JPH0343227B2 - - Google Patents
Info
- Publication number
- JPH0343227B2 JPH0343227B2 JP63279978A JP27997888A JPH0343227B2 JP H0343227 B2 JPH0343227 B2 JP H0343227B2 JP 63279978 A JP63279978 A JP 63279978A JP 27997888 A JP27997888 A JP 27997888A JP H0343227 B2 JPH0343227 B2 JP H0343227B2
- Authority
- JP
- Japan
- Prior art keywords
- carbon
- mandrel
- temperature
- resin
- carbon fiber
- 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.)
- Expired - Lifetime
Links
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 34
- 229910052799 carbon Inorganic materials 0.000 claims description 31
- 239000002131 composite material Substances 0.000 claims description 23
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 17
- 239000004917 carbon fiber Substances 0.000 claims description 17
- 238000010438 heat treatment Methods 0.000 claims description 12
- 238000003763 carbonization Methods 0.000 claims description 10
- 229920005989 resin Polymers 0.000 claims description 9
- 239000011347 resin Substances 0.000 claims description 8
- 238000004519 manufacturing process Methods 0.000 claims description 7
- 238000004804 winding Methods 0.000 claims description 7
- 239000012298 atmosphere Substances 0.000 claims description 6
- 238000010030 laminating Methods 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 229910010293 ceramic material Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 description 9
- 239000011159 matrix material Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000011280 coal tar Substances 0.000 description 3
- 229910002804 graphite Inorganic materials 0.000 description 3
- 239000010439 graphite Substances 0.000 description 3
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 3
- 229910010271 silicon carbide Inorganic materials 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- YLQBMQCUIZJEEH-UHFFFAOYSA-N Furan Chemical compound C=1C=COC=1 YLQBMQCUIZJEEH-UHFFFAOYSA-N 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- 239000003575 carbonaceous material Substances 0.000 description 2
- 238000010000 carbonizing Methods 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 239000012299 nitrogen atmosphere Substances 0.000 description 2
- FRWYFWZENXDZMU-UHFFFAOYSA-N 2-iodoquinoline Chemical compound C1=CC=CC2=NC(I)=CC=C21 FRWYFWZENXDZMU-UHFFFAOYSA-N 0.000 description 1
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
- 229910052580 B4C Inorganic materials 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N Phenol Chemical compound OC1=CC=CC=C1 ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 1
- 239000004642 Polyimide Substances 0.000 description 1
- 229920000297 Rayon Polymers 0.000 description 1
- 229910052581 Si3N4 Inorganic materials 0.000 description 1
- 229910026551 ZrC Inorganic materials 0.000 description 1
- OTCHGXYCWNXDOA-UHFFFAOYSA-N [C].[Zr] Chemical compound [C].[Zr] OTCHGXYCWNXDOA-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 239000012300 argon atmosphere Substances 0.000 description 1
- LTPBRCUWZOMYOC-UHFFFAOYSA-N beryllium oxide Inorganic materials O=[Be] LTPBRCUWZOMYOC-UHFFFAOYSA-N 0.000 description 1
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical compound B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 description 1
- 150000001721 carbon Chemical class 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000000280 densification Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000009730 filament winding Methods 0.000 description 1
- 239000007849 furan resin Substances 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 238000005470 impregnation Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- NFFIWVVINABMKP-UHFFFAOYSA-N methylidynetantalum Chemical compound [Ta]#C NFFIWVVINABMKP-UHFFFAOYSA-N 0.000 description 1
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000011295 pitch Substances 0.000 description 1
- 229920002239 polyacrylonitrile Polymers 0.000 description 1
- 229920001721 polyimide Polymers 0.000 description 1
- 238000011417 postcuring Methods 0.000 description 1
- 239000002243 precursor Substances 0.000 description 1
- 239000002964 rayon Substances 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910003468 tantalcarbide Inorganic materials 0.000 description 1
- 238000005979 thermal decomposition reaction Methods 0.000 description 1
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 description 1
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 description 1
- 229910001928 zirconium oxide Inorganic materials 0.000 description 1
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、炭素繊維強化炭素複合材の製法に関
するものである。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention relates to a method for producing carbon fiber-reinforced carbon composite materials.
