WO2018058306A1 - 一种钎焊蜂窝板用铝合金复合面板材料及其制造方法 - Google Patents

一种钎焊蜂窝板用铝合金复合面板材料及其制造方法 Download PDF

Info

Publication number
WO2018058306A1
WO2018058306A1 PCT/CN2016/100360 CN2016100360W WO2018058306A1 WO 2018058306 A1 WO2018058306 A1 WO 2018058306A1 CN 2016100360 W CN2016100360 W CN 2016100360W WO 2018058306 A1 WO2018058306 A1 WO 2018058306A1
Authority
WO
WIPO (PCT)
Prior art keywords
aluminum alloy
alloy
panel
layer
thickness
Prior art date
Application number
PCT/CN2016/100360
Other languages
English (en)
French (fr)
Inventor
周德敬
李龙
夏承东
吕金明
Original Assignee
银邦金属复合材料股份有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 银邦金属复合材料股份有限公司 filed Critical 银邦金属复合材料股份有限公司
Priority to PCT/CN2016/100360 priority Critical patent/WO2018058306A1/zh
Publication of WO2018058306A1 publication Critical patent/WO2018058306A1/zh

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure

Definitions

  • the invention relates to a high-strength aluminum alloy composite panel material for brazing honeycomb panels and a manufacturing method thereof.
  • the aluminum alloy honeycomb panel has excellent performances such as sound insulation, heat insulation, shock absorption, energy absorption and electromagnetic shielding. It can be used for car (cabin) doors, floors, roofs, etc. in rail transportation, new energy vehicles, construction, shipbuilding, aerospace and other fields. Side panels, skirts and partitions. At present, the common aluminum honeycomb manufacturing at home and abroad is mostly adhesive structure. Its strength (stability), service life and allowable application environment are restricted by the performance of the adhesive, poor temperature resistance, aging and cracking of the adhesive, and release of toxic gases in case of fire. It is difficult to apply on rail vehicles or other high-end equipment.
  • the invention discloses a method for manufacturing a brazed metal honeycomb panel, which is formed by soldering a honeycomb core by adding a flux on a side of the front and rear panels in contact with the honeycomb core, and the method realizes metallurgical bonding of the whole metal.
  • the mechanical properties of the honeycomb panel are not only higher than the adhesive structure of the same specification, but also completely overcome the defects of high temperature difference, adhesive aging and the like of the adhesive aluminum honeycomb panel.
  • the 3 series aluminum alloy is a good and commonly used aluminum honeycomb panel material.
  • the 3 series aluminum alloy has good high temperature strength due to the inclusion of Mn, so that the brazed workpiece is not easily deformed under high temperature conditions, and the yield strength after brazing is generally 40-60 MPa.
  • the demand for lightweight in engineering applications is becoming more and more intense, and the application of aluminum honeycomb panels is becoming more and more extensive.
  • the development of lighter and thinner aluminum honeycomb panels has become an important research direction of aluminum honeycomb panels. Due to weight reduction and thickness reduction, the brazing sheet is required to have a higher strength under the same load or stress conditions to prevent deformation or even cracking during subsequent brazing or use.
  • the strength of the existing 3 series aluminum alloy panels can not fully meet the above requirements of weight reduction and thickness reduction, so developing a higher strength brazable aluminum alloy sheet is an effective way to achieve weight reduction of the honeycomb panel.
  • Mg metal to create solid solution strengthening or to form second phase particles with other elements to increase the strength of the brazing sheet.
  • the vapor pressure of Mg is large, and the Mg-containing alloy is easily evaporated by heat during the brazing process, and diffuses to the surface of the aluminum alloy to form MgO.
  • the mixture of the MgO and the aluminum surface Al 2 O 3 has extremely low solubility in the flux and is not easily dissolved, thereby greatly reducing the fluidity of the solder.
  • Mg also easily forms a compound such as MgF 2 , KMgF 3 , K 2 MgF 4 with a flux to increase the melting point of the flux and lose its activity.
  • Mg-containing aluminum alloy parts are not suitable for connection by carrier gas brazing, but vacuum brazing should be used.
  • vacuum brazing can obtain high-quality devices, the production process must be heated and brazed in a near-vacuum (3.5 ⁇ 10 -3 Pa) closed furnace, and the production efficiency is extremely low.
  • the carrier gas brazing can be continuously produced under the protection of inert gas, and the production efficiency is high, and the brazed defective product can be subjected to secondary brazing, so the yield is as high as 99%.
  • the use of carrier gas brazing aluminum alloy parts with high Mg content has become a new research direction.
  • the present invention provides an aluminum alloy composite panel material for brazing honeycomb panels and a manufacturing method thereof, wherein the panel material has a high Mg content.
  • the carrier gas brazing of the composite sheet is realized, thereby realizing high production efficiency of light and thin honeycomb sheets and high-yield brazing production.
  • the invention discloses an aluminum alloy composite panel material for brazing honeycomb panels, comprising a skin material layer aluminum alloy and a core material layer aluminum alloy, and a first cladding layer aluminum alloy and a second cladding layer aluminum alloy, and The skin material layer aluminum alloy, the first cladding layer aluminum alloy, the core material layer aluminum alloy and the second cladding layer aluminum alloy are sequentially compounded into a sheet material;
  • the leather material layer aluminum alloy contains 7.0- 10.5% of Si, the balance being Al and less than 0.5% of unavoidable impurities;
  • the material of the first cladding layer aluminum alloy and the second cladding layer aluminum alloy containing 0-0.7% of Cu, 1.1-1.7 % Mn, 0-1.7% Zn, 0-0.2% Ti, 0-0.8% Si, the balance being Al and less than 0.15% of unavoidable impurities;
  • the core layer aluminum alloy contains 0.3-3.0%
  • the core material layer has a thickness ratio of 70% or more.
  • the invention may also include the following preferred solutions:
  • the skin material layer aluminum alloy has a thickness of 40 to 200 ⁇ m.
  • the first cladding layer aluminum alloy and the second cladding layer aluminum alloy each have a thickness of 50-100 ⁇ m.
  • the sheet has a final thickness of 1-3 mm.
  • the material of the core material aluminum alloy may be composed of the following four types of alloys:
  • the core material layer aluminum alloy material contains 0.7-2.0% Cu, 0.3-1.0% Mn, 0.3-1.0% Mg, 0.2-0.5% Zn, 0.1-0.3% Ti, 0.3- 0.8% Fe, 0.5-1.2% Si, the balance being Al and less than 0.15% of unavoidable impurities.
  • the core material layer aluminum alloy material contains 0.04-0.2% Cu, 0.1-0.65% Mn, 1.0-3.0% Mg, 0.05-0.3% Zn, 0.05-0.25% Cr, 0- The total content of 0.2% Ti, Fe and Si is less than 0.8%, and the balance is Al and less than 0.15% of unavoidable impurities.
