Space device layered composite material and method for manufacturing the same
By adding an additional layer to the outside of 2A12 aluminum alloy and then performing cold rolling composite, the problem of edge cracking in the rolling process of space-use device materials was solved, the yield was improved and the cost was reduced.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- YINBANG CLAD MATERIAL
- Filing Date
- 2023-12-18
- Publication Date
- 2026-05-19
AI Technical Summary
Among the existing radiation-resistant materials for space-based devices, 2A12 aluminum alloy is prone to edge cracking during the rolling process, resulting in low material yield and increased costs.
An additional layer is laminated to the outside of the 2A12 aluminum alloy. The additional layer is selected from 1-series alloys, 3-series aluminum alloys, copper, or low-carbon steel. It is processed by cold rolling. The width of the additional layer is 10-20mm wider than that of the 2A12 aluminum alloy. After surface treatment, it is riveted and coated with rolling lubricant.
This effectively avoids edge cracking of 2A12 aluminum alloy and tantalum plate during the rolling process, improving the yield of materials and reducing costs.
Smart Images
Figure CN117772791B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of space-based device technology, specifically to a layered composite material for space-based devices and its preparation method. Background Technology
[0002] Currently, radiation-resistant materials for space-based devices use aluminum / tantalum layered composite materials. The aluminum material is 2A12 aluminum alloy, and the tantalum is pure tantalum. Since 2A12 aluminum alloy is an Al-Cu alloy, its processing performance is poor, and edge cracking may occur during the rolling process. Summary of the Invention
[0003] To address the aforementioned deficiencies in this field, this application aims to provide a layered composite material for space devices and a method for preparing the same.
[0004] According to one aspect of this application, a method for preparing a layered composite material for space-borne devices is provided, comprising:
[0005] The surfaces of the 2A12 aluminum alloy and tantalum plate are surface treated.
[0006] Rivet in the order of tantalum plate, 2A12 aluminum alloy, and additional layer;
[0007] The three riveted layers are then subjected to cold rolling composite with a single-pass deformation of 40-50% to obtain the final product.
[0008] The additional layer is selected from one of the following: 1-series alloys, 3-series aluminum alloys, copper, and low-carbon steel;
[0009] The additional layer is not surface treated;
[0010] The thickness of the additional layer is 2-3 mm.
[0011] According to some embodiments of this application, the thickness of the 2A12 aluminum alloy is 1-3 mm; the thickness of the tantalum plate is 0.5-2 mm.
[0012] According to some embodiments of this application, the width of the additional layer is 10-20 mm wider than the width of the 2A12 aluminum alloy.
[0013] According to some embodiments of this application, the length of the additional layer is 10-20 mm longer than the length of the 2A12 aluminum alloy.
[0014] According to some embodiments of this application, the surface treatment includes: acid and alkali washing and polishing.
[0015] According to some embodiments of this application, the temperature of the cold rolling composite is 25-35°C.
[0016] According to some embodiments of this application, a solid rolling lubricant is also applied between the additional layer and the 2A12 aluminum alloy.
[0017] According to some embodiments of this application, the rolling lubricant is paraffin wax.
[0018] According to another aspect of this application, a layered composite material for space devices prepared by the above-described preparation method is also provided, wherein the composite material comprises, in sequence: a tantalum plate, a 2A12 aluminum alloy, and an additional layer;
[0019] The additional layer is selected from one of the following: 1-series alloys, 3-series aluminum alloys, copper, and low-carbon steel;
[0020] The thickness of the additional layer is 2-3 mm.
[0021] Compared with the prior art, this application has at least the following beneficial effects:
[0022] This application provides a layered composite material for space-borne devices and its preparation method. An additional layer is added to the outside of the 2A12 aluminum alloy sheet, so that the 2A12 aluminum alloy sheet and the pure tantalum sheet do not crack during the rolling composite process, which greatly improves the material yield. Attached Figure Description
[0023] Figure 1 This is a schematic diagram of the layered composite material used in the spacecraft of this application.
[0024] Figure 2 This is a schematic diagram of the composite of 2A12 aluminum alloy and additional layer in this application.
[0025] Figure 3 The composite material is an example embodiment of this application.
[0026] Figure 4 The composite material is used as an example comparative example in this application.
