare the optimized structural member based on the exported optimized model.

[0013] Optionally, after the optimization analysis in Step 3, the process of obtaining the optimized structural member is as follows:

[0014] According to the optimization analysis results, reconstruct the model of the structure of the target structural member and smooth the stress concentration positions to obtain the final optimized structural member.

[0015] Optionally, in Step 4, if the difference between the maximum equivalent stresses of the target structural member and the optimized structural member is within the preset range, the strength of the optimized structural member meets the preset requirements; otherwise, it does not meet the preset requirements.

[0016] Optionally, the format of the optimized model exported in Step 5 is adapted to the format of additive manufacturing.

[0017] Optionally, the preparation process of the optimized structural member includes additive manufacturing forming, heat treatment of the formed part, and post-treatment of the formed part.

[0018] Optionally, the process of additive manufacturing forming is as follows:

[0019] S1: Select the forming placement method on the substrate based on the principle of minimum stress and minimum support.

[0020] S2: Set process parameters. Select TC4 titanium alloy as the additive raw material. The process parameters are: laser power 160W - 180W, spot diameter 80μm, single-layer powder spreading thickness 30μm, and laser scanning speed 1000 - 1300mm / s.

[0021] Optionally, the heat treatment process of the formed part is: after the additive manufacturing forming is completed, perform heat treatment together with the substrate, and the heat treatment system is 800°C / 4h.

[0022] Optionally, the post-treatment process of the formed part is: separate the formed part of the additive manufacturing forming from the substrate and process it to meet the usage requirements.

[0023] Advantages of the present invention:

[0024] This method realizes the structural optimization of the target structural member, achieves a weight reduction of 29%, and realizes the forming of complex models after structural optimization through selective laser melting forming, which can achieve the innovative design and low-cost rapid preparation of typical aviation parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] For the convenience of those skilled in the art to understand, the present invention will be further described below in conjunction with the accompanying drawings.

[0026] Figure 1 It is a structural schematic diagram of the target structural member in the second embodiment of the present invention.

[0027] Figure 2 It is a structural schematic diagram of applying force and displacement to the target structural member in the second embodiment of the present invention.

[0028] Figure 3 It is a schematic diagram of the result after preliminary optimization in the second embodiment of the present invention.

[0029] Figure 4 It is a schematic diagram of the result after final optimization in the second embodiment of the present invention.

[0030] Figure 5 It is an equivalent stress nephogram of the target structural member in the second embodiment of the present invention.

[0031] Figure 6 It is an equivalent stress nephogram of the optimized structural member in the second embodiment of the present invention.

[0032] Figure 7 It is a flow chart of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0034] Embodiment 1:

[0035] Refer to Figure 7 , a method for structural optimization and rapid preparation of an aviation structural member, including the following steps:

[0036] Step 1: Define the optimization space, define the design space and non-design space for the target structural member to be optimized, and conduct optimization analysis on the parts in the design space to remove redundant materials until the requirements are met, while the parts in the non-design space will remain unchanged.

[0037] Step 2: Apply force and displacement, apply displacement constraints and test loads to the target structural member, and test to obtain the maximum stiffness of the target structural member; the displacement constraints can be clamping and fixing with a fixture or other limiting methods to keep the position of the target structural member stable during testing and make the test results accurate.

[0038] Step 3: Optimization analysis, based on the maximum stiffness of the target structural member as the optimization goal, conduct optimization analysis on the target structural member. According to the optimization analysis results, reconstruct the model of the structure of the target structural member and smooth the positions with stress concentration to obtain the final optimized structural member. The mass of the optimized structural member is reduced by 29% compared to the target structural member.

[0039] Step 4: Result comparison and analysis, conduct strength comparison and analysis between the target structural member and the optimized structural member to determine whether the strength of the optimized structural member meets the preset requirements; if the difference between the maximum equivalent stresses of the target structural member and the optimized structural member is within the preset range, the strength of the optimized structural member meets the preset requirements, otherwise it does not. If the preset requirements are not met, the model of the structure of the target structural member needs to be reconstructed until the preset requirements are met.

[0040] The optimized structural member meets the mechanical property requirements to achieve the preset requirements and can produce qualified parts.

[0041] Step 5: Export the digital model, export the optimized model whose strength of the optimized structural member meets the preset requirements; the format of the exported optimized model is adapted to the format of additive manufacturing. Generally, the optimized model formats are stl and stp, etc., which are the formats of 3D software models. The specific format is based on the final additive manufacturing software as the reference benchmark.

[0042] Step 6: Additive manufacturing preparation, prepare the optimized structural member based on the exported optimized model.

[0043] Specifically, the preparation process of the optimized structural member includes additive manufacturing forming, heat treatment of the formed part, and post-treatment of the formed part.

