JPH044107A - Prepreg sheet of carbon fiber reinforced composite material - Google Patents
Prepreg sheet of carbon fiber reinforced composite materialInfo
- Publication number
- JPH044107A JPH044107A JP2104451A JP10445190A JPH044107A JP H044107 A JPH044107 A JP H044107A JP 2104451 A JP2104451 A JP 2104451A JP 10445190 A JP10445190 A JP 10445190A JP H044107 A JPH044107 A JP H044107A
- Authority
- JP
- Japan
- Prior art keywords
- composite material
- carbon fiber
- reinforced composite
- prepreg sheet
- fiber reinforced
- 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 21
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 21
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 17
- 239000011208 reinforced composite material Substances 0.000 title claims abstract description 10
- 239000002131 composite material Substances 0.000 claims abstract description 26
- 239000003822 epoxy resin Substances 0.000 claims abstract description 15
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 15
- 239000000463 material Substances 0.000 claims abstract description 12
- 239000003733 fiber-reinforced composite Substances 0.000 claims abstract description 8
- 229920003002 synthetic resin Polymers 0.000 claims abstract description 7
- 239000000057 synthetic resin Substances 0.000 claims abstract description 7
- 230000001070 adhesive effect Effects 0.000 claims abstract description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 239000010410 layer Substances 0.000 abstract description 21
- 229920000098 polyolefin Polymers 0.000 abstract description 12
- 238000010030 laminating Methods 0.000 abstract description 5
- 239000004743 Polypropylene Substances 0.000 abstract description 3
- 239000012790 adhesive layer Substances 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- -1 polypropylene Polymers 0.000 abstract description 3
- 229920001155 polypropylene Polymers 0.000 abstract description 3
- VXNZUUAINFGPBY-UHFFFAOYSA-N 1-Butene Chemical compound CCC=C VXNZUUAINFGPBY-UHFFFAOYSA-N 0.000 abstract description 2
- 239000000853 adhesive Substances 0.000 abstract description 2
- IAQRGUVFOMOMEM-UHFFFAOYSA-N butene Natural products CC=CC IAQRGUVFOMOMEM-UHFFFAOYSA-N 0.000 abstract description 2
- 150000001732 carboxylic acid derivatives Chemical class 0.000 abstract description 2
- 229920001577 copolymer Polymers 0.000 abstract description 2
- 238000002844 melting Methods 0.000 abstract description 2
- 230000008018 melting Effects 0.000 abstract description 2
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 10
- 229920005989 resin Polymers 0.000 description 6
- 239000011347 resin Substances 0.000 description 6
- 239000011159 matrix material Substances 0.000 description 4
- 238000000465 moulding Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000835 fiber 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
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 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
- 230000032798 delamination Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000000155 melt Substances 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
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Adhesive Tapes (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
Description
【発明の詳細な説明】
［産業上の利用分野１
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材料の素材として用いられる炭素
繊維強化複合材料プリプレグシートに関するものである
。[Detailed Description of the Invention] [Industrial Application Field 1] The present invention relates to carbon fiber reinforced composite material prepreg sheets used as structural materials for space structures such as artificial satellites, aircraft, automobiles, leisure goods, etc. be.
［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
用品なとの構造材料として巾広く用いられるようになっ
て来ている。[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 suitable for structural materials such as aerospace, automobiles, and leisure goods. It has come to be widely used as a.
ＣＦ ＲＰ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。The currently mainstream CF RP 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二と、
また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-hardened and flexible state, so structures with complex shapes can be easily manufactured.
It also 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、
引張り破断伸ひか１．５％と、繊維自体の破断伸ひの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 a CFRP with a quasi-isotropic structure based on the high-strength fiber trading card T800 (manufactured by Toshi Co., Ltd.),
Tensile elongation at break: 1.5% and elongation at break of the fiber itself: 1.5%
．． This value is smaller than 9%. 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もあった。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か作製し難いなとの
間顧点かあり効果的ではない。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 as 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. Comparatively speaking, it is difficult to fabricate structures with complex shapes, so 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の成形方法を用いて機械的強
度に優れた炭素繊維強化複合材料を提イ共する二どにあ
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］
前記目的を達成するため、本発明に係る炭素繊維強化複
合材料プリプレグシートにおいては、エポキシ樹脂にカ
ーボン繊維を含む半硬化状態の複合材料層と、熱接着性
を有する合成樹脂フィルムとの組合せからなる炭素繊維
強化複合材料プリプレグシートであって、
前記複合材料層と合成樹脂フィルムとは、積層一体止さ
れたものである。[Means for Solving the Problems] In order to achieve the above object, the carbon fiber reinforced composite material prepreg sheet according to the present invention includes a semi-cured composite material layer containing carbon fibers in an epoxy resin, and a thermally adhesive layer. A carbon fiber-reinforced composite material prepreg sheet comprising a synthetic resin film, wherein the composite material layer and the synthetic resin film are laminated and fixed together.
