JPS58204139A - Production of fiber-reinforced aluminum alloy - Google Patents
Production of fiber-reinforced aluminum alloyInfo
- Publication number
- JPS58204139A JPS58204139A JP8677082A JP8677082A JPS58204139A JP S58204139 A JPS58204139 A JP S58204139A JP 8677082 A JP8677082 A JP 8677082A JP 8677082 A JP8677082 A JP 8677082A JP S58204139 A JPS58204139 A JP S58204139A
- Authority
- JP
- Japan
- Prior art keywords
- aluminum
- alloy
- aluminum alloy
- fiber
- foil
- Prior art date
- Legal status (The legal status 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 status listed.)
- Pending
Links
- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 23
- 238000004519 manufacturing process Methods 0.000 title claims description 7
- 239000002131 composite material Substances 0.000 claims abstract description 18
- 239000011888 foil Substances 0.000 claims abstract description 16
- 239000012783 reinforcing fiber Substances 0.000 claims abstract description 15
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 14
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 9
- 239000000956 alloy Substances 0.000 claims abstract description 9
- 238000005219 brazing Methods 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims abstract description 5
- 238000002844 melting Methods 0.000 claims description 14
- 230000008018 melting Effects 0.000 claims description 13
- 230000001590 oxidative effect Effects 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- 239000000835 fiber Substances 0.000 abstract description 19
- 229910052751 metal Inorganic materials 0.000 abstract description 8
- 239000002184 metal Substances 0.000 abstract description 8
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 abstract description 3
- 229910010271 silicon carbide Inorganic materials 0.000 abstract description 3
- 229920000049 Carbon (fiber) Polymers 0.000 abstract description 2
- 239000004917 carbon fiber Substances 0.000 abstract description 2
- 238000010030 laminating Methods 0.000 abstract description 2
- 239000000463 material Substances 0.000 abstract description 2
- 229910000861 Mg alloy Inorganic materials 0.000 abstract 1
- 239000011159 matrix material Substances 0.000 description 14
- 238000000034 method Methods 0.000 description 10
- 239000012779 reinforcing material Substances 0.000 description 4
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 238000013329 compounding Methods 0.000 description 3
- 230000010354 integration Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 229910007981 Si-Mg Inorganic materials 0.000 description 2
- 229910008316 Si—Mg Inorganic materials 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000000155 melt Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000010953 base metal Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000011162 core material Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000004070 electrodeposition Methods 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Landscapes
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
Description
【発明の詳細な説明】
この発明はアルミニウム合金をマトリックスとし、その
中に強化材として繊維物質を分散せしめた繊維強化アル
ミニウム合金の製造方法に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a method for manufacturing a fiber-reinforced aluminum alloy in which an aluminum alloy is used as a matrix and a fiber material is dispersed therein as a reinforcing material.
従来、アルミニウム合金をマトリックスとする繊維−Ａ
Ｉ複合材料の製造法としては、主に溶浸法の１つとして
の鋳造法、あるいはホットプレス法が一般によく知られ
ている。しかしながら、概して、鋳造法によるときは、
複合化を行う際の高温により強化材としての繊維が劣化
し易いという問題点かあシ、また、従来のホットプレス
法によるときは、複合化に高圧力、長時間を要するため
、生産性が悪いというような難点があった。Conventionally, fibers with aluminum alloy as a matrix-A
As a method for manufacturing I-composite materials, a casting method as one of the infiltration methods or a hot pressing method is generally well known. However, in general, when using the casting method,
The problem is that the fibers used as reinforcing materials tend to deteriorate due to high temperatures during compositing.Furthermore, when using the conventional hot press method, compositing requires high pressure and a long time, which reduces productivity. There were some drawbacks.
この発明の目的は上記のような問題点に鑑み、低圧力、
短時間で、マトリックスとなるアルミニウムと強化材と
しての繊維との良好な複合一体化を達成しうる繊維強化
アルミニウム合金の製造方法を提供しようとするもので
ある。In view of the above-mentioned problems, the purpose of this invention is to provide low pressure,
The object of the present invention is to provide a method for manufacturing a fiber-reinforced aluminum alloy that can achieve good composite integration of aluminum as a matrix and fibers as a reinforcing material in a short time.