炭素繊維強化炭素複合材は、マトリツクスが炭
素又は黒鉛であるため、昇華温度が高く、高温に
なる程機械的特性が向上し、熱衝撃に強く、アブ
レーチヨン性能に優れ、化学的に不活性である。
それに加え、炭素繊維で強化されているために機
械的特性が一般の炭素材料に比較して著しく良好
である。したがつて、炭素繊維強化炭素複合材
は、高温断熱材や航空機ブレーキ材や宇宙工業用
構造材等に広く使用されている。 Carbon fiber-reinforced carbon composites have a matrix of carbon or graphite, so they have a high sublimation temperature, and the higher the temperature, the better their mechanical properties, resistance to thermal shock, excellent ablation performance, and chemical inertness. .
In addition, because it is reinforced with carbon fiber, its mechanical properties are significantly better than that of general carbon materials. Therefore, carbon fiber-reinforced carbon composite materials are widely used in high-temperature insulation materials, aircraft brake materials, structural materials for the aerospace industry, and the like.
〔従来技術及び問題点〕
従来、中空円筒状炭素繊維強化炭素複合材の製
法は、通常、スチール製マンドレルに炭素繊維の
フイラメント又はテープをワインドし硬化後、マ
ンドレルから脱型したのち、炭素化するか、又
は、円筒状金型を用いて、その内側に炭素繊維プ
リプグレを積層後、加圧硬化させ脱型したのち、
炭化させていた。しかし、この炭化時において、
変形剥離、割れ等の構造的損傷を生ずることが多
く、特に肉厚の炭素繊維強化炭素複合材を構造的
損傷なしに製造することは著しく困難であつた。[Prior art and problems] Conventionally, the method for manufacturing hollow cylindrical carbon fiber reinforced carbon composite materials is to wind a carbon fiber filament or tape around a steel mandrel, cure it, remove it from the mandrel, and then carbonize it. Or, using a cylindrical mold, after laminating carbon fiber prepure on the inside thereof, curing it under pressure and removing it from the mold,
It was carbonized. However, during this carbonization,
Structural damage such as deformation and peeling and cracking often occurs, and it has been extremely difficult to manufacture particularly thick carbon fiber-reinforced carbon composite materials without structural damage.
これらの損傷が生ずる要因として次の如く考え
られる。 The following factors may be considered to cause these damages.
炭化工程において、マトリツクスは初期の加熱
工程で熱膨張を起こし、次いで、熱分解により体
積収縮を起こす。強化繊維は熱膨張係数が非常に
小さいので、マトリツクスの変形との差により、
大きな内部応力が発生する。更に、マトリツクス
が炭化されるまでの中間段階において、マトリツ
クスが強度的に非常に弱くなる過程があるため、
内部応力がマトリツクスの強度により大となり、
前記の如く構造的損傷が生ずる。 In the carbonization process, the matrix undergoes thermal expansion during an initial heating step and then volumetric contraction due to thermal decomposition. The reinforcing fiber has a very small coefficient of thermal expansion, so due to the difference in matrix deformation,
Large internal stresses occur. Furthermore, in the intermediate stage before the matrix is carbonized, there is a process in which the strength of the matrix becomes extremely weak.
The internal stress increases due to the strength of the matrix,
Structural damage occurs as described above.