  • the core material layer aluminum alloy material contains 0.2-0.7% Cu, 0.1-0.8% Mn, 0.3-1.2% Mg, 0.08-0.2% Ti, 0.3-1.2% Si, 0.2- 0.8% Fe, the balance being Al and less than 0.15% of unavoidable impurities.
  • the core material layer aluminum alloy material contains 0.1-1.0% Cu, 0.1-0.5% Mn, 1.0-3.0% Mg, 3.0-7.0% Zn, 0.05-0.35% Cr, 0.05-0.2 % Ti, 0.05-0.25% Zr, the sum of Fe and Si content is lower than 0.7%, the balance being Al and less than 0.15% of unavoidable impurities.
  • the invention also discloses a manufacturing method for manufacturing the high-strength aluminum alloy composite panel material for the brazed honeycomb panel, comprising the following steps:
  • Alloy casting aluminum material of the skin layer, aluminum alloy of the first cladding layer, aluminum alloy of the core layer and aluminum alloy of the second cladding layer are respectively cast into a billet and surface-treated;
  • Composite hot rolling the surface treated leather alloy ingot, the first cladding alloy ingot and the second cladding alloy ingot are hot rolled to a certain thickness, and then stacked with the core layer alloy ingot in order And bundling, after multiple passes hot rolling to a thickness of 5-10mm, the final rolling temperature is greater than 300 ° C, and then air-cooled;
  • Annealing The composite cold rolled coil is annealed and insulated to obtain a high strength aluminum alloy composite panel material for the brazed honeycomb panel.
  • the annealing step has an annealing temperature of 360-380 ° C and is incubated for 2-4 h after warming.
  • the present invention has the following beneficial effects:
  • a material containing elements such as Cu, Mn, Mg, Zn, Cr, etc. is added as a core material layer to the composite material, and the thickness ratio thereof is more than 70%, and the alloy is solid solution strengthened during hot working, heat treatment and brazing process or
  • the second phase strengthening method produces a strengthening effect, thereby improving the strength of the composite sheet, and the yield strength of the sheet after welding is up to 117 MPa, which is greatly improved from the 40-60 MPa of the yield strength of the conventional brazing sheet; the first cladding layer and the second cladding layer
  • the two sides of the core material layer are coated to prevent the Mg element in the core material layer from diffusing to the welding interface during the material preparation process and the subsequent brazing process, completely avoiding the reaction of the Mg element with the flux to form a high melting point during the brazing process.
  • the compound is inactive and cannot be brazed. Therefore, the Mg-containing alloy composite sheet can still be brazed with other components, and has the advantages of high production efficiency and high yield.
  • 1 is a schematic view showing the structure of an interlayer of an aluminum alloy composite panel of the present invention.
  • the present invention provides an aluminum alloy composite panel material for brazing honeycomb panels, including a leather layer aluminum alloy and a core. a layer of aluminum alloy, further comprising a first cladding layer aluminum alloy and a second cladding layer aluminum alloy, the skin material layer aluminum alloy, the first cladding layer aluminum alloy, the core material layer aluminum alloy and The second cladding layer aluminum alloy is sequentially compounded into a sheet; the leather layer The aluminum alloy contains 7.0-10.5% Si, and the rest is Al and less than 0.5% of unavoidable impurities; the first cladding aluminum alloy and the second cladding aluminum alloy have 0-0.7% of material Cu, 1.1-1.7% Mn, 0-1.7% Zn, 0-0.2% Ti, 0-0.8% Si, the balance being Al and less than 0.15% of unavoidable impurities; the core layer aluminum alloy It contains 0.3-3.0% of Mg, and the
  • the composite panel material is a four-layer aluminum alloy composite board, which can be used as a panel material of a honeycomb panel, including the top layer of the aluminum alloy 1 and the first package which are combined from top to bottom as shown in FIG. 1 .
  • the aluminum alloy 1 of the skin material layer contains 7.0-10.5% of Si.
  • the leather material of the composite material in the invention is mainly used for the brazing process to realize the metallurgical connection between the panel material and the aluminum honeycomb, so that the stripping strength is extremely high. If the thickness of the aluminum alloy of the skin material layer is less than 40 ⁇ m, the brazing material is too small to effectively connect the high-strength sheet material and the aluminum honeycomb; if the thickness of the aluminum alloy material layer is higher than 200 ⁇ m, the thickness ratio of the aluminum alloy in the composite sheet is Too large, reducing the thickness ratio of other alloy layers, resulting in poor reinforcement. Therefore, it is preferred that the single layer skin material has a thickness of 40 to 200 ⁇ m.
  • the first cladding layer aluminum alloy 2 and the second cladding layer aluminum alloy 4 are composited on both sides of the core material layer aluminum alloy 3, and the core layer aluminum alloy 3 is coated to be isolated from the outside.
  • the coating according to the present invention refers to the coating of the core material layer on both sides. Since the thickness of the composite material is only millimeters, the sections of the core material layer are exposed to the air, which is negligible.
  • the material of the first cladding layer aluminum alloy 2 and the second cladding layer aluminum alloy 4 may be the same or different, and any one of the above components may satisfy the cladding core layer aluminum alloy 3, and Requirements for composite with leather layer aluminum alloy 1.
  • the single-layer core material 1 has a thickness of 50 to 100 ⁇ m, which can effectively prevent Mg from diffusing to the skin material or the surface, and can also ensure the thickness of the core material layer aluminum alloy 3 as much as possible to produce an optimum strengthening effect.
  • the Mg element in the core layer aluminum alloy 3 is solid-solution-formed in the Al matrix to cause solid solution strengthening, or to form Al 2 CuMg or Mg 2 Si or MgZn 2 , etc.
  • the small second phase produces a strengthening effect, thereby greatly improving the strength of the aluminum alloy composite sheet before and after welding.
  • the core material aluminum alloy 3 alloy of the present invention can be composed of the following four types of alloys, and the effect of improving the strength of the final sheet can be obtained:
  • the main alloying element Mg has a great influence on the melting point of the alloy, and when the content thereof is higher than 3.0%, the melting point of the alloy is lowered to 600 ° C or lower, thereby causing subsequent During the brazing process, the alloy has the risk of being scrapped or over-burned and scrapped; when the Mg content is less than 1.0%, the amount of MgZn 2 strengthening phase is too small and does not contribute significantly to the strength.