而して、この発明は、アルミニウムに対してぬれ性の良
い、またはぬれ性を改善した強化繊維と、アルミニウム
合金相当の低融点アルミニウム合金箔とを交互に積層し
、この積層物を非酸化性雰囲気中で前記低融点アルミニ
ウム合金箔の融点以上に加熱し、かつ加圧することによ
って複合一体化することを特徴とする繊軸強化アルミニ
ウム合金の製造方法に係るものである。Therefore, the present invention alternately laminates reinforcing fibers that have good or improved wettability with respect to aluminum and low melting point aluminum alloy foil equivalent to aluminum alloy, and makes this laminate non-oxidizing. The present invention relates to a method for producing a filament-strengthened aluminum alloy, which comprises heating the low-melting-point aluminum alloy foil in an atmosphere to a temperature higher than its melting point and pressurizing the foil to form a composite and integral piece.
この発明の実施において、強化繊維の種類は特に限定さ
れるものではなく、繊維強化金属の強化材として従来既
知の各種繊維を任意に選択使用しうる。もっとも、その
繊維が、例えばシリコンカーバイド繊維のようにそれ自
体マトリックス金属に対してぬれ性の良いものである場
合には、これをそのまま用いて低融点アルミニウム合金
箔と積層することができるが、炭素繊維のようにそれ本
来のぬれ性が悪いものである場合には、予め金属を被覆
してぬれ性を改善して用いることが必要である。この金
属被覆の手段は、電着法、プラズマスプレー法等の種々
の方法が採用され得るが、繊維表面に均一な金属被膜を
所望の厚さに形成しうる点でイオンブレーティング法に
よるのが有利である。また、その被覆金属としては、母
材金属であるアルミニウムのほか、ケイ素あるいはチタ
ン等を用いても良い。In carrying out this invention, the type of reinforcing fibers is not particularly limited, and any conventionally known various fibers may be used as reinforcing materials for fiber-reinforced metals. However, if the fiber itself has good wettability with the matrix metal, such as silicon carbide fiber, it can be used as is and laminated with a low melting point aluminum alloy foil, but carbon In the case of fibers that inherently have poor wettability, it is necessary to coat them with metal in advance to improve their wettability before use. Various methods such as electrodeposition and plasma spraying can be used for this metal coating, but ion blating is preferable because it can form a uniform metal coating on the fiber surface to a desired thickness. It's advantageous. Furthermore, as the coating metal, silicon, titanium, or the like may be used in addition to aluminum, which is the base metal.
マトリックスであるアルミニウムろう合金相当の低融点
アルミニウム合金は、最も一般的にはＡＩ −Ｓｉ −
Ｍｇ系合金からなるものが用いられる。かかるマトリッ
クスは、それ自体低融点であることによって複合時に全
体が溶融して、強化金属繊維間に速やかに浸透し、低圧
力、短時間で複合化を達成しうると共に、ぬれ性の良好
なことも相俟って強化繊維との一体化が良好に行われ、
複合材料に優れた強度、弾性を帯有せしめうるものであ
る。The low melting point aluminum alloy equivalent to the aluminum brazing alloy that is the matrix is most commonly AI-Si-
A material made of Mg-based alloy is used. Since such a matrix itself has a low melting point, it melts as a whole during compounding and quickly penetrates between the reinforcing metal fibers, making it possible to achieve compounding at low pressure and in a short time, as well as having good wettability. Together with this, the integration with the reinforcing fibers is performed well,
This allows composite materials to have excellent strength and elasticity.
強化繊維と低融点アルミニウム合金箔との複合化操作は
、それらを適当な割合で積層し、この積層物を雄型と雌
型の間にセットし、非酸化性雰囲気、例えば真空中で適
当な圧力をかけ、かつ低融点アルミニウム合金箔の融点
以上に加熱することによって行われる。これにより、マ
トリックスである低融点アルミニウムはその全体が溶融
し、強化繊維間に含浸され、かつそれと一体化されて複
合化が達成されるものである。The composite operation of reinforcing fibers and low-melting point aluminum alloy foil involves laminating them in an appropriate ratio, setting this laminate between a male mold and a female mold, and heating it in an appropriate non-oxidizing atmosphere, such as a vacuum. This is done by applying pressure and heating above the melting point of the low melting point aluminum alloy foil. As a result, the entire low melting point aluminum matrix is melted, impregnated between the reinforcing fibers, and integrated with the reinforcing fibers, thereby achieving a composite.