[0044] Optionally, the process of additive manufacturing forming is as follows:

[0045] S1: Select the forming and placement method on the substrate based on the principle of minimum stress and minimum support;

[0046] S2: Set process parameters, select TC4 titanium alloy as the additive raw material, and the process parameters are laser power 160W - 180W, spot diameter 80μm, single-layer powder spreading thickness 30μm, and laser scanning speed 1000 - 1300mm / s.

[0047] Specifically, the heat treatment process of the formed part is: after the additive manufacturing forming is completed, conduct heat treatment together with the substrate, and the heat treatment system is 800°C / 4h.

[0048] Specifically, the post-processing process of the formed part is as follows: the formed part manufactured by additive manufacturing is cut and separated from the substrate by wire cutting, and then processed by machining until it meets the usage requirements.

[0049] Embodiment 2:

[0050] Refer to Figures 1-6 as shown

[0051] Take Figure 1 a certain aviation structural part in

[0052] Define the optimization space, Figure 1 the reddish-brown part in

[0053] is the optimization design space. Figure 2 as shown

[0054] Apply force and displacement, apply displacement constraints and test loads to the target structural part, as Figure 3 shown

[0055] Optimal analysis, select maximizing stiffness as the optimization goal, conduct optimal analysis on the target structural part, and obtain the preliminary optimization result as Figure 4 shown

[0056] Model re-optimization and reconstruction of the structure of the benchmark structural part, and smooth treatment of some stress concentration positions. The final re-optimization result is as Figure 5 shown Figure 6 The equivalent stress nephogram of the target structural part is as

[0057] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor limit the invention to the specific embodiments described. Obviously, many modifications and changes can be made according to the content of this specification. These embodiments are selected and specifically described in this specification to better explain the principle and practical application of the present invention, so that those skilled in the art can understand and utilize the present invention well. The present invention is only limited by the claims and their full scope and equivalents.

Claims

1. A method for structural optimization and rapid preparation of aviation structural parts, characterized in that: The following steps are involved: Step 1: Define the optimization space, define the design space and non-design space for the target structural part to be optimized, and perform optimization analysis on the parts of the design space; Step 2: Apply force and displacement, apply displacement constraints and test loads to the target structural parts, and test to obtain the maximum stiffness of the target structural parts; Step 3: Optimization analysis: Based on the maximum stiffness of the target structural part as the optimization target, the target structural part is optimized and analyzed to obtain the optimized structural part; Step 4: Comparative analysis of results: comparative analysis of the target structural parts and the optimized structural parts to determine whether the strength of the optimized structural parts meets the preset requirements; Step 5: Export the digital model and export the optimized model whose strength of the optimized structural parts meets the preset requirements; Step 6: Additive manufacturing: manufacturing optimized structural parts based on the exported optimization model.

2. The method for optimizing and rapidly preparing aerospace structural parts according to claim 1, characterized in that: After the optimization analysis in step 3, the process of obtaining the optimized structural parts is as follows: According to the optimization analysis results, the structure of the target structural part is reconstructed and the stress concentration position is smoothed to obtain the final optimized structural part.

3. The method for structural optimization and rapid preparation of aviation structural parts according to claim 1, characterized in that: In the step 4, if the difference between the maximum equivalent stress of the target structural component and the optimized structural component is within a preset range, the strength of the optimized structural component meets the preset requirement; otherwise, it does not meet the preset requirement.

4. The method for optimizing and rapidly preparing aerospace structural parts according to claim 1, characterized in that: The format of the optimized model exported in step 5 is compatible with the format of additive manufacturing.

5. The method for structural optimization and rapid preparation of aviation structural parts according to claim 1, characterized in that: The preparation process of the optimized structural part includes additive manufacturing, heat treatment of the formed part and post-processing of the formed part.

6. The method for optimizing and rapidly preparing aerospace structural parts according to claim 1, characterized in that: The process of additive manufacturing is as follows: S1: Select the forming placement method on the substrate based on the principle of minimum stress and minimum support; S2: Set the process parameters and select TC4 titanium alloy as the additive raw material. The process parameters are: laser power 160W-180W, spot diameter 80μm, single layer powder thickness 30μm, laser scanning speed 1000-1300mm / s.

7. The method for optimizing and rapidly preparing aerospace structural parts according to claim 1, characterized in that: The heat treatment process of the molded part is: after the additive manufacturing is completed, the molded part is heat treated together with the substrate, and the heat treatment system is 800°C / 4h.

8. The method for structural optimization and rapid preparation of aviation structural parts according to claim 1, characterized in that: The post-processing process of the molded part is: separating the molded part formed by additive manufacturing from the substrate and processing it until it meets the use requirements.

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