Space device anti-radiation thin layer composite material and preparation method thereof
By adding a fixing layer between the 2A12 aluminum alloy and the tantalum layer and using a rolling lubricant, and employing a cold rolling composite process, the problem of warping in thin-layer composite materials during rolling was solved, achieving the preparation of high-quality and high-precision composite materials.
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
During the rolling and composite process of existing radiation-resistant materials for space-based devices, the different deformation resistance of 2A12 aluminum alloy and pure tantalum leads to warping of thin-layer composite materials, making it difficult to maintain good flatness.
A fixing layer (such as 3-series aluminum alloy or low-carbon steel plate) is added between the 2A12 aluminum alloy and the tantalum layer, and rolling lubricant is used during the rolling process to control the rolling deformation at 35-50%. Cold rolling composite process is adopted to avoid warping.
The prepared radiation-resistant thin-layer composite material for space devices has high surface quality and dimensional accuracy, with a thickness of less than 1 mm, and does not warp after rolling, maintaining good flatness.
Smart Images
Figure CN117772790B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of composite materials for space-based devices, specifically to a radiation-resistant thin-film 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. Due to the different deformation resistance of 2A12 aluminum alloy and pure tantalum, the different fluidity of the two metals during the rolling composite process can cause the rolled composite material to warp. Summary of the Invention
[0003] To address the aforementioned deficiencies in this field, this application aims to provide a radiation-resistant thin-layer composite material for space-based devices and its preparation method, ensuring that the thin-layer 2A12 aluminum alloy sheet and the pure tantalum sheet do not warp after rolling and composite, maintaining good flatness.
[0004] According to one aspect of this application, a method for preparing a radiation-resistant thin-film composite material for space-based devices is provided, comprising:
[0005] The 2A12 aluminum alloy layer and the tantalum layer are respectively surface treated;
[0006] The surface-treated 2A12 aluminum alloy layer and tantalum layer are respectively combined with the fixing layer to obtain the fixing layer-2A12 aluminum alloy layer and the fixing layer-tantalum layer.
[0007] The fixed layer-2A12 aluminum alloy layer and the fixed layer-tantalum layer are rolled and annealed to obtain a fixed layer-2A12-tantalum layer-fixed layer thin-layer composite material.
[0008] The fixing layer does not undergo the aforementioned surface treatment;
[0009] The rolling composite includes:
[0010] When the deformation amount of a single rolling composite layer is ≤35%, the heads of the fixed layer-2A12 aluminum alloy layer and the fixed layer-tantalum layer are riveted together for rolling composite.
[0011] When the deformation amount of a single pass in the rolling composite is greater than 35%, rolling lubricant is applied between the fixed layer alloy and the 2A12 aluminum alloy, and between the fixed layer alloy and the tantalum layer, and the head is riveted to perform rolling composite.
[0012] According to some embodiments of this application, the fixing layer is selected from: 3-series aluminum alloy, copper plate or low carbon steel plate.
[0013] According to some embodiments of this application, the fixing layer is a 3-series aluminum alloy.
[0014] According to some embodiments of this application, the thickness of the radiation-resistant thin-layer composite material for the space-based device is less than 1 mm.
[0015] According to some embodiments of this application, the annealing temperature is 400-500℃ and the annealing time is 12-36h.
[0016] According to some embodiments of this application, the rolling process is cold rolling at 25-35°C.
[0017] According to some embodiments of this application, the rolling lubricant is paraffin wax.
[0018] According to some embodiments of this application, the thickness of the fixing layer is less than 5 mm. Optionally, the thickness of the fixing layer is 3 mm.
[0019] According to another aspect of this application, a radiation-resistant thin-film composite material for space devices prepared by the above-described preparation method is also provided.
[0020] Compared with the prior art, this application has at least the following beneficial effects:
[0021] A radiation-resistant thin-film composite material for satellite devices and its preparation method are disclosed. The preparation method of this application adopts cold rolling composite, which does not require complex rolling methods such as differential temperature or asynchronous rolling, and the preparation process is simple; moreover, the prepared composite material has high surface quality and dimensional accuracy.
