JPH044144A - Carbon fiber reinforced composite material - Google Patents
Carbon fiber reinforced composite materialInfo
- Publication number
- JPH044144A JPH044144A JP10445390A JP10445390A JPH044144A JP H044144 A JPH044144 A JP H044144A JP 10445390 A JP10445390 A JP 10445390A JP 10445390 A JP10445390 A JP 10445390A JP H044144 A JPH044144 A JP H044144A
- Authority
- JP
- Japan
- Prior art keywords
- composite material
- carbon fiber
- reinforced composite
- synthetic resin
- strength
- 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
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 17
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 17
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 14
- 239000011208 reinforced composite material Substances 0.000 title claims abstract description 10
- 239000002131 composite material Substances 0.000 claims abstract description 19
- 239000003822 epoxy resin Substances 0.000 claims abstract description 12
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 12
- 229920003002 synthetic resin Polymers 0.000 claims abstract description 10
- 239000000057 synthetic resin Substances 0.000 claims abstract description 10
- 239000000463 material Substances 0.000 claims description 13
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 10
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 238000010030 laminating Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract 1
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 10
- 229920000098 polyolefin Polymers 0.000 description 8
- 229920005989 resin Polymers 0.000 description 5
- 239000011347 resin Substances 0.000 description 5
- 239000000835 fiber Substances 0.000 description 4
- 238000000465 moulding Methods 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 3
- 229920005992 thermoplastic resin Polymers 0.000 description 3
- 239000004696 Poly ether ether ketone Substances 0.000 description 2
- 239000004695 Polyether sulfone Substances 0.000 description 2
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 2
- 229920006393 polyether sulfone Polymers 0.000 description 2
- 229920002530 polyetherether ketone Polymers 0.000 description 2
- VXNZUUAINFGPBY-UHFFFAOYSA-N 1-Butene Chemical compound CCC=C VXNZUUAINFGPBY-UHFFFAOYSA-N 0.000 description 1
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- 239000004743 Polypropylene Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- IAQRGUVFOMOMEM-UHFFFAOYSA-N butene Natural products CC=CC IAQRGUVFOMOMEM-UHFFFAOYSA-N 0.000 description 1
- 150000001732 carboxylic acid derivatives Chemical class 0.000 description 1
- 229920001577 copolymer Polymers 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- -1 polypropylene Polymers 0.000 description 1
- 229920001155 polypropylene Polymers 0.000 description 1
- QQONPFPTGQHPMA-UHFFFAOYSA-N propylene Natural products CC=C QQONPFPTGQHPMA-UHFFFAOYSA-N 0.000 description 1
- 125000004805 propylene group Chemical group [H]C([H])([H])C([H])([*:1])C([H])([H])[*:2] 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Landscapes
- Laminated Bodies (AREA)
Abstract
Description
【発明の詳細な説明】
［産業上の利用分野］
本発明は人工衛星等の宇宙構造物、航空機、自動車、レ
ジャー用品などの構造体に用いる炭素繊維強化複合材料
に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a carbon fiber reinforced composite material used for structures such as space structures such as artificial satellites, aircraft, automobiles, and leisure goods.
［従来の技術］
炭素繊維をベースにした繊維強化複合材料（ＣＦＲＰ）
は、比強度や比弾性率の面で、他の強化繊維であるガラ
ス、アラミドおよびボロン繊維などを用いた繊維強化複
合材料よりも優れており、航空宇宙、自動車、レジャー
用品などの構造材料として巾広く用いられるようになっ
てきているＣＦＲＰのなかで現在主流となっているのが
、炭素繊維をエポキシ樹脂で固型化した複合材料である
。[Conventional technology] Carbon fiber-based fiber reinforced composite material (CFRP)
In terms of specific strength and specific modulus, it is superior to fiber-reinforced composite materials using other reinforcing fibers such as glass, aramid, and boron fibers, and is used as a structural material for aerospace, automobiles, leisure goods, etc. Among CFRPs that are becoming widely used, the current mainstream is a composite material made of carbon fibers solidified with epoxy resin.