この発明に基づ（繊維強化アルミニウム合金の製造方法
によれば、前述のように複合時に、マトリックスである
低融点アルミニウム合金が全体に溶融して強化繊維間に
入り込んでそれと複合されるため、この複合化を低圧力
、短時間で行うことができ、生産性を向上しうると共に
、マＩ−ＩＪワックス強化繊維との一体性の良好な、複
合材料として遜色のない強度、弾性を保有した製品を得
ることができる。かつ上記の如くマトリックスを溶融し
て複合化するので、平板状の製品に限らす、曲面形状等
の任意の形状に自在に複合成形できる。また、マトリッ
クスに低融点アルミニウム合金を用いることによって、
複合時の高温による繊維劣化のおそれを回避しうるのは
もとより、複合材料の繊維体積率を下げることがない。Based on this invention (according to the manufacturing method of fiber-reinforced aluminum alloy), as mentioned above, at the time of compounding, the low melting point aluminum alloy that is the matrix melts throughout and enters between the reinforcing fibers and is compounded with it. A product that can be composited at low pressure and in a short time, improving productivity, and has good integration with MAI-IJ wax reinforced fibers and has strength and elasticity comparable to that of a composite material. Moreover, since the matrix is melted and composited as described above, it is possible to freely mold the composite into any shape, such as a curved shape, not just a flat product. By using
Not only can it avoid the possibility of fiber deterioration due to high temperatures during compositing, but it also does not reduce the fiber volume fraction of the composite material.
即ち、例えばマトリックスとしてアルミニウムブレージ
ングシートラ用いたような場合には、そのコア材の存在
のために、複合材料の繊維体積率がそれだけ低下するが
、この発明に於ては、マ） ＩＪワックス全体が溶融し
て複合化されるのでそのような繊維体積率の低下要因が
なく、複合時の加圧力を調整して要すれば余分なマトリ
ックスをはみ出させることにより、あるいはまたマトリ
ックスとして使用する低融点アルミニウム合金箔の厚さ
を選定することにより、複合材料中の繊維体積率を自在
にコントロールすることができる等の種々の優れた利点
がある。That is, for example, when aluminum brazing sheets are used as a matrix, the fiber volume fraction of the composite material decreases due to the presence of the core material, but in this invention, the entire IJ wax is Because it is melted and composited, there is no such factor that reduces the fiber volume percentage, and by adjusting the pressure during composite and forcing out the excess matrix if necessary, or by adding low melting point aluminum to be used as a matrix. By selecting the thickness of the alloy foil, there are various excellent advantages such as being able to freely control the fiber volume fraction in the composite material.
次に、この発明の実施例を示す。Next, examples of this invention will be shown.
実施例１
直径１０μの炭化珪素繊維を強化繊維とし、マトリック
スとして、アルミニウムろう合金４００３相当の下記組
成を有するＡＩ −Ｓｉ −Ｍｇ系アルミニウム合金箔
で厚さ０．１７ｍｍのものを用いた。Example 1 Silicon carbide fibers with a diameter of 10 μm were used as reinforcing fibers, and as a matrix, an AI-Si-Mg-based aluminum alloy foil having the following composition and equivalent to aluminum brazing alloy 4003 and having a thickness of 0.17 mm was used.
マトリックス組成 （ｗｔ％）
ＡＩ Ｓｉ Ｆｅ Ｍｎ Ｍｇ Ｃｕ Ｚ
ｎ Ｃｒ Ｔｉ残 ６．６ ０．１８ ０．０１
１．９７ Ｔｒ Ｏ，０１Ｔｒ Ｏ，０１
そして、上記強化繊維とアルミニウム合金箔とを交互に
、前者を７層、後者を８層にして積層し、この積層を雌
型と雄型との間にセットして、ｌ ｃｒＩ′ｔｏｒｒ
の真空中で温度５８５℃、時間この複合材料は、引張
強度４０ＫＳｌ／１１１１１１’、繊維体積率（Ｖｆ）
１７％のものであった。Matrix composition (wt%) AI Si Fe Mn Mg Cu Z
n Cr Ti remaining 6.6 0.18 0.01
1.97 Tr O,01 Tr O,01
Then, the reinforcing fibers and aluminum alloy foil are alternately laminated with 7 layers of the former and 8 layers of the latter, and this laminated layer is set between the female mold and the male mold.