[0022] The radiation-resistant thin-layer composite material for space-borne devices in this application has a thickness of less than 1 mm and does not warp after rolling and lamination, maintaining good flatness. Attached Figure Description
[0023] Figure 1 This is a schematic diagram of the structure of a thin-layer composite material in an example embodiment of this application.
[0024] Figure 2 This is a schematic diagram illustrating the warping of the composite material as an example of 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. Detailed Implementation
[0027] 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.
[0028] 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.
[0029] 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.
[0030] The following is a detailed description of this application.
[0031] The problem of warping of the radiation-resistant aluminum / tantalum layered composite material for current space-based devices after rolling is caused by the different deformation resistance.
[0032] When the thickness of the composite material after rolling exceeds 1.5mm, a leveling machine can be used to level it; when the thickness of the raw material 2A12 aluminum alloy sheet and pure tantalum sheet is relatively thick (generally both raw material sheets are thicker than 1.5mm), asynchronous rolling and differential temperature rolling can be used to roll and composite them.
[0033] However, for thin-layer composite materials, i.e., finished composite materials with a thickness of less than 1 mm, the leveling machine cannot level them, and due to their excessively thin original thickness, it is also difficult to use differential temperature and asynchronous rolling.
[0034] Based on the above problems, this application provides a method for preparing a radiation-resistant thin-layer composite material for space-based devices, which can prevent warping of thinner 2A12 aluminum alloy plates and pure tantalum plates after rolling and composite bonding, and maintain good flatness.
[0035] The method for preparing the radiation-resistant layered composite material for thin-gauge spacecraft devices disclosed in this application involves adding a 2-3 mm thick fixing layer to the outermost layer before compositing the 2A12 aluminum alloy and tantalum. The fixing layer can be made of 3-series aluminum alloy sheet, the surface of which is not surface-treated (including acid and alkali washing and polishing). The contact surfaces of the 2A12 aluminum alloy and tantalum sheet are both surface-treated, including acid and alkali washing and steel brush polishing. The four layers are then rolled together, with a rolling deformation of 35-50%.
[0036] When the deformation amount of a single pass in the rolling composite is ≤35%, the heads of the four layers of materials can be directly riveted together for rolling composite.
[0037] When the deformation amount of a single rolling pass is greater than 35%, a solid rolling lubricant (usually paraffin wax) should be applied between the 3-series aluminum alloy and the 2A12 aluminum alloy, and between the 3-series aluminum alloy and Ta, to ensure that the 3-series aluminum alloy and the 2A12 aluminum alloy, and the 3-series aluminum alloy and Ta will not stick during the rolling composite process. Then the heads of the four layers of materials can be directly riveted together for rolling composite.
[0038] The technical solution of this application will be described in detail below with reference to specific embodiments.
[0039] Example 1
[0040] The radiation-resistant thin-film composite material for space-borne devices of this application was prepared with 2A12: 1 mm, Ta: 0.8 mm, and a fixing layer of 3-series aluminum alloy with a deformation of 45%. The preparation steps are as follows:
[0041] The 2A12 aluminum alloy layer and the tantalum layer are respectively surface treated;
[0042] The surface-treated 2A12 aluminum alloy layer is riveted to the 3-series aluminum alloy.
[0043] The surface-treated tantalum layer is riveted to the 3-series aluminum alloy.
[0044] Apply paraffin lubricant between 3-series aluminum alloys and 2A12 aluminum alloys, and between 3-series aluminum alloys and Ta.
[0045] Following the sequence of 3-series aluminum alloy - 2A12 - tantalum layer - 3-series aluminum alloy, the heads of the four layers of materials are directly riveted together, and a single-pass cold rolling composite with a deformation of 45% is carried out at room temperature.
[0046] The finished composite material has a thickness of 0.99 mm and can be subjected to heat treatment at 500℃ for 24 hours.