  • the aluminum alloy 3 is coated with a layer of aluminum alloy on the upper and lower layers of the core material layer 3 to prevent processing, heat treatment and brazing.
  • Mg elements diffuse to the surface of the skin or material to affect the deterioration of brazing.
  • Another object of the present invention is to provide a method for producing a high-strength composite sheet material for carrier gas brazing, that is, a method for producing a high-strength aluminum alloy composite panel material for brazing honeycomb sheets.
  • the composite sheet is melt-casted by various alloys, combined in the order and ratio shown in Fig. 1, large-deformation hot-rolling, cold-rolling and annealing to produce a finished panel material having a final thickness of 1-3 mm.
  • the method for manufacturing a high-strength aluminum alloy composite panel material for brazing honeycomb panels disclosed in the present invention comprises the following steps:
  • Alloy casting respectively, taking the aluminum alloy material layer, the first cladding layer aluminum alloy, the core material layer aluminum alloy and the second cladding layer aluminum alloy raw material into a billet;
  • Composite hot rolling the surface treated leather alloy ingot, the first cladding alloy ingot and the second cladding alloy ingot are hot rolled to a certain thickness, and then stacked with the core layer alloy ingot in order Putting and bundling, hot rolling to a thickness of 5-10mm, final rolling temperature of more than 300 ° C, and then air-cooling;
  • Annealing The composite cold rolled coil is annealed and insulated to obtain a high strength aluminum alloy composite panel material for the brazed honeycomb panel.
  • the annealing temperature is 360-380 ° C and is kept for 2-4 h.
  • the leather alloy ingot, the first cladding alloy ingot and the second cladding aluminum alloy ingot are hot rolled to a certain thickness, which means that the skin material alloy ingot, the first A cladding alloy ingot and a second cladding aluminum alloy ingot are hot rolled to a thick plate of 17 to 40 mm to facilitate compounding with the core layer alloy ingot.
  • Annealing The composite cold rolled coil is kept in a 360 ° C annealing furnace for 4 h, and the carrier-gas brazed high-strength composite sheet according to the present invention is obtained by air cooling.
  • the thickness of the AA4045 alloy was about 92 ⁇ m
  • the thickness of the single-layer AA3003Mod alloy was about 60 ⁇ m.
  • the aluminum alloy composite sheet prepared by the present embodiment is simulated and brazed, and the simulated brazing process is heated to 600 ° C for 24 min, kept for 10 min, and the protective atmosphere is argon.
  • the test results show that the brazing joint effect is good, and the mechanical properties before and after brazing are shown in Table 1.
  • the yield strength after brazing is increased to a certain extent before welding, up to 88 MPa, while the yield strength of ordinary 4 series/3 series aluminum alloy brazing sheets is only 40-60 MPa.
  • AA4343, AA3003Mod and AA5052 alloys were cast according to their respective standard components, and the ingot size was 450 ⁇ 1450 ⁇ 4800 mm. Among them, AA4343 contains 7.4% Si, the rest is Al and less than 0.5% of unavoidable impurities; AA3003Mod alloy contains 1.6% Mn, 0.65% Cu, 0.12% Fe, 0.13% Zr, 0.04% Ti, and the rest Al and less than 0.15% of unavoidable impurities; AA5052 alloy contains 2.6% Mg, 0.15% Si, 0.02% Ti, 0.25% Cr, 0.3% Fe, and the balance is Al and less than 0.15% of unavoidable impurities.
  • Annealing The composite cold rolled coil is kept in a 370 ° C annealing furnace for 4 h, and air-cooled to obtain the carrier-gas brazed high-strength composite sheet of the present invention.
  • the thickness of the AA4343 alloy was about 68 ⁇ m
  • the thickness of the single-layer AA3003Mod alloy was about 54 ⁇ m.
  • test results of the mechanical properties before and after the simulated brazing of the aluminum alloy composite sheet prepared in this example are shown in Table 2.
  • the simulated brazing process was carried out by heating to 600 ° C for 24 min, holding for 10 min, and the protective atmosphere was argon. Test results show the plate The brazing joint has a good effect, and the yield strength after welding is 84 MPa, while the ordinary 4 series/3 series aluminum alloy brazing sheet has a yield strength of only 40-60 MPa.
  • AA4045, AA3003Mod and AA6A02 alloys were respectively cast according to their respective standard components, and the ingot size was 400 ⁇ 1120 ⁇ 5100 mm.
  • the AA4045 alloy contains 10.4% Si, the rest is Al and less than 0.5% of unavoidable impurities;
  • the AA3003Mod alloy contains 1.6% Mn, 0.65% Cu, 0.12% Fe, 0.1% Ti, and the rest is Al and less than 0.15.
  • AA6A02 alloy contains 1.1% Si, 0.7% Mg, 0.25% Mn, 0.25% Cu, 0.3% Fe, 0.13% Ti, the balance is Al and less than 0.15% of unavoidable impurities .
  • Annealing The composite cold rolled coil is kept in a 380 ° C annealing furnace for 2 h, and air-cooled to obtain the carrier-gas brazed high-strength composite sheet according to the present invention.
  • the thickness of the AA4045 alloy was about 145 ⁇ m
  • the thickness of the single-layer AA3003Mod alloy was about 98 ⁇ m.
  • the test results of the mechanical properties before and after the simulated brazing of the aluminum alloy composite sheet prepared in this example are shown in Table 2.
  • the simulated brazing process was carried out by heating to 600 ° C for 24 min, holding for 10 min, and the protective atmosphere was argon.
  • the results show that the argon gas protection welding effect is good, the yield strength after welding can reach 85MPa, and the ordinary 4 series/3 series aluminum alloy brazing sheet yield strength is only 40-60MPa.
  • AA4343, AA3003Mod and AA7005 alloys were respectively cast according to their respective standard components, and the ingot size was 450 ⁇ 1450 ⁇ 4800 mm. Among them, AA4343 contains 7.4% Si, the rest is Al and less than 0.5% of unavoidable impurities; AA3003Mod alloy contains 1.48% Mn, 0.35% Cu, 0.22% Fe, 0.15% Ti, and the rest is Al and less than 0.15%. Inevitable impurities; AA7005 alloy contains 4.45% Zn, 1.45% Mg, 0.65% Mn, 0.02% Ti and 0.08% Cr, the balance being Al and less than 0.25% of unavoidable impurities.
  • the test results of mechanical properties before and after simulated brazing of the aluminum alloy composite sheet prepared in this example are shown in Table 1.
  • the simulated brazing process was carried out by heating to 600 ° C for 24 min, holding for 10 min, and the protective atmosphere was argon.
  • the test results show that the brazing joint effect is good, the yield strength after welding is 117 MPa, and the yield strength of the ordinary 4 series/3 series aluminum alloy brazing sheet is only 40-60 MPa.