［作用１
本発明の炭素繊維強化複合材料プリプレグシトを任意の
構成に積層するか、又は本発明のプリプレグシートを従
来のプリプレグシートと組み合わせ積層した後、硬化さ
せて得られる複合材ｔトは、層間に合成樹脂フィルムを
有するものとなる。合成樹脂フィルムは、一般に破断伸
びがマトリックス樹脂に用いられているエポキシ樹脂よ
りも大きいため、複合材料層の層間破壊初生を高める二
とが可能となり、層間剥離なとの損傷の進展か抑制され
、引張り強度、疲労強度なとの機械的強度を改善できる
。[Effect 1] The composite material obtained by laminating the carbon fiber reinforced composite prepreg sheet of the present invention in any configuration, or by laminating the prepreg sheet of the present invention in combination with a conventional prepreg sheet and then curing it, is as follows: It has a synthetic resin film between the layers. Synthetic resin films generally have a greater elongation at break than epoxy resins used as matrix resins, so they can increase the initial onset of interlayer fracture in composite material layers, suppressing the progression of damage such as delamination, and Mechanical strength such as tensile strength and fatigue strength can be improved.
〔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プリプレグシ
ートを示す断面図である。FIG. 1 is a sectional view showing a fiber-reinforced composite material prepreg sheet 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炭素
繊維トレカＴ８００ （東し株式会社製）を半硬化処理
したエポキシ樹脂に充填した複合材料層２にポリオレフ
ィンフィルム３を積層・である。ここで用いたポリオレ
フィンフィルム３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°Ｃ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。外層の接着層は、複
合材料層２のエポキシ樹脂の硬化温度である１３５°Ｃ
近辺の温度で溶融するように調整しである。In the example shown in the figure, a polyolefin film 3 is laminated on a composite material layer 2 in which high-strength carbon fiber trading cards T800 (manufactured by Toshi Co., Ltd.) aligned in one direction are filled with semi-cured epoxy resin. The polyolefin film 3 used here has a three-layer structure in which the outer layer is adhesive polypropylene modified with an unsaturated carboxylic acid, and the inner layer is a copolymer mainly composed of propylene and butene with a Tg of 60°C and no melting point. was used. The outer adhesive layer is heated to 135°C, which is the curing temperature of the epoxy resin of composite material layer 2.
It is adjusted so that it melts at a temperature in the vicinity.
第２図に、第１図実施例のプリプレグシートと、ポリオ
レフィンフィルムを持たない従来のプリプレグシートと
を組み合せて積層し、硬化することにより作製した複合
材料の断面図を示す。実施例では、炭素繊維トしカＴ８
００とエポキシ樹脂硬化物からなる複合材料層４をＯｏ
、±４５°、９ｏ°の角度に並べた疑似等方性の積層板
の４５°と９０’の層間にポリオレフィンフィルム３が
挿入された構成となっている。成形は、プリプレグシー
トを積層した徒、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。FIG. 2 shows a cross-sectional view of a composite material produced by laminating and curing the prepreg sheet of the embodiment shown in FIG. 1 and a conventional prepreg sheet without a polyolefin film. In the example, carbon fiber toshika T8
Composite material layer 4 consisting of O0 and cured epoxy resin
The polyolefin film 3 is inserted between the 45° and 90' layers of pseudo-isotropic laminates arranged at angles of , ±45°, and 90°. The molding was performed by heating and pressurizing and curing the laminated prepreg sheets in an autoclave.
第３図〜第５図は、第２図実施例と同様に第１図実施例
のプリプレグシートと従来の７１ノブレグシートとを用
いて作製した複合材料の断面図である。第３図実施例は
ポリオレフィンフィルム３を０°と４５°の層間に設け
た複合材料の断面図を、第４図はポリオレフィンフィル
ム３を９０’層間に設けた複合材料の断面図を、第５図
はポリオレフインフィルム３を全層間に設けた複合材料
の断面図をそれぞれ示す。3 to 5 are cross-sectional views of a composite material produced using the prepreg sheet of the embodiment in FIG. 1 and a conventional 71 knobreg sheet, similar to the embodiment in FIG. 2. FIG. 3 shows a cross-sectional view of a composite material in which a polyolefin film 3 is provided between 0° and 45° layers, FIG. 4 shows a cross-sectional view of a composite material in which a polyolefin film 3 is provided between 90′ layers, and FIG. The figures each show a cross-sectional view of a composite material in which a polyolefin film 3 is provided between all layers.