[0027] Figure 5 The composite material is used as an example comparative example in this application. Detailed Implementation
[0028] The technical solution of this application will be clearly and completely described below with reference to the embodiments of this application. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0029] It should be particularly noted that similar substitutions and modifications made to this application are obvious to those skilled in the art, and they are all considered to be included in this application. Those skilled in the art can obviously make modifications or appropriate alterations and combinations to the methods and applications described herein without departing from the content, spirit, and scope of this application to implement and apply the technology of this application. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.
[0030] Unless otherwise specified, this application is conducted under standard conditions or conditions recommended by the manufacturer. The raw materials or excipients used, as well as the reagents or instruments used, whose manufacturers are not specified, are all conventional products that can be obtained commercially.
[0031] The following is a detailed description of this application.
[0032] Currently, radiation-resistant materials for space-based devices use aluminum / tantalum layered composite materials. The aluminum material is 2A12 aluminum alloy, and the tantalum is pure tantalum. Since 2A12 aluminum alloy is an Al-Cu alloy, its processing performance is poor, and edge cracking may occur during the rolling process.
[0033] During the rolling and lamination process of 2A12 aluminum alloy sheet and pure tantalum sheet, edge cracks may occur on the edges of the 2A12 aluminum alloy sheet. The tantalum sheet, affected by the 2A12 aluminum alloy sheet, may also experience edge cracks. Figure 5 As shown. Severe edge cracking during rolling can lead to extensive tearing of the composite material, such as... Figure 4 As shown. Regarding the aforementioned cracking problem, the cracked portion can be removed after rolling and compounding. However, for this product, the price of pure tantalum is very expensive (3-4 million RMB / ton). Extensive edge trimming would drastically increase material costs. Furthermore, if large-scale edge tearing occurs, the remaining material after trimming would be insufficient to meet product delivery requirements.
[0034] Edge cracks occur during the rolling process of 2A12 aluminum alloy, mainly due to ① the material itself being relatively brittle, and ② the edge being subjected to tensile stress in two directions and compressive stress in one direction during the rolling process. The edge cracks are caused by the larger tensile stress in the two directions.
[0035] The preparation method of this application can change the stress distribution of 2A12 aluminum alloy from the original 2-tension-1-compression to 2-compression-1-tension, which can significantly reduce the risk of edge cracking. This method can prevent edge cracking during the rolling composite process of 2A12 aluminum alloy sheet and pure tantalum sheet, greatly improving the material yield.
[0036] Based on this, this application provides a method for preparing a layered composite material for space-borne devices. An additional layer of 2-3 mm is laminated onto the outside of a 2A12 aluminum alloy sheet. The width of the additional layer is 10-20 mm wider than the 2A12 aluminum alloy sheet, and the 2A12 aluminum alloy sheet is placed in the middle of the additional layer. Figure 2 As shown.
[0037] The surface of the additional layer sheet is not surface treated (including acid and alkali washing and polishing), while the contact surfaces of the 2A12 aluminum alloy and tantalum plate are surface treated, including acid and alkali washing and steel brush polishing.
[0038] according to Figure 1 After assembly and riveting, the material is cold-rolled and composited, with a single-pass deformation of 40-45%. A solid rolling lubricant (usually paraffin wax) is applied between the additional layer and the 2A12 aluminum alloy.
[0039] The additional layer materials are selected from 1-series aluminum alloys, 3-series aluminum alloys, copper, low-carbon steel, and other materials.
[0040] The technical solution of this application will be further described below with reference to specific embodiments.
[0041] Example 1
[0042] The layered composite material for space-borne devices of this application was prepared.
[0043] Take 2A12 alloy: 200mm wide, 400mm long, and 3mm thick;
[0044] Tan layer: 200mm wide, 400mm long, 1mm thick;
[0045] O-temper 1 series aluminum alloy: width 300-350mm, length 450mm, thickness 2mm.
[0046] The 2A12 aluminum alloy and tantalum plate were sequentially pickled, alkali-washed, and polished.
[0047] After grinding, the tantalum plate, 2A12 aluminum alloy, and 1-series alloy are riveted in that order.
[0048] The riveted three-layer material is then subjected to room temperature cold rolling with a single-pass deformation of 40% to obtain (e.g.) Figure 3 (As shown).