Landscapes

  • Laminated Bodies (AREA)

Abstract

一种钎焊蜂窝板用铝合金复合面板材料及其制造方法。其包括皮材层铝合金和芯材层铝合金，还包括第一包覆层铝合金和第二包覆层铝合金，以皮材层铝合金、第一包覆层铝合金、芯材层铝合金和第二包覆层铝合金的顺序复合为板材；皮材层铝合金中含有7.0-10.5％的Si，其余为Al和小于0.5％的不可避免杂质；第一包覆层铝合金述第二包覆层铝合金的材质中含有0-0.7％的Cu，1.1-1.7％的Mn，0-1.7％的Zn，0-0.2％的Ti，0-0.8％的Si，其余为Al和小于0.15％的不可避免杂质；芯材层铝合金中含有0.3-3.0％的Mg，芯材层的厚度占比为70％以上。制造方法包括将原料合金熔铸、按顺序和厚度比例复合、大变形量热轧、冷轧和退火，制成复合板材成品。

Description

一种钎焊蜂窝板用铝合金复合面板材料及其制造方法 技术领域
本发明涉及一种钎焊蜂窝板用高强度铝合金复合面板材料及其制造方法。
背景技术
铝合金蜂窝板具有隔音、隔热、减震、吸能、电磁屏蔽等优异性能，可用于轨道交通、新能源汽车、建筑、船舶、航空航天等领域的车(舱)门、地板、顶板、侧板、裙板和间壁等诸多部位。目前，国内外常见的铝蜂窝制造多为胶粘结构，其强度(刚度)、使用寿命以及允许的应用环境受胶粘剂性能的制约，耐温性差、黏胶老化开裂、遇火灾释放有毒气体等，难以在轨道交通车辆或其它一些高端设备上开展应用。现有一种钎焊式金属蜂窝板的制造方法，通过在前、后面板与蜂窝芯接触的一面添加焊剂的方式，实现与蜂窝芯钎焊成一体，该方法实现了全金属的冶金结合，得到的蜂窝板的力学性能不仅高于同规格的胶粘结构，同时完全克服胶粘铝蜂窝板耐高温差、黏胶老化等缺陷。
3系铝合金是现有良好的、常用的铝蜂窝板面板材料。3系铝合金因含Mn而具有较好的高温强度，使得钎焊工件在高温条件下不易变形，其钎焊后屈服强度一般在40-60MPa。目前工程应用领域轻量化的需求日趋强烈，铝蜂窝板应用越来越广泛，开发更轻更薄的铝蜂窝板成为了铝蜂窝板的重要研究方向。由于重量减轻和厚度减薄，这就要求钎焊板材在相同载荷或受力条件下材料具有更高的强度，以防止其在后续钎焊过程或使用过程中变形甚至开裂。现有的3系铝合金面板的强度已不能完全满足上述重量减轻和厚度减薄的要求，因此开发更高强度的可钎焊铝合金板材是实现蜂窝板轻量化的有效途径。
业内人士通常在铝中添加Mg以产生固溶强化或与其它元素形成第二相颗粒来提高钎焊板材的强度。然而Mg的蒸气压大，含Mg的合金在钎焊过程中Mg易受热而蒸发出来，扩散至铝合金表面而形成MgO。该MgO和铝表面Al2O3的混合物在钎剂中的溶解度极低，不易溶解，因此大大降低钎料的流动性。此外，Mg还易与钎剂形成MgF2、KMgF3、K2MgF4等化合物，使钎剂熔点升高而失去活性。因此，实际生产过程中，含Mg的铝合金零部件不适合采用载气钎焊方式进行连接，而应采用真空钎焊方式。真空钎焊虽然可以获得高质量的器件，然而其生产过程必须在近真空状态的(3.5×10-3Pa)封闭式炉体中升温钎焊，生产效率极低。而载气钎焊则可以在惰性气体保护下，可以实现连续生产，生产效率高，且钎焊不良品可以进行二次钎焊，因此成品率高达99％。基于Mg元素对合金强度的有利影响及 载气钎焊方式的优势，采用载气钎焊高Mg含量的铝合金零部件成为当前研究的新方向。
发明内容
为了解决现有铝合金复合材料由于厚度减薄而不能满足铝蜂窝板强度要求的问题，本发明提供了一种钎焊蜂窝板用铝合金复合面板材料及其制造方法，面板材料中Mg含量高，在显著提高板材强度的同时，实现复合板材的载气钎焊，从而实现轻、薄蜂窝板的高生产效率、高成品率的钎焊生产。
本发明是通过如下技术方案实现的：
本发明公开一种钎焊蜂窝板用铝合金复合面板材料，包括皮材层铝合金和芯材层铝合金，以及第一包覆层铝合金和第二包覆层铝合金，且以所述皮材层铝合金、所述第一包覆层铝合金、所述芯材层铝合金和所述第二包覆层铝合金的顺序复合为板材；所述皮材层铝合金中含有7.0-10.5％的Si，其余为Al和小于0.5％的不可避免杂质；所述第一包覆层铝合金和所述第二包覆层铝合金的材质中含有0-0.7％的Cu，1.1-1.7％的Mn，0-1.7％的Zn，0-0.2％的Ti，0-0.8％的Si，其余为Al和小于0.15％的不可避免杂质；所述芯材层铝合金中含有0.3-3.0％的Mg，所述芯材层的厚度占比为70％以上。
本发明还可包括如下优选方案：
优选地，所述皮材层铝合金的厚度为40-200μm。所述第一包覆层铝合金和所述第二包覆层铝合金的厚度均为50-100μm。所述的板材最终厚度为1-3mm。
所述芯材层铝合金的材质可以分别由以下四类合金构成：
1)所述芯材层铝合金的材质中含有0.7-2.0％的Cu，0.3-1.0％的Mn，0.3-1.0％的Mg，0.2-0.5％的Zn，0.1-0.3％的Ti，0.3-0.8％的Fe，0.5-1.2％的Si，其余为Al和小于0.15％的不可避免杂质。
2)所述芯材层铝合金的材质中含有0.04-0.2％的Cu，0.1-0.65％的Mn，1.0-3.0％的Mg，0.05-0.3％的Zn，0.05-0.25％的Cr，0-0.2％的Ti，Fe和Si含量总和低于0.8％，其余为Al和小于0.15％的不可避免杂质。
3)所述芯材层铝合金的材质中含有0.2-0.7％的Cu，0.1-0.8％的Mn，0.3-1.2％的Mg，0.08-0.2％的Ti，0.3-1.2％的Si，0.2-0.8％的Fe，其余为Al和小于0.15％的不可避免杂质。
4)所述芯材层铝合金的材质中含有0.1-1.0％的Cu，0.1-0.5％的Mn，1.0-3.0％的Mg，3.0-7.0％的Zn，0.05-0.35％Cr，0.05-0.2％的Ti，0.05-0.25％Zr，Fe和Si含量总和低于 0.7％，其余为Al和小于0.15％的不可避免杂质。
本发明还公开一种制造方法，用于制造上述钎焊蜂窝板用高强度铝合金复合面板材料，包括如下步骤：
合金熔铸：分别取皮材层铝合金、第一包覆层铝合金、芯材层铝合金和第二包覆层铝合金原料熔铸成坯锭，并作表面处理；
复合热轧：经表面处理后的皮材合金铸锭、第一包覆层合金铸锭和第二包覆层合金铸锭热轧至一定厚度，然后与芯材层合金铸锭按顺序叠放并捆扎，经多道次热轧至厚度为5-10mm，终轧温度大于300℃，然后打卷空冷；
冷轧：经多道次冷精轧至最终厚度；
退火：复合材料冷轧卷退火、保温，得到所述钎焊蜂窝板用高强度铝合金复合面板材料。
优选地，所述退火步骤的退火温度为360-380℃，到温后保温2-4h。
本发明与现有技术相比，本发明的有益效果在于：
将含Cu、Mn、Mg、Zn、Cr等元素的材质作为芯材层添加至复合材料中，其厚度比例占70％以上，该合金在热加工、热处理和钎焊过程中通过固溶强化或第二相强化方式产生强化作用，从而提高复合板材的强度，板材焊后屈服强度可达117MPa，比常规钎焊板材屈服强度的40-60MPa大幅提高；第一包覆层和第二包覆层将芯材层的两面包覆隔绝，防止芯材层铝合金中Mg元素在材料制备过程和后续钎焊过程中扩散至焊接界面，完全避免了钎焊过程中Mg元素与钎剂反应形成高熔点化合物失去活性而无法钎焊连接。因此该含Mg元素合金复合板材仍然可以与其它零部件进行载气钎焊连接，具有生产效率高和成品率高的优点。
附图说明
图1为本发明铝合金复合面板层间结构示意图。
具体实施方式