表１に、第２図〜第５図実施例の複合材料と、ポリオレ
フィンフィルム３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、２５ｍｍ巾の短冊状試験片
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、従来のものに比較して、大きな破断
強度か得られている。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 shows the tensile breaking loads of the composite materials of the embodiments shown in FIGS. 2 to 5 and the conventional composite materials not provided with the polyolefin film 3. The test was conducted using a strip-shaped test piece with a width of 25 mm. As is clear from Table 1, the fiber-reinforced composite material of the present invention has a greater breaking strength than the conventional material. Furthermore, the coefficient of variation, which represents variations in strength, has also become smaller, indicating that reliability has improved.
表 １
第６図に、第２図実施例の複合材料とポリオレフィンフ
ィルム３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、引張り一引張りの紛多ノ返し荷重を加え
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、本発明を用いた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。Table 1 FIG. 6 shows the fatigue life of the composite material of the example shown in FIG. 2 and a conventional composite material not provided with the polyolefin film 3. The test was conducted by applying a tension-to-tension repeated load. 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 using 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のプリプレグシートを用いれば、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, by using the prepreg sheet of the present invention, it is possible to realize a carbon fiber reinforced composite material with excellent mechanical strength using a conventional molding method. In addition, because it can reduce variations in strength, it has the effect of improving the reliability of aerospace-related structures.
第１図は本発明に係る炭素繊維強化複合材料プリプレグ
シートを示す断面図、第２図〜第５図は本発明のプリプ
レグシートを用いて作製した炭素繊維強化複合材料を示
す断面図、第６図は第２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・・・プリプレグシート
３・・ポリオレフィンフィルムFIG. 1 is a sectional view showing a carbon fiber reinforced composite material prepreg sheet according to the present invention, FIGS. 2 to 5 are sectional views showing a carbon fiber reinforced composite material produced using the prepreg sheet of the present invention, and FIG. The figure is a diagram showing the fatigue life of the composite material of the embodiment shown in FIG. 2 and the conventional composite material. 1... Prepreg sheet 3... Polyolefin film
Claims (1)
複合材料層と、熱接着性を有する合成樹脂フィルムとの
組合せからなる炭素繊維強化複合材料プリプレグシート
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
プリプレグシート。(1) A carbon fiber reinforced composite material prepreg sheet consisting of a combination of a semi-cured composite material layer containing carbon fiber in an epoxy resin and a synthetic resin film having thermal adhesive properties, the composite material layer and the synthetic resin The film is a carbon fiber-reinforced composite material prepreg sheet characterized by being integrated into layers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2104451A JPH044107A (en) | 1990-04-20 | 1990-04-20 | Prepreg sheet of carbon fiber reinforced composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2104451A JPH044107A (en) | 1990-04-20 | 1990-04-20 | Prepreg sheet of carbon fiber reinforced composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH044107A true JPH044107A (en) | 1992-01-08 |
Family
ID=14380993
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2104451A Pending JPH044107A (en) | 1990-04-20 | 1990-04-20 | Prepreg sheet of carbon fiber reinforced composite material |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH044107A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354436A (en) * | 2014-11-07 | 2015-02-18 | 湖北三江航天江北机械工程有限公司 | Manufacturing method of composite material shell wound by high-temperature-resistant fiber |
| CN104985828A (en) * | 2015-07-02 | 2015-10-21 | 北京博简复才技术咨询有限公司 | Carbon fiber composite material waistband and manufacturing method thereof |
| CN106863848A (en) * | 2017-02-17 | 2017-06-20 | 南京航空航天大学 | The forming method of the composite material blade of aero-engine |
| WO2021131347A1 (en) | 2019-12-23 | 2021-07-01 | 東レ株式会社 | Prepreg, molded article, and integrally molded article |
-
1990
- 1990-04-20 JP JP2104451A patent/JPH044107A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354436A (en) * | 2014-11-07 | 2015-02-18 | 湖北三江航天江北机械工程有限公司 | Manufacturing method of composite material shell wound by high-temperature-resistant fiber |
| CN104985828A (en) * | 2015-07-02 | 2015-10-21 | 北京博简复才技术咨询有限公司 | Carbon fiber composite material waistband and manufacturing method thereof |
| CN106863848A (en) * | 2017-02-17 | 2017-06-20 | 南京航空航天大学 | The forming method of the composite material blade of aero-engine |
| WO2021131347A1 (en) | 2019-12-23 | 2021-07-01 | 東レ株式会社 | Prepreg, molded article, and integrally molded article |
| EP4082738A1 (en) | 2019-12-23 | 2022-11-02 | Toray Industries, Inc. | Prepreg, molded article, and integrally molded article |
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