エポキシ樹脂を用いたＣＦＲＰは、半硬化のフレキシブ
ルな状態で積層し焼き固めるという一体成形が可能であ
るため、複雑な形状の構造物を容易に作製できること、
さらには耐熱性に優れているなどの特長を有する。CFRP using epoxy resin can be integrally molded by laminating and baking in a semi-cured and flexible state, so structures with complex shapes can be easily manufactured.
Furthermore, it has features such as excellent heat resistance.
〔発明が解決しようとする課題］
炭素繊維自体の性能が高まるにつれて、エポキシ樹脂の
脆性的特性が問題になっている。エポキシ樹脂をマトリ
ックスにするＣＦＲＰに引っ張り、繰返し、衝撃などの
荷重を加えた場合、最初に樹脂の破壊が生じ、前記破壊
がＣＦＲＰ全体の破壊を引起こす。このため、炭素繊維
自体の強度を高めても、ＣＦＲＰの強度はそれ程増加し
ない。例えば、高強度繊維トレカＴ８００ （東し株式
会社製）をベースにした擬似等方性構成のＣＦＲＰでは
、引っ張り破断伸びが１．５％と繊維自体の破断伸びの
１．９％よりも小さな値となっている。また、前記複合
材料では、伸びが１％の状態で９０°と４５°の層間に
顕著な剥離が生じており、この段階で構造材料としての
使用は難しいことを示している。[Problems to be Solved by the Invention] As the performance of carbon fiber itself increases, the brittle characteristics of epoxy resins have become a problem. When a load such as tension, repetition, impact, etc. is applied to a CFRP having an epoxy resin as a matrix, the resin first breaks down, and the breakage causes the entire CFRP to break. For this reason, even if the strength of the carbon fiber itself is increased, the strength of CFRP will not increase that much. For example, in CFRP with a quasi-isotropic structure based on the high-strength fiber Torayca T800 (manufactured by Toshi Co., Ltd.), the tensile elongation at break is 1.5%, which is smaller than the elongation at break of the fiber itself, which is 1.9%. It becomes. Furthermore, in the composite material, significant peeling occurred between the layers at 90° and 45° at an elongation of 1%, indicating that it is difficult to use it as a structural material at this stage.
また、エポキシ樹脂の脆性的特性はＣＦＲＰの強度特性
のばらつきを大きくするため、構造物設計時の安全率を
低下させるという問題があった。Furthermore, the brittle characteristics of the epoxy resin increase the variation in the strength characteristics of the CFRP, resulting in a problem of lowering the safety factor when designing a structure.
これら問題を解決する目的で、マトリックス樹脂に靭性
の大きな熱可塑性樹脂を使用し、ＣＦＲＰの強度特性を
向上させる試みが検討されている。これは、耐熱性に優
れた熱可塑性樹脂であるポリエーテルエーテルケトン樹
脂（ＰＥＥＫ）やポリエーテルサルホン樹脂（ＰＥＳ）
をマトリックス樹脂に用いるものである。しかし、この
ような熱可塑性樹脂の適用は、ＣＦＲＰの強度特性を向
上できるものの、成形温度が非常に高くなり現有の設備
では成形できないばかりでなく、プリプレグシートのフ
レキシビリティがエポキシ樹脂ベースのものに比較して
乏しく複雑な形状の構造物が作製し難いなどの問題点が
あり効果的でない。In order to solve these problems, attempts are being made to improve the strength characteristics of CFRP by using a thermoplastic resin with high toughness as the matrix resin. This is a thermoplastic resin with excellent heat resistance such as polyether ether ketone resin (PEEK) and polyether sulfone resin (PES).
is used for the matrix resin. However, although the application of such thermoplastic resins can improve the strength properties of CFRP, the molding temperature is extremely high, making it impossible to mold with existing equipment, and the flexibility of the prepreg sheet is not limited to that of epoxy resin-based ones. There are problems in that it is difficult to fabricate structures with complicated shapes, and it is not effective.
本発明は前記課題を解決するものであり、その目的とす
るところは従来のＣＦＲＰの成形方法で機械的強度に優
れた炭素繊維強化複合材料を提供することにある。The present invention is intended to solve the above problems, and its purpose is to provide a carbon fiber reinforced composite material with excellent mechanical strength using a conventional CFRP molding method.