为了解决现有铝合金复合材料在厚度减薄的情况下不能满足铝蜂窝板强度要求的问题，本发明提供了一种钎焊蜂窝板用铝合金复合面板材料，包括皮材层铝合金和芯材层铝合金，还包括第一包覆层铝合金和第二包覆层铝合金，以所述皮材层铝合金、所述第一包覆层铝合金、所述芯材层铝合金和所述第二包覆层铝合金的顺序复合为板材；所述皮材层 铝合金中含有7.0-10.5％的Si，其余为Al和小于0.5％的不可避免杂质；所述第一包覆层铝合金和所述第二包覆层铝合金的材质中含有0-0.7％的Cu，1.1-1.7％的Mn，0-1.7％的Zn，0-0.2％的Ti，0-0.8％的Si，其余为Al和小于0.15％的不可避免杂质；所述芯材层铝合金中含有0.3-3.0％的Mg，所述芯材层的厚度占比为70％以上。
下面以图1为例，对本发明的钎焊蜂窝板用高强度铝合金复合面板材料的结构和成分进行说明。
如图1所示，复合面板材料为四层铝合金复合的板材，可用作为蜂窝板的面板材料，包括图1所示的由上至下复合在一起的皮材层铝合金1、第一包覆层铝合金2、芯材层铝合金3、第二包覆层铝合金4。
其中皮材层铝合金1中含有7.0-10.5％的Si。本发明中复合材料的皮材，主要用于钎焊过程实现面板材料与铝蜂窝通过冶金方式连接，使其具有极高的剥离强度。该皮材层铝合金的厚度若低于40μm，其钎料过少而不能有效连接高强度板材和铝蜂窝；若皮材层铝合金的厚度高于200μm，则其在复合板材中厚度占比过大，降低了其它合金层的厚度比例，从而导致强化效果不佳。因此优选单层皮材厚度为40-200μm。
第一包覆层铝合金2和第二包覆层铝合金4(下面简称包覆层)复合在芯材层铝合金3的两面，将芯材层铝合金3包覆，与外界隔绝。本发明所述的包覆，是指将芯材层在两个面上的包覆，因复合材料厚度仅为毫米级，芯材层的各断面暴露于空气中的情况，可忽略不计。第一包覆层铝合金2和第二包覆层铝合金4的材质可相同，也可有所不同，取上述成分中的任一种，都可满足包覆芯材层铝合金3，并与皮材层铝合金1复合的要求。
本发明中的包覆层，若单层厚度低于50μm，不能有效防止芯材层铝合金3中的Mg元素扩散至皮材或合金表面；由于板材的最终厚度为1-3mm，若单层厚度高于100μm，则复合板材中芯材层铝合金3的厚度占比过少，强化效果不佳。因此优选单层芯材1厚度在50-100μm，既可有效防止Mg扩散至皮材或表面，也能尽可能保证芯材层铝合金3厚度以产生最佳强化效果。
在热加工、热处理和后续钎焊过程中，芯材层铝合金3中的Mg元素，以固溶形式存在Al基体中而产生固溶强化，或形成Al2CuMg或Mg2Si或MgZn2等细小第二相而产生强化效应，从而较大程度的提高铝合金复合板材焊接前后的强度。鉴于合金中各元素的相生相克，相辅相成的复杂制约关系，发明人发现，本发明的芯材层铝合金3合金可分别由以下四类合金构成，都可以取得提高最终板材的强度的效果：
(1)0.7-2.0％的Cu，0.3-1.0％的Mn，0.3-1.0％的Mg，0.2-0.5％的Zn，0.1-0.3％的 Ti，0.3-0.8％的Fe，0.5-1.2％的Si，其余为Al和小于0.15％的不可避免杂质。在该组分的芯材层铝合金3中，当主要合金元素Cu的含量高于2.0％时，则合金的熔点约为600℃或更低，从而导致在后续的钎焊过程中，该层合金存在熔化或过烧而失效的风险；当Cu含量低于0.7％时，则生成的Al2CuMg强化相数量过少而对强度无明显贡献。
(2)0.04-0.2％的Cu，0.1-0.65％的Mn，1.0-3.0％的Mg，0.05-0.3％的Zn，0.05-0.25％的Cr，0-0.2％的Ti，Fe和Si含量总和低于0.8％，其余为Al和小于0.15％的不可避免杂质。在该组分的芯材层铝合金3中，当主要合金元素Mg的含量高于3.0％时，合金的熔点约为600℃或更低，从而导致在后续的钎焊过程中，该层合金存在熔化或过烧而失效的风险；当Mg含量低于1.0％时，则Mg固溶于Al基体中产生的固溶强化达不到预期强化效果。
(3)0.2-0.7％的Cu，0.1-0.8％的Mn，0.3-1.2％的Mg，0.08-0.2％的Ti，0.3-1.2％的Si，0.2-0.8％的Fe，其余为Al和小于0.15％的不可避免杂质。在该组分的芯材层铝合金3中，当主要合金元素Mg、Si在0.3-1.2％范围内，合金具有抗拉强度、伸长率、抗应力腐蚀、抗焊接开裂等性能的良好组合；当Mg、Si的含量高于1.2％时，合金的耐蚀性降低；当含量Mg、Si的含量低于0.3％，则Mg2Si强化相数量过少而对强度无明显贡献。
(4)0.1-1.0％的Cu，0.1-0.5％的Mn，1.0-3.0％的Mg，3.0-7.0％的Zn，0.05-0.35％Cr，0.05-0.2％的Ti，0.05-0.25％Zr，Fe和Si含量总和低于0.7％，其余为Al和小于0.15％的不可避免杂质。在该组分的芯材层铝合金3中，主要合金元素Mg对合金的熔点影响较大，当其含量高于3.0％时，合金的熔点降低至600℃或更低，从而导致在后续的钎焊过程中，该层合金存在熔化或过烧而报废的风险；当Mg含量低于1.0％时，则MgZn2强化相数量过少而对强度无明显贡献。
本发明为了解决上述四类含Mg元素芯材层铝合金3合金的钎焊问题，在芯材层铝合金3上下各复合一层包覆层铝合金，用来防止在加工、热处理和钎焊过程中，Mg元素扩散至皮材或者材料表面从而影响恶化钎焊。采取该技术措施后，可以实现高Mg含量铝合金面板材料和蜂窝的连续载气钎焊连接，从而获得高的钎焊生产效率和成品率。
本发明的另一目的在于提供一种用于载气钎焊的高强度复合板材的制造方法，即上述钎焊蜂窝板用高强度铝合金复合面板材料的制造方法。该复合板材经各种合金熔铸、按图1所示的顺序和比例复合、大变形热轧、冷轧和退火，制成最终厚度为1-3mm复合面板材料成品。
详细来说，本发明公开的一种钎焊蜂窝板用高强度铝合金复合面板材料的制造方法，包括如下步骤：
合金熔铸：分别取皮材层铝合金、第一包覆层铝合金、芯材层铝合金和第二包覆层铝合金原料熔铸成坯锭；
表面处理：将各合金铸锭经铣削去除表面铸造缺陷；
复合热轧：经表面处理后的皮材合金铸锭、第一包覆层合金铸锭和第二包覆层铝合金铸锭热轧至一定厚度，然后与芯材层合金铸锭按顺序叠放并捆扎，经多道次热轧至厚度为5-10mm，终轧温度大于300℃，然后打卷空冷；
冷轧：经多道次冷精轧至最终厚度；
退火：复合材料冷轧卷退火、保温，得到所述钎焊蜂窝板用高强度铝合金复合面板材料。
优选地，退火温度为360-380℃，保温2-4h。
在复合热轧步骤中，所述的皮材合金铸锭、第一包覆层合金铸锭和第二包覆层铝合金铸锭热轧至一定厚度，是指将皮材合金铸锭、第一包覆层合金铸锭和第二包覆层铝合金铸锭热轧至17至40mm的厚板，方便与芯材层合金铸锭复合。
下面，例举本发明的不同实施例来对本发明进行更详尽的具体说明。需要说明的是，下面具体实施例所例举的数值为有限例举，经试验证明，上述范围内的数值，均可达到答复提高复合板材强度的效果，不再一一例举。
实施例1：
本实施例按以下步骤进行：
1)合金熔铸：分别按照各自标准成分熔铸AA4045、AA3003Mod和AA2006合金，铸锭尺寸均为400×1120×5100mm，其中AA4045合金含有10.4％的Si，其余为Al和小于0.5％的不可避免杂质；AA3003Mod合金含有1.65％的Mn，1.5％的Zn，0.65％的Si，0.12％的Zr，其余为Al和小于0.15％的不可避免杂质；AA2006合金含有0.95％的Mg，1.5％的Cu，0.8％的Mn，1.0％的Si，0.7％的Fe，0.2％的Zn，0.3％的Ti，和其余为Al和小于0.15％的不可避免杂质。