This composite material has a tensile strength of 40 KSl/111111' and a fiber volume fraction (Vf) of
It was 17%.
実施例２
直径７μの炭素繊維にイオンブレーティング法によりア
ルミニウムを厚さ１５μ被覆してぬれ性を改善したもの
を強化繊維として使用し、マトリックスは前記実施例１
と同様のＡＩ −Ｓｉ−Ｍｇ系アルミニウム合金箔を用
いた。Example 2 Carbon fibers with a diameter of 7 μm coated with aluminum to a thickness of 15 μm by ion-blating method to improve wettability were used as reinforcing fibers, and the matrix was the same as in Example 1 above.
The same AI-Si-Mg-based aluminum alloy foil was used.
そして、これらを実施例１と同じく積層し、Ｉ Ｑ＝ｔ
ｏｒｒ の真空中で温度６００℃、時間１０分、圧力
２３”１７／ｃ＋ＩＹの条件で複合化し、板状の複合材
料を得た。Then, these are stacked in the same manner as in Example 1, and IQ=t
The mixture was composited in a vacuum at 600° C. for 10 minutes and at a pressure of 23”17/c+IY to obtain a plate-like composite material.
この複合材料は、引張強度６０Ｋｙ／＋□２、繊維体積
率（Ｖｆ）２７％のものであった。This composite material had a tensile strength of 60 Ky/+□2 and a fiber volume fraction (Vf) of 27%.
以 上that's all
Claims (1)
善した強化繊維と、アルミニウムろう合金相当の低融点
アルミニウム合金箔とを交互に積層し、この積層物を非
酸化性雰囲気中で前記低融点アルミニウム合金箔の融点
以上に加熱しかつ加圧することによって複合化すること
を特徴とする繊維強化アルミニウム合金の製造方法。Reinforcing fibers with good wettability or improved wettability for aluminum and low melting point aluminum alloy foil equivalent to aluminum brazing alloy are alternately laminated, and this laminate is bonded to the low melting point aluminum in a non-oxidizing atmosphere. 1. A method for producing a fiber-reinforced aluminum alloy, which comprises heating the alloy foil to a temperature higher than its melting point and applying pressure to form a composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8677082A JPS58204139A (en) | 1982-05-21 | 1982-05-21 | Production of fiber-reinforced aluminum alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8677082A JPS58204139A (en) | 1982-05-21 | 1982-05-21 | Production of fiber-reinforced aluminum alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58204139A true JPS58204139A (en) | 1983-11-28 |
Family
ID=13895979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8677082A Pending JPS58204139A (en) | 1982-05-21 | 1982-05-21 | Production of fiber-reinforced aluminum alloy |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58204139A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4732314A (en) * | 1984-11-12 | 1988-03-22 | Director-General Of Agency Of Industrial Science And Technology | Method of manufacturing a metal-based composite material |
| EP0648593A2 (en) * | 1993-10-19 | 1995-04-19 | DEUTSCHE FORSCHUNGSANSTALT FÜR LUFT- UND RAUMFAHRT e.V. | Process for manufacturing long-fiber reinforced parts |
-
1982
- 1982-05-21 JP JP8677082A patent/JPS58204139A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4732314A (en) * | 1984-11-12 | 1988-03-22 | Director-General Of Agency Of Industrial Science And Technology | Method of manufacturing a metal-based composite material |
| WO1993014233A1 (en) * | 1984-11-12 | 1993-07-22 | Akira Sakamoto | Method of manufacturing compound materials of metal group |
| EP0648593A2 (en) * | 1993-10-19 | 1995-04-19 | DEUTSCHE FORSCHUNGSANSTALT FÜR LUFT- UND RAUMFAHRT e.V. | Process for manufacturing long-fiber reinforced parts |
| EP0648593A3 (en) * | 1993-10-19 | 1995-11-08 | Deutsche Forsch Luft Raumfahrt | Process for manufacturing long-fiber reinforced parts. |
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