本発明者等は、この問題を解決すべく鋭意検討
の結果、本発明に至つた。本発明の目的は、変形
剥離、割れ等の構造的損傷のない肉厚の中空の円
柱、角柱、円錐、截頭円錐、三角フラスコ形、ワ
インボルト形等の炭素繊維強化炭素複合材を製造
する方法を提供することである。
The inventors of the present invention have conducted intensive studies to solve this problem, and as a result, have arrived at the present invention. The purpose of the present invention is to manufacture carbon fiber-reinforced carbon composite materials in the shape of thick hollow cylinders, prisms, cones, truncated cones, Erlenmeyer flasks, wine bolts, etc., without structural damage such as deformation and peeling, cracking, etc. The purpose is to provide a method.
本発明は下記の通りである。 The present invention is as follows.
500〜1500℃の炭素化温度又は2000℃以上の熱
処理温度において不活性雰囲気中で炭素と反応せ
ず、１×10-5／℃以下の線膨張係数を有し、か
つ、その炭素化温度以上又は熱処理温度以上の融
点をもつセラミツク材料からなるマンドレルに、
樹脂を含浸した炭素繊維を捲回積層するか、又
は、炭素繊維を捲回積層したのち樹脂を含浸し、
次いで、硬化したのち500〜1500℃で炭素化する
か、又は、更に2000℃以上で熱処理することを特
徴とする炭素繊維強化炭素複合材の製法。 Does not react with carbon in an inert atmosphere at a carbonization temperature of 500 to 1500℃ or a heat treatment temperature of 2000℃ or higher, has a linear expansion coefficient of 1×10 -5 /℃ or less, and is higher than the carbonization temperature Or, on a mandrel made of ceramic material with a melting point higher than the heat treatment temperature,
By winding and laminating carbon fibers impregnated with resin, or by winding and laminating carbon fibers and then impregnating them with resin,
A method for producing a carbon fiber-reinforced carbon composite material, which is then cured and then carbonized at 500 to 1,500°C, or further heat-treated at 2,000°C or higher.
本発明によれば、構造的損傷のない肉厚の中空
の炭素繊維強化炭素複合材を容易に製造すること
が可能である。 According to the present invention, it is possible to easily manufacture a thick, hollow carbon fiber-reinforced carbon composite material without structural damage.
以下、本発明を更に詳細に説明する。 The present invention will be explained in more detail below.
本発明に用いられるマンドレルの材質は、500
〜1500℃の炭素化温度において、又は、2000℃以
上の熱処理温度において窒素又はアルゴン等の不
活性雰囲気中で炭素と反応せず、線膨張係数が１
×10-5／℃以下、好ましくは５×10-5／℃以下で
あり、かつ、その炭素化温度以上又は熱処理温度
以上に融点を持つセラミツク材料である。 The material of the mandrel used in the present invention is 500
It does not react with carbon in an inert atmosphere such as nitrogen or argon at a carbonization temperature of ~1500℃ or a heat treatment temperature of 2000℃ or higher, and its linear expansion coefficient is 1.
×10 -5 /°C or less, preferably 5 × 10 -5 /°C or less, and has a melting point higher than its carbonization temperature or heat treatment temperature.
ここでいうセラミツク材料とは、酸化ベリリウ
ム、酸化ジルコニウム、ボロンカーバイド、炭化
ケイ素、炭化タンタル、炭化チタン、炭化タング
ステン、炭化ジルコニウム、窒化ケイ素を主成分
とする材料である。 The ceramic material referred to herein is a material whose main components are beryllium oxide, zirconium oxide, boron carbide, silicon carbide, tantalum carbide, titanium carbide, tungsten carbide, zirconium carbide, and silicon nitride.
本発明において、マンドレルの材質を限定する
理由は、下記の通りである。 In the present invention, the reason why the material of the mandrel is limited is as follows.