2)复合热轧：经表面处理后的AA4045热轧至28±0.5mm，AA3003Mod铝合金铸锭热轧至18±0.5mm，然后均分断成5100mm长一段，与铣面后厚度约为390mm的AA2006合金按照AA4045、AA3003Mod、AA2006、AA3003Mod的顺序自上而下叠放并捆扎，加热至480±10℃并保温12h，然后经多道次热轧至8±1mm，终轧温度大于300℃，然后打卷空冷。
3)冷轧：经多道次冷精轧至1.5±0.01mm。
4)退火：复合材料冷轧卷在360℃退火炉中保温4h，空冷即得到本发明所述的可载气钎焊高强度复合板材。所制得的复合板材中，AA4045合金的厚度约为92μm，单层AA3003Mod合金的厚度约为60μm。
本实施例所制备的铝合金复合板材模拟钎焊检测，模拟钎焊工艺为经24min升温至600℃，保温10min，保护气氛为氩气。检测结果显示钎焊连接效果良好，钎焊前后的力学性能如表1所示。钎焊后屈服强度较焊前有一定程度升高，可达88MPa，而普通的4系/3系铝合金钎焊板材屈服强度仅为40-60MPa。
表1 实施例1所制备的铝合金复合材料板材性能
状态 厚度/mm 屈服强度/MPa 抗拉强度/MPa 延伸率/％
成品O态 1.5 62 161 23.8
钎焊后 1.5 88 194 20.1
实施例2：
本实施例按以下步骤进行：
1)合金熔铸：分别按照各自标准成分熔铸AA4343、AA3003Mod和AA5052合金，铸锭尺寸均为450×1450×4800mm。其中AA4343含有7.4％的Si，其余为Al和小于0.5％的不可避免杂质；AA3003Mod合金含有1.6％的Mn，0.65％的Cu，0.12％的Fe，0.13％的Zr，0.04％的Ti，其余为Al和小于0.15％的不可避免杂质；AA5052合金含有2.6％的Mg，0.15％的Si，0.02％的Ti，0.25％的Cr，0.3％的Fe，其余为Al和小于0.15％的不可避免杂质。
2)复合热轧：经表面处理后的AA4343热轧至28±0.5mm，AA3003铝合金铸锭热轧至22±0.5mm，均分断成4800mm长，AA5052合金经铣面后厚度约为440mm。将厚板和铸锭按照AA4343、AA3003Mod、AA5052、AA3003Mod的顺序自上而下叠放并捆扎，加热至480±10℃并保温12h，然后经多道次热轧至5±1mm，终轧温度大于300℃，然后打卷空冷。
3)冷轧：经多道次冷精轧至1.2±0.01mm。
4)退火：复合材料冷轧卷在370℃退火炉中保温4h，空冷即得到本发明所述可载气钎焊的高强度复合板材。所制得的复合板材中，AA4343合金的厚度约为68μm，单层AA3003Mod合金的厚度约为54μm。
本实施例所制备的铝合金复合板材模拟钎焊前后的力学性能检测结果如表2所示，模拟钎焊工艺为经24min升温至600℃，保温10min，保护气氛为氩气。检测结果显示板材 钎焊连接效果良好，焊后屈服强度84MPa，而普通的4系/3系铝合金钎焊板材屈服强度仅为40-60MPa。
表2 实施例2所制备的铝合金复合板材钎焊前后的力学性能
状态 厚度/mm 屈服强度/MPa 抗拉强度/MPa 延伸率/％
成品O态 1.2 86 184 21.3
模拟钎焊后 1.2 84 172 20.6
实施例3：
本实施例按以下步骤进行：
1)合金熔铸：分别按照各自标准成分熔铸AA4045、AA3003Mod和AA6A02合金，铸锭尺寸均为400×1120×5100mm。其中AA4045合金含有10.4％的Si，其余为Al和小于0.5％的不可避免杂质；AA3003Mod合金含有1.6％的Mn，0.65％的Cu，0.12％的Fe，0.1％的Ti，其余为Al和小于0.15％的不可避免杂质；AA6A02合金含有1.1％的Si，0.7％的Mg，0.25％的Mn，0.25％的Cu，0.3％的Fe，0.13％的Ti，其余为Al和小于0.15％的不可避免杂质。
2)复合热轧：经表面处理后的AA4045热轧至32±0.5mm，AA3003铝合金铸锭热轧至22±0.4mm，然后分断成与5100mm长的厚板，与铣面后厚度约为390mm的AA6A02合金按照AA4045、AA3003、AA6A02、AA3003的顺序自上而下叠放并捆扎，加热至480±10℃并保温12h，然后经多道次热轧至7±1mm，终轧温度大于300℃，然后打卷空冷。
3)冷轧：经多道次冷精轧至2.0±0.02mm。
4)退火：复合材料冷轧卷在380℃退火炉中保温2h，空冷即得到本发明所述可载气钎焊的高强度复合板材。所制得的复合板材中，AA4045合金的厚度约为145μm，单层AA3003Mod合金的厚度约为98μm。
本实施例所制备的铝合金复合板材模拟钎焊前后的力学性能检测结果如表2所示，模拟钎焊工艺为经24min升温至600℃，保温10min，保护气氛为氩气。结果显示氩气保护焊接效果良好，焊后屈服强度可达85MPa，而普通的4系/3系铝合金钎焊板材屈服强度仅为40-60MPa。
表3 实施例3所制备的铝合金复合材料板材性能
状态 厚度/mm 屈服强度/MPa 抗拉强度/MPa 延伸率/％
成品O态 2 65 137 24.1
钎焊后 2 85 191 18.3
实施例4：
本实施例按以下步骤进行：
1)合金熔铸：分别按照各自标准成分熔铸AA4343、AA3003Mod和AA7005合金，铸锭尺寸均为450×1450×4800mm。其中AA4343含有7.4％的Si，其余为Al和小于0.5％的不可避免杂质；AA3003Mod合金含有1.48％的Mn，0.35％的Cu，0.22％的Fe，0.15％的Ti，其余为Al和小于0.15％的不可避免杂质；AA7005合金含有4.45％的Zn，1.45％的Mg，0.65％的Mn，0.02％的Ti和0.08％的Cr，其余为Al和小于0.25％的不可避免杂质。
2)复合热轧：经表面处理后的AA4343热轧至40±0.5mm，AA3003Mod铝合金铸锭热轧至17±0.5mm，均分断成4800mm长，AA7005合金经铣面后厚度约为440mm。将厚板和铸锭按照AA4343、AA3003Mod、AA7005、AA3003Mod的顺序自上而下叠放并捆扎，加热至480±10℃并保温12h，然后经多道次热轧至10±1mm，终轧温度大于300℃，然后打卷空冷。
3)冷轧：经多道次冷精轧至2.5±0.01mm。
4)退火：复合材料冷轧卷在370℃退火炉中保温4h，空冷即得到本发明所述的可载气钎焊的高强度复合板材。所制得的复合板材中，AA4343合金的厚度约为192μm，单层AA3003Mod合金的厚度约为82μm
本实施例所制备的铝合金复合板材模拟钎焊前后的力学性能检测结果如表1所示，模拟钎焊工艺为经24min升温至600℃，保温10min，保护气氛为氩气。检测结果显示钎焊连接效果良好，焊后屈服强度117MPa，而普通的4系/3系铝合金钎焊板材屈服强度仅为40-60MPa。
表4 实施例4所制备的铝合金复合板材钎焊前后的力学性能
状态 厚度/mm 屈服强度/MPa 抗拉强度/MPa 延伸率/％
成品O态 2.5 81 192 21.3
模拟钎焊后 2.5 117 230 17.6