［課題を解決するための手段］
Ａｊｊ記目的を達成するため、本発明に係る炭メ′、繊
維強化複合材料においては、カーボン繊維をエポキシ樹
脂に充填した複合材料層と、合成樹脂フィルムとを組合
せてなる炭素繊維強化複合材料であって、
前記複合材料層と合成樹脂フィルムとは、１」７層一体
化されたものである。[Means for Solving the Problems] In order to achieve the objects listed in Ajj, the carbon fiber-reinforced composite material according to the present invention includes a composite material layer in which carbon fibers are filled in an epoxy resin and a synthetic resin film. The carbon fiber reinforced composite material is a combination of carbon fiber reinforced composite materials, in which the composite material layer and the synthetic resin film are integrated into 1"7 layers.
［作用］
本発明の炭素繊維強化複合材料では、層間に合成樹脂フ
ィルムを設けである。合成樹脂フィルムは、一般に破断
伸びがエポキシ樹脂よりも大きいため、複合材料の層間
破壊靭性を高めることが可能となる。これにより、層間
剥離なとの損傷の進展が抑制され、引張り強度、疲労強
度などの機械的強度を改善できる。[Function] In the carbon fiber reinforced composite material of the present invention, a synthetic resin film is provided between the layers. Since synthetic resin films generally have a higher elongation at break than epoxy resins, it is possible to improve the interlaminar fracture toughness of the composite material. This suppresses the progress of damage such as delamination, and improves mechanical strength such as tensile strength and fatigue strength.
〔実施例］ 以下に、本発明の実施例を図によって説明する。〔Example] Embodiments of the present invention will be described below with reference to the drawings.
第１図は本発明に係る繊維強化複合材料を示す断面図で
ある。FIG. 1 is a sectional view showing a fiber reinforced composite material according to the present invention.
図において実施例は、一方向に引き揃えた高強度繊維ト
レカＴ８００ （東し株式会社製）とエポキシ樹脂とか
らなる複合材料層１をｏｏ、±４５°、９０゜の角度に
並べた擬似等方性の積層板の４５°と９０’の層間にポ
リオレフィンフィルム２を設けである。In the example shown in the figure, a composite material layer 1 made of high-strength fiber trading card T800 (manufactured by Toshi Co., Ltd.) aligned in one direction and an epoxy resin is arranged at angles of oo, ±45°, and 90°. A polyolefin film 2 is provided between the 45° and 90' layers of the oriented laminate.
ここで用いたポリオレフィンフィルム２は不飽和カルボ
ン酸で変性した接着性ポリプロピレンを外層とし、内層
はプロピレン、ブテンを主体とするＴｇ６０℃で且つ融
点を示さない共重合体である３層構造のものを用いた。The polyolefin film 2 used here has a three-layer structure with an outer layer made of adhesive polypropylene modified with an unsaturated carboxylic acid, and an inner layer made of a copolymer mainly composed of propylene and butene with a Tg of 60°C and no melting point. Using.
成形は、半硬化状態の複合材料層ｌとポリオレフィンフ
ィルム２とを積層し、オートクレーブで加熱加圧硬化さ
せることにより行った。The molding was performed by laminating the semi-cured composite material layer 1 and the polyolefin film 2 and curing them under heat and pressure in an autoclave.
第２図に、ポリオレフィンフィルム２を０°と４５°の
層間に設けた本発明繊維強化複合材料の断面を、第３図
に、ポリオレフィンフィルム２を９０’層間に設けた本
発明繊維強化複合材料の断面を、第４図に、ポリオレフ
ィンフィルム２を全層間に設けた本発明繊維強化複合材
料の断面をそれぞれ示す。Fig. 2 shows a cross section of the fiber-reinforced composite material of the present invention in which the polyolefin film 2 is provided between the 0° and 45° layers, and Fig. 3 shows the cross-section of the fiber-reinforced composite material of the present invention in which the polyolefin film 2 is provided between the 90° layers. FIG. 4 shows a cross section of a fiber-reinforced composite material of the present invention in which a polyolefin film 2 is provided between all layers.