マンドレルに捲回積層した炭素繊維及び樹脂か
らなる成形物を500〜1500℃の温度で炭素化し炭
素繊維強化炭素複合材を得るか又は該複合材を更
に緻密化するために、樹脂又はコールタール、ピ
ツチ等に含浸したのち炭素化するか、又は、必要
により更に2000℃以上の温度で熱処理する場合に
おいて、窒素又はアルゴン等の不活性雰囲気中で
マンドレルの材料が該複合材の主成分である炭素
又は黒鉛と反応したのでは、機械的特性に満足し
得る炭素繊維強化炭素複合材が得られないからで
ある。また、500〜1500℃以上の融点を持ち、又
は、必要により2000℃以上で熱処理する場合はそ
の熱処理温度以上の融点を持ち、しかも、その温
度で該成形物の内表面の変形を防ぎ得る強度を持
つ材質からなるマンドレルでなければならないの
である。更に、マンドレルは、上記炭素化温度又
は熱処理温度で熱膨張する際、複合材を損傷して
ならないので、線膨張係数が１×10-5／℃以下で
なければならない。それを超えると、マンドレル
の熱膨張と複合材の熱膨張の差により複合材が破
壊される。 In order to obtain a carbon fiber-reinforced carbon composite material by carbonizing a molded product made of carbon fibers and resin wound and laminated on a mandrel at a temperature of 500 to 1500°C, or to further densify the composite material, resin or coal tar, In cases where the material of the mandrel is impregnated with pitch etc. and then carbonized, or further heat treated at a temperature of 2000°C or higher if necessary, in an inert atmosphere such as nitrogen or argon, the carbon which is the main component of the composite material is Otherwise, if it reacts with graphite, a carbon fiber-reinforced carbon composite material with satisfactory mechanical properties cannot be obtained. In addition, it has a melting point of 500 to 1,500℃ or higher, or if necessary, if heat treatment is performed at 2,000℃ or higher, a melting point that is higher than the heat treatment temperature, and has a strength that can prevent the inner surface of the molded product from deforming at that temperature. The mandrel must be made of a material that has a Further, the mandrel must have a linear expansion coefficient of 1×10 −5 /° C. or less in order not to damage the composite material when it thermally expands at the above carbonization temperature or heat treatment temperature. If this is exceeded, the composite will fail due to the difference between the thermal expansion of the mandrel and the composite.
マンドレルの形状は、円筒（柱）、角柱、截形
の外、截頭錐形、三角フラスコ形、ワインボトル
形、その他の形状のものが目的物の形状に合せて
選定される。 The shape of the mandrel may be a cylinder (column), a prism, a truncated shape, a truncated pyramid, an Erlenmeyer flask, a wine bottle, or other shapes depending on the shape of the object.
本発明に使用される炭素繊維は、レーヨン、ポ
リアクリロニトリル、ピツチ等を主成分とするプ
レカーサーを不活性雰囲気中で1000〜2000℃で炭
化した炭素質繊維、又は、2000℃以上の温度で黒
鉛化した黒鉛質繊維である。 The carbon fibers used in the present invention are carbon fibers obtained by carbonizing a precursor mainly composed of rayon, polyacrylonitrile, pitch, etc. at 1000 to 2000°C in an inert atmosphere, or graphitized at a temperature of 2000°C or higher. It is a graphite fiber.
炭素繊維をマンドレルの周囲に捲回積層するに
は、炭素繊維のフイラメント又はテープをワイン
ドするか、又は、炭素繊維の一方向シート、織
物、マツト等をマンドレルの周囲にローリングす
る方法が採用される。 In order to wind and laminate carbon fibers around a mandrel, winding a filament or tape of carbon fibers, or rolling a unidirectional sheet, fabric, mat, etc. of carbon fibers around a mandrel is adopted. .
本発明では、マンドレルに、樹脂を含浸した炭
素繊維を捲回積層するか、又は、炭素繊維を捲回
積層したのち樹脂を含浸し、次いで硬化を行う。
この際、必要により予備硬化を行い成形を容易に
することも可能である。 In the present invention, resin-impregnated carbon fibers are wound and laminated on a mandrel, or carbon fibers are wound and laminated on a mandrel and then impregnated with a resin, and then cured.