Claims (10)

  1. 一种钎焊蜂窝板用高强度铝合金复合面板材料，包括皮材层铝合金和芯材层铝合金，其特征在于，还包括第一包覆层铝合金和第二包覆层铝合金，以所述皮材层铝合金、所述第一包覆层铝合金、所述芯材层铝合金和所述第二包覆层铝合金的顺序复合为板材；
    所述皮材层铝合金中含有7.0-10.5％的Si；
    所述第一包覆层铝合金和所述第二包覆层铝合金的材质中含有0-0.7％的Cu，1.1-1.7％的Mn，0-1.7％的Zn，0-0.2％的Ti，0-0.8％的Si，其余为Al和小于0.15％的不可避免杂质；
    所述芯材层铝合金中含有0.3-3.0％的Mg，所述芯材层的厚度占比为70％以上。
  2. 如权利要求1所述的面板材料，其特征在于，所述皮材层铝合金的厚度为40-200μm。
  3. 如权利要求1所述的面板材料，其特征在于，所述第一包覆层铝合金和所述第二包覆层铝合金的厚度均为50-100μm。
  4. 如权利要求1所述的面板材料，其特征在于，所述芯材层铝合金的材质中含有0.7-2.0％的Cu，0.3-1.0％的Mn，0.3-1.0％的Mg，0.2-0.5％的Zn，0.1-0.3％的Ti，0.3-0.8％的Fe，0.5-1.2％的Si，其余为Al和小于0.15％的不可避免杂质。
  5. 如权利要求1所述的面板材料，其特征在于，所述芯材层铝合金的材质中含有0.04-0.2％的Cu，0.1-0.65％的Mn，1.0-3.0％的Mg，0.05-0.3％的Zn，0.05-0.25％的Cr，0-0.2％的Ti，Fe和Si含量总和低于0.8％，其余为Al和小于0.15％的不可避免杂质。
  6. 如权利要求1所述的面板材料，其特征在于，所述芯材层铝合金的材质中含有0.2-0.7％的Cu，0.1-0.8％的Mn，0.3-1.2％的Mg，0.08-0.2％的Ti，0.3-1.2％的Si，0.2-0.8％的Fe，其余为Al和小于0.15％的不可避免杂质。
  7. 如权利要求1所述的面板材料，其特征在于，所述芯材层铝合金的材质中含有0.1-1.0％的Cu，0.1-0.5％的Mn，1.0-3.0％的Mg，3.0-7.0％的Zn，0.05-0.35％Cr，0.05-0.2％的Ti，0.05-0.25％Zr，Fe和Si含量总和低于0.7％，其余为Al和小于0.15％的不可避免杂质。
  8. 如权利要求1所述的面板材料，其特征在于，所述板材的最终厚度为1-3mm。
  9. 一种钎焊蜂窝板用高强度铝合金复合面板材料的制造方法，其特征在于，包括如下步骤：
    合金熔铸：分别取皮材层铝合金、第一包覆层铝合金、芯材层铝合金和第二包覆层铝合金原料熔铸成坯锭，并作表面处理；
    复合热轧：经表面处理后的皮材合金铸锭、第一包覆层合金铸锭和第二包覆层铝合金铸锭热轧至一定厚度，然后与芯材层合金铸锭按顺序叠放并捆扎，经多道次热轧至厚度为5-10mm，终轧温度大于300℃，然后打卷空冷；
    冷轧：经多道次冷精轧至最终厚度；
    退火：复合材料冷轧卷退火、保温，得到所述钎焊蜂窝板用高强度铝合金复合面板材料。
  10. 如权利要求9所述的制造方法，其特征在于，所述退火步骤的退火温度为360-380℃，到温后保温2-4h。
PCT/CN2016/100360 2016-09-27 2016-09-27 一种钎焊蜂窝板用铝合金复合面板材料及其制造方法 WO2018058306A1 (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/100360 WO2018058306A1 (zh) 2016-09-27 2016-09-27 一种钎焊蜂窝板用铝合金复合面板材料及其制造方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/100360 WO2018058306A1 (zh) 2016-09-27 2016-09-27 一种钎焊蜂窝板用铝合金复合面板材料及其制造方法