表１に、第１図〜第４図に示す各実施例の複合材料と、
ポリオレフィンフィルム２を設けていない従来の複合材
料の引張り破断荷重を示す。試験は、２５ ｍｍ １４
］の短冊状試験片を用いて行った。表１より明らかなよ
うに、本発明の繊維強化複合材料は、従来のものに比中
交して、大きな破断強度が得られている。Table 1 shows the composite materials of each example shown in FIGS. 1 to 4,
The tensile breaking load of a conventional composite material without a polyolefin film 2 is shown. The test is 25 mm 14
] using a strip-shaped test piece. As is clear from Table 1, the fiber-reinforced composite material of the present invention has a greater breaking strength than that of the conventional material.
表 １
また、強度のばらつきを表す変動係数も小さくなってお
り、信頼性が向上していることがわかる。Table 1 Furthermore, the coefficient of variation, which represents the variation in strength, has also become smaller, indicating that reliability has improved.
第５図に、第１図実施例の複合材料と、ポリオレフィン
フィルム２を設けていない従来の複合材料との疲労寿命
を示す。試験は、引張り一引張りの繰り返し荷重を加え
行った。縦軸は静的引張強度を基準にし算出した応力比
、横軸は破断回数をそれぞれ表す。図より明らかなとお
り、本発明の繊維強化複合材料は、従来のものに比較し
て、疲労寿命が長いことが分かる。FIG. 5 shows the fatigue life of the composite material of the example shown in FIG. 1 and a conventional composite material in which the polyolefin film 2 is not provided. The test was conducted by applying a repeated load of one tension to another. The vertical axis represents the stress ratio calculated based on static tensile strength, and the horizontal axis represents the number of fractures. As is clear from the figure, the fiber-reinforced composite material of the present invention has a longer fatigue life than the conventional one.
［発明の効果］
以上のように本発明によれば、従来の成形法で機械的強
度に優れた炭素繊維強化複合材料を実現することが可能
となる。また、強度のばらつきを小さくできるため宇宙
航空関連等構造体の信頼性を向上できる効果を有するも
のである。[Effects of the Invention] As described above, according to the present invention, it is possible to realize a carbon fiber reinforced composite material with excellent mechanical strength using a conventional molding method. Furthermore, since variations in strength can be reduced, the reliability of aerospace-related structures can be improved.
第１図〜第４図は本発明に係る炭素繊維強化複合材料を
示す断面図、第５図は第１図実施例の複合材料と従来の
複合材料の疲労寿命を示す図である。1 to 4 are cross-sectional views showing the carbon fiber reinforced composite material according to the present invention, and FIG. 5 is a diagram showing the fatigue life of the composite material of the embodiment shown in FIG. 1 and the conventional composite material.
Claims (1)
層と、合成樹脂フィルムとを組合せてなる炭素繊維強化
複合材料であって、 前記複合材料層と合成樹脂フィルムとは、積層一体化さ
れたものであることを特徴とする炭素繊維強化複合材料
。(1) A carbon fiber-reinforced composite material formed by combining a composite material layer in which carbon fibers are filled in an epoxy resin and a synthetic resin film, wherein the composite material layer and the synthetic resin film are laminated into one piece. A carbon fiber reinforced composite material characterized by:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10445390A JPH044144A (en) | 1990-04-20 | 1990-04-20 | Carbon fiber reinforced composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10445390A JPH044144A (en) | 1990-04-20 | 1990-04-20 | Carbon fiber reinforced composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH044144A true JPH044144A (en) | 1992-01-08 |
Family
ID=14381040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10445390A Pending JPH044144A (en) | 1990-04-20 | 1990-04-20 | Carbon fiber reinforced composite material |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH044144A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105252842A (en) * | 2015-10-30 | 2016-01-20 | 安徽佳力奇航天碳纤维有限公司 | Carbon fiber flat structural member |
-
1990
- 1990-04-20 JP JP10445390A patent/JPH044144A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105252842A (en) * | 2015-10-30 | 2016-01-20 | 安徽佳力奇航天碳纤维有限公司 | Carbon fiber flat structural member |
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