[0047] Example 2
[0048] The radiation-resistant thin-film composite material for space-borne devices of this application was prepared with 2A12: 0.9 mm, Ta: 0.8 mm, and a low-carbon steel plate as the fixing layer, with a deformation of 35%. The preparation steps are as follows:
[0049] The 2A12 aluminum alloy layer and the tantalum layer are respectively surface treated;
[0050] The surface-treated 2A12 aluminum alloy layer is riveted to the low-carbon steel plate.
[0051] The surface-treated tantalum layer is riveted to the low-carbon steel plate.
[0052] Apply paraffin lubricant between the low-carbon steel plate and the 2A12 aluminum alloy, and between the low-carbon steel plate and Ta.
[0053] Following the sequence of low-carbon steel plate - 2A12 - tantalum layer - low-carbon steel plate, the heads of the four layers of materials are directly riveted together, and a single-pass cold rolling composite with a deformation of 35% is carried out at room temperature.
[0054] The finished composite material has a thickness of 0.98 mm and can be subjected to heat treatment at 400℃ for 30 hours.
[0055] Comparative Example
[0056] A radiation-resistant thin-film composite material for space-borne devices was prepared, with 2A12: 1 mm, Ta: 0.8 mm, and a deformation of 45%. The preparation steps are as follows:
[0057] The 2A12 aluminum alloy layer and the tantalum layer are respectively surface treated;
[0058] The surface-treated 2A12-tantalum layers were directly riveted together and then subjected to single-pass cold rolling composite with a deformation of 45% at room temperature.
[0059] The finished composite material has a thickness of 0.99 mm and is subsequently subjected to heat treatment at 500℃ for 24 hours.
[0060] like Figure 4 As shown, the material is warped and, due to its small thickness, cannot be straightened using a leveling machine.
[0061] 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 radiation-resistant thin-film composite material for space-based devices, characterized in that, include: The 2A12 aluminum alloy layer and the tantalum layer are respectively surface treated; The surface-treated 2A12 aluminum alloy layer and tantalum layer are respectively combined with the fixing layer to obtain the fixing layer-2A12 aluminum alloy layer and the fixing layer-tantalum layer. The fixed layer-2A12 aluminum alloy layer and the fixed layer-tantalum layer are rolled and annealed to obtain a fixed layer-2A12-tantalum layer-fixed layer thin-layer composite material. The fixing layer does not undergo the aforementioned surface treatment; The rolling composite includes: When the deformation amount of a single rolling composite layer is ≤35%, the heads of the fixed layer-2A12 aluminum alloy layer and the fixed layer-tantalum layer are riveted together for rolling composite. When the deformation amount of a single pass in the rolling composite is greater than 35%, rolling lubricant is applied between the fixed layer alloy and the 2A12 aluminum alloy, and between the fixed layer alloy and the tantalum layer, and the head is riveted to perform rolling composite. The thickness of the radiation-resistant thin-layer composite material for the space-borne device is less than 1 mm; The rolling composite is a cold rolling composite.
2. The preparation method according to claim 1, characterized in that, The fixing layer is selected from: 3-series aluminum alloy, copper plate or low carbon steel plate.
3. The preparation method according to claim 2, characterized in that, The fixing layer is made of 3-series aluminum alloy.
4. The preparation method according to claim 1, characterized in that, The annealing temperature is 400-500℃, and the annealing time is 12-36h.
5. The preparation method according to claim 1, characterized in that, The rolling process is cold rolling at 25-35℃.
6. The preparation method according to claim 1, characterized in that, The rolling lubricant is paraffin wax.
7. The preparation method according to claim 1, characterized in that, The thickness of the fixing layer is less than 5 mm.
8. The preparation method according to claim 1, characterized in that, The thickness of the fixing layer is 3mm.
9. A radiation-resistant thin-film composite material for space devices prepared by any one of the preparation methods described in claims 1-8.