At this time, if necessary, it is also possible to perform preliminary curing to facilitate molding.
成形硬化に使用する樹脂は、フラン、フエノー
ル、ポリイミド、エポキシ等の各樹脂である。樹
脂が高粘度のもの又は固体である場合には、適当
な溶媒に溶かすか、又は加熱して溶融して用い
る。また、必要により緻密化するために複合材を
フラン樹脂、フエノール樹脂、コールタール、ピ
ツチ等に含浸し、不活性雰囲気中で炭化すること
も可能である。更に、高温で熱処理することによ
り、炭素質を黒鉛質に変えることも可能である。 The resin used for molding and curing is furan, phenol, polyimide, epoxy, and the like. When the resin is highly viscous or solid, it is used by dissolving it in an appropriate solvent or by heating it to melt it. Further, in order to make the composite material denser if necessary, it is also possible to impregnate the composite material with furan resin, phenolic resin, coal tar, pitch, etc., and carbonize it in an inert atmosphere. Furthermore, it is also possible to change carbonaceous material to graphitic material by heat treatment at high temperature.
マンドレルは上記の最終工程まで挿入したまま
でもよいし、複合材が緻密化し充分な強度を保持
したら、除去したのち更に処理を行なつてもよ
い。 The mandrel may remain inserted until the final step described above, or it may be removed after the composite material is densified and maintains sufficient strength for further processing.
マンドレルを中空状とし、その側面に幾つかの
小さな穴をあけて、複合材の緻密化工程での含浸
を容易にすることも可能である。 It is also possible for the mandrel to be hollow and have several small holes in its side to facilitate impregnation during the densification process of the composite.
使用目的によつては、内層にマンドレルを残し
たまま外層を炭素繊維強化炭素複合材の２層構造
として使用することも可能である。 Depending on the purpose of use, it is also possible to use the outer layer as a two-layer structure of carbon fiber-reinforced carbon composite material while leaving the mandrel in the inner layer.
実施例 １
線膨張係数4.7×10-6／℃を有する炭化ケイ素
からなるマンドレル（外径10mm）を使用して、フ
エノール樹脂（住友化学社製スミライトレンジ
PR−50273）を含浸した炭素繊維（東邦レーヨン
社製ベスフアイトHTA−6000）を、フイラメ
ントワインド法によりマンドレルに巻き角度60゜
で捲回積層し、外径35mmの成形物を得た。この成
形物を170℃で１時間硬化し、250℃で６時間ポス
トキユアしたのち、窒素雰囲気中で50℃／時間で
1000℃まで昇温し炭素化した。
Example 1 Using a mandrel (outer diameter 10 mm) made of silicon carbide with a coefficient of linear expansion of 4.7 × 10 -6 /°C,
Carbon fiber (Besphite HTA-6000 manufactured by Toho Rayon Co., Ltd.) impregnated with PR-50273) was wound around a mandrel by the filament winding method at an angle of 60° and laminated to obtain a molded product with an outer diameter of 35 mm. This molded product was cured at 170℃ for 1 hour, post-cured at 250℃ for 6 hours, and then cured at 50℃/hour in a nitrogen atmosphere.
The temperature was raised to 1000℃ to carbonize.
この複合材を緻密化するため、コールタールへ
の浸漬と前記条件での炭素化とを６回繰返した。 In order to densify this composite material, immersion in coal tar and carbonization under the above conditions were repeated six times.
次いで、芯部の炭化ケイ素材マンドレルを切削
除去したのち、アルゴン雰囲気中で50℃１時間で
昇温し2800℃て黒鉛化した。 Next, the core silicon carbide mandrel was cut and removed, and then the temperature was raised to 50°C for 1 hour in an argon atmosphere to 2800°C to graphitize.