Publications (1)

Publication Number Publication Date
WO2018058306A1 true WO2018058306A1 (zh) 2018-04-05

Family

ID=61763249

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/100360 WO2018058306A1 (zh) 2016-09-27 2016-09-27 一种钎焊蜂窝板用铝合金复合面板材料及其制造方法

Country Status (1)

Country Link
WO (1) WO2018058306A1 (zh)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109266888A (zh) * 2018-12-03 2019-01-25 东北轻合金有限责任公司 一种308合金铸锭的及其制备方法和应用
CN112848551A (zh) * 2020-12-11 2021-05-28 西南铝业（集团）有限责任公司 一种铝合金板材及其制备方法
CN113957296A (zh) * 2021-10-21 2022-01-21 江苏鼎胜新能源材料股份有限公司 一种哈兹列特3003芯材生产的水箱主板材料及其制造方法
CN113969338A (zh) * 2021-09-28 2022-01-25 材谷金带(佛山)金属复合材料有限公司 一种层状铝/钢复合板材制备方法
CN114148046A (zh) * 2021-10-27 2022-03-08 银邦金属复合材料股份有限公司 一种铝合金复合材料及其制备方法与应用
CN114292995A (zh) * 2021-12-01 2022-04-08 长沙新材料产业研究院有限公司 一种铝镁复合板材及其制备方法
CN115366502A (zh) * 2022-09-01 2022-11-22 燕山大学 一种具有自熔合层状微结构的热传输复合铝板及制备方法
CN115570294A (zh) * 2022-10-28 2023-01-06 沈阳大学 一种用于7xxx铝合金焊接的焊丝及其制备工艺

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2378450B (en) * 2001-07-09 2005-03-02 Corus Aluminium Walzprod Gmbh Structural component for an aircraft
CN102448662A (zh) * 2009-05-29 2012-05-09 美铝公司 具有优良的受控气氛钎焊（cab）钎焊性能的高强度多层钎焊片材结构
JP2015217403A (ja) * 2014-05-15 2015-12-07 株式会社Uacj アルミニウムクラッド材の製造方法

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2378450B (en) * 2001-07-09 2005-03-02 Corus Aluminium Walzprod Gmbh Structural component for an aircraft
CN102448662A (zh) * 2009-05-29 2012-05-09 美铝公司 具有优良的受控气氛钎焊（cab）钎焊性能的高强度多层钎焊片材结构
JP2015217403A (ja) * 2014-05-15 2015-12-07 株式会社Uacj アルミニウムクラッド材の製造方法

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109266888A (zh) * 2018-12-03 2019-01-25 东北轻合金有限责任公司 一种308合金铸锭的及其制备方法和应用
CN112848551A (zh) * 2020-12-11 2021-05-28 西南铝业（集团）有限责任公司 一种铝合金板材及其制备方法
CN113969338A (zh) * 2021-09-28 2022-01-25 材谷金带(佛山)金属复合材料有限公司 一种层状铝/钢复合板材制备方法
CN113957296A (zh) * 2021-10-21 2022-01-21 江苏鼎胜新能源材料股份有限公司 一种哈兹列特3003芯材生产的水箱主板材料及其制造方法
CN114148046A (zh) * 2021-10-27 2022-03-08 银邦金属复合材料股份有限公司 一种铝合金复合材料及其制备方法与应用
CN114148046B (zh) * 2021-10-27 2023-05-30 银邦金属复合材料股份有限公司 一种铝合金复合材料及其制备方法与应用
CN114292995A (zh) * 2021-12-01 2022-04-08 长沙新材料产业研究院有限公司 一种铝镁复合板材及其制备方法
CN115366502A (zh) * 2022-09-01 2022-11-22 燕山大学 一种具有自熔合层状微结构的热传输复合铝板及制备方法
CN115366502B (zh) * 2022-09-01 2024-04-12 燕山大学 一种具有自熔合层状微结构的热传输复合铝板及制备方法
CN115570294A (zh) * 2022-10-28 2023-01-06 沈阳大学 一种用于7xxx铝合金焊接的焊丝及其制备工艺

Similar Documents

Publication Publication Date Title
WO2018058306A1 (zh) 一种钎焊蜂窝板用铝合金复合面板材料及其制造方法
CN108602317B (zh) 铝多层钎焊板制品和无钎剂钎焊方法
EP2243589B1 (en) Aluminum alloy clad sheet for heat exchangers and method of producing the same
EP3615329B1 (en) Clad aluminum alloy products
CN110735074B (zh) 一种蜂窝板用铝合金复合材料及其制备方法
EP2969376B1 (en) Clad sheet alloys for brazing applications
CN103122427A (zh) 钎焊用铝合金复合板材及其制造方法
CN106335247A (zh) 一种用于载气钎焊的铝蜂窝结构板及制作方法
CN106514033A (zh) 铝合金、热交换器、铝合金复合材料及其制备方法
CN110947762A (zh) 一种真空钎焊用308铝合金三层复合板的制备方法
CN109797323A (zh) 一种高耐腐蚀多层复合铝合金管材及其生产方法
WO2013157455A1 (ja) アルミニウムクラッド材の製造方法およびアルミニウムクラッド材
JP6542649B2 (ja) アルミニウム合金クラッド板およびアルミニウム合金クラッド構造部材
US10272645B2 (en) Aluminum-alloy-clad plate and aluminum-alloy-clad structural member
CN113692454B (zh) 铝合金硬钎焊板及其制造方法
CN112955574B (zh) 铝合金硬钎焊板及其制造方法
JP7275336B1 (ja) アルミニウム合金材の製造方法及びアルミニウム合金材
CN113878947B (zh) 一种五层铝合金复合材料及其制造方法
EP3785844A1 (en) Aluminum alloy material, fluxless brazed structure, and fluxless brazing method
EP3976371A1 (en) Clad 2xxx-series aerospace product
JP2003147467A (ja) 熱交換器用アルミニウム合金ブレージングシートおよびその製造方法
JP2015131417A (ja) 接合材とその製造方法、鉄道車両の構体及び交通輸送手段の構体
CN114148046B (zh) 一种铝合金复合材料及其制备方法与应用
JPH01111840A (ja) 成形性及び焼付硬化性の優れたアルミニウム合金合せ板
US20220325388A1 (en) Clad 2xxx-series aerospace product

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16917066

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 16917066

Country of ref document: EP

Kind code of ref document: A1