[0049] Example 2
[0050] The layered composite material for space-borne devices of this application was prepared.
[0051] Take 2A12 alloy: 200mm wide, 400mm long, and 1mm thick;
[0052] Tan layer: 200mm wide, 400mm long, 0.5mm thick;
[0053] Low carbon steel plate: 300-350mm wide, 450mm long, 4mm thick.
[0054] The 2A12 aluminum alloy and tantalum plate were sequentially pickled, alkali-washed, and polished.
[0055] After grinding, the tantalum plate, 2A12 aluminum alloy, and low carbon steel plate are riveted in that order.
[0056] The three riveted materials are then subjected to room temperature cold rolling composite with a single-pass deformation of 45% to obtain the final product.
[0057] Example 3
[0058] The layered composite material for space-borne devices of this application was prepared.
[0059] Take 2A12 alloy: 200mm wide, 400mm long, and 2mm thick;
[0060] Tan layer: 200mm wide, 400mm long, 1.5mm thick;
[0061] Copper plate: 300-350mm wide, 450mm long, 3mm thick.
[0062] The 2A12 aluminum alloy and tantalum plate were sequentially pickled, alkali-washed, and polished.
[0063] After polishing, rivet the plates in the following order: tantalum plate, 2A12 aluminum alloy, and copper plate.
[0064] The three riveted materials are then subjected to room temperature cold rolling composite with a single-pass deformation of 50% to obtain the final product.
[0065] Comparative Example 1
[0066] The preparation steps are the same as in Example 1, except that no additional layer is added.
[0067] The 2A12 aluminum alloy and tantalum plate were sequentially pickled, alkali-washed, and polished.
[0068] Then the 2A12 aluminum alloy and tantalum plate are riveted together;
[0069] Cold rolling composite is performed at room temperature.
[0070] The deformation is 40%, such as Figure 5 As shown, edge cracks occurred on the 2A12 aluminum alloy, and slight edge cracks also occurred in the tantalum layer.
[0071] Comparative Example 2
[0072] The preparation steps are the same as in Example 1, except that no additional layer is added.
[0073] The 2A12 aluminum alloy and tantalum plate were sequentially pickled, alkali-washed, and polished.
[0074] Then the 2A12 aluminum alloy and tantalum plate are riveted together;
[0075] Cold rolling composite is performed at room temperature.
[0076] The deformation is 50%, such as Figure 4 As shown, the edge of the 2A12 aluminum alloy was severely torn, and the tantalum layer was also severely torn.
[0077] The above description of the embodiments is only for the purpose of helping to understand the method and core ideas of this application. It should be noted that, for those skilled in the art, several improvements and modifications can be made to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of the claims of this application.
Claims
1. A method for preparing a layered composite material for space-borne devices, characterized in that, include: The surfaces of the 2A12 aluminum alloy and tantalum plate are surface treated. Rivet in the order of tantalum plate, 2A12 aluminum alloy, and additional layer; The three riveted layers are then subjected to cold rolling composite with a single-pass deformation of 40-50% to obtain the final product. The additional layer is selected from one of 1-series aluminum alloys, 3-series aluminum alloys, copper, and low-carbon steel; The additional layer is not surface treated; The thickness of the additional layer is 2-3 mm.
2. The preparation method according to claim 1, characterized in that, The thickness of the 2A12 aluminum alloy is 1-3mm; the thickness of the tantalum plate is 0.5-2mm.
3. The preparation method according to claim 1, characterized in that, The width of the additional layer is 10-20 mm greater than the width of the 2A12 aluminum alloy.
4. The preparation method according to claim 1, characterized in that, The length of the additional layer is 10-20 mm longer than the length of the 2A12 aluminum alloy.
5. The preparation method according to claim 1, characterized in that, The surface treatment includes: acid and alkali washing and polishing.
6. The preparation method according to claim 1, characterized in that, The temperature for cold rolling composite is 25-35℃.
7. The preparation method according to claim 1, characterized in that, It also includes applying a solid rolling lubricant between the additional layer and the 2A12 aluminum alloy.
8. The preparation method according to claim 7, characterized in that, The rolling lubricant is paraffin wax.
9. A layered composite material for space devices prepared by any one of the preparation methods described in claims 1-8.