その結果、見掛密度1.55ｇ／cm3のクラツクのな
い均質な円筒状炭素繊維強化炭素複合材が得られ
た。 As a result, a homogeneous cylindrical carbon fiber-reinforced carbon composite material with no cracks and an apparent density of 1.55 g/cm 3 was obtained.
比較例 １
通常のスチール材（線膨張係数２×10-5／℃）
からなるマンドレル（外径30mm）を使用して、実
施例１と同様にして、巻き角度45℃で捲回積層し
て、外径75mmの成形物を得た。この成形物を170
℃で１時間硬化したのち、内芯のスチール製マン
ドレルを引抜いて、更に250℃で８時間ポストキ
ユアした。Comparative example 1 Ordinary steel material (linear expansion coefficient 2×10 -5 /℃)
Using a mandrel (outer diameter 30 mm), winding and lamination were carried out in the same manner as in Example 1 at a winding angle of 45° C. to obtain a molded product with an outer diameter of 75 mm. This molded product is 170
After curing at 250°C for 1 hour, the inner core steel mandrel was pulled out and post-curing was further carried out at 250°C for 8 hours.
これを窒素雰囲気中で50℃／時間で1000℃まで
昇温し炭素化した。その結果、クラツクが著しく
多発した品質不良の炭素繊維強化炭素複合材が得
られた。 This was heated to 1000°C at a rate of 50°C/hour in a nitrogen atmosphere to carbonize it. As a result, a poor quality carbon fiber-reinforced carbon composite material with a significant number of cracks was obtained.
Claims (1)
熱処理温度において不活性雰囲気中で炭素と反応
せず、１×10-5／℃以下の線膨張係数を有し、か
つ、その炭素化温度以上又は熱処理温度以上の融
点をもつセラミツク材料からなるマンドレルに、
樹脂を含浸した炭素繊維を捲回積層するか、又
は、炭素繊維を捲回積層したのち樹脂を含浸し、
次いで、硬化したのち500〜1500℃で炭素化する
か、又は、更に2000℃以上で熱処理することを特
徴とする炭素繊維強化炭素複合材の製法。1. Does not react with carbon in an inert atmosphere at a carbonization temperature of 500 to 1500℃ or a heat treatment temperature of 2000℃ or higher, has a linear expansion coefficient of 1×10 -5 /℃ or less, and has a carbonization temperature on a mandrel made of ceramic material with a melting point above or above the heat treatment temperature,
By winding and laminating carbon fibers impregnated with resin, or by winding and laminating carbon fibers and then impregnating them with resin,
A method for producing a carbon fiber-reinforced carbon composite material, which is then cured and then carbonized at 500 to 1,500°C, or further heat-treated at 2,000°C or higher.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63279978A JPH01153571A (en) | 1988-11-05 | 1988-11-05 | Production of carbon composite material reinforced with carbon fiber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63279978A JPH01153571A (en) | 1988-11-05 | 1988-11-05 | Production of carbon composite material reinforced with carbon fiber |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10717180A Division JPS5734085A (en) | 1980-08-06 | 1980-08-06 | Manufacture of carbon fiber reinforced carbon composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01153571A JPH01153571A (en) | 1989-06-15 |
| JPH0343227B2 true JPH0343227B2 (en) | 1991-07-01 |
Family
ID=17618599
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63279978A Granted JPH01153571A (en) | 1988-11-05 | 1988-11-05 | Production of carbon composite material reinforced with carbon fiber |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01153571A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11549420B2 (en) | 2019-02-04 | 2023-01-10 | Honda Motor Co., Ltd. | Outboard motor catalytic converter |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3917884A (en) * | 1973-04-23 | 1975-11-04 | Fiber Materials | Method of making wound graphite carbon body |
-
1988
- 1988-11-05 JP JP63279978A patent/JPH01153571A/en active Granted
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3917884A (en) * | 1973-04-23 | 1975-11-04 | Fiber Materials | Method of making wound graphite carbon body |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH01153571A (en) | 1989-06-15 |
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