JPH11254564A - Manufacturing method of carbon honeycomb structure - Google Patents
Manufacturing method of carbon honeycomb structureInfo
- Publication number
- JPH11254564A JPH11254564A JP10062367A JP6236798A JPH11254564A JP H11254564 A JPH11254564 A JP H11254564A JP 10062367 A JP10062367 A JP 10062367A JP 6236798 A JP6236798 A JP 6236798A JP H11254564 A JPH11254564 A JP H11254564A
- Authority
- JP
- Japan
- Prior art keywords
- carbon fiber
- fiber base
- resin prepolymer
- honeycomb structure
- prepolymer
- 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.)
- Granted
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 5
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 5
- 229920005989 resin Polymers 0.000 claims abstract description 42
- 239000011347 resin Substances 0.000 claims abstract description 42
- 239000004962 Polyamide-imide Substances 0.000 claims abstract description 28
- 229920002312 polyamide-imide Polymers 0.000 claims abstract description 28
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 22
- 239000004917 carbon fiber Substances 0.000 claims abstract description 22
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000004744 fabric Substances 0.000 claims abstract description 21
- 238000000034 method Methods 0.000 claims abstract description 7
- 238000004132 cross linking Methods 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims description 9
- 239000000853 adhesive Substances 0.000 claims description 7
- 230000001070 adhesive effect Effects 0.000 claims description 7
- 239000002759 woven fabric Substances 0.000 claims description 4
- 229920002239 polyacrylonitrile Polymers 0.000 claims description 2
- 238000005470 impregnation Methods 0.000 description 6
- 238000003825 pressing Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- ZMXDDKWLCZADIW-UHFFFAOYSA-N N,N-Dimethylformamide Chemical compound CN(C)C=O ZMXDDKWLCZADIW-UHFFFAOYSA-N 0.000 description 3
- 239000002904 solvent Substances 0.000 description 3
- 229920005992 thermoplastic resin Polymers 0.000 description 3
- SECXISVLQFMRJM-UHFFFAOYSA-N N-Methylpyrrolidone Chemical compound CN1CCCC1=O SECXISVLQFMRJM-UHFFFAOYSA-N 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- 230000009477 glass transition Effects 0.000 description 2
- 229920006015 heat resistant resin Polymers 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000005011 phenolic resin Substances 0.000 description 2
- 229920003987 resole Polymers 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 210000002777 columnar cell Anatomy 0.000 description 1
- 238000007429 general method Methods 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 239000002655 kraft paper Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000004745 nonwoven fabric Substances 0.000 description 1
- 239000000123 paper Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Landscapes
- Ceramic Products (AREA)
- Laminated Bodies (AREA)
Abstract
(57)【要約】
【課題】 高温度域での機械的強度に優れ、曲面への加
熱成形性に優れたハニカム構造体を、安価に製造する方
法を提供すること。
【解決手段】 ポリアミドイミド樹脂プレポリマーを含
浸した炭素繊維基布をコルゲート成形し、成形と同時又
は成形後、架橋硬化させた波板シートと、ポリアミドイ
ミド樹脂プレポリマーを含浸した炭素繊維基布からなる
平板シートとを、交互に多数枚積層し、加圧加熱して樹
脂を架橋硬化させて積層体を形成し、この積層体にポリ
アミドイミド樹脂プレポリマーを含浸し、架橋硬化させ
ることを特徴とするカーボンハニカム構造体の製造法。(57) [Summary] [PROBLEMS] To provide a method for inexpensively manufacturing a honeycomb structure excellent in mechanical strength in a high temperature range and excellent in heat formability on a curved surface. SOLUTION: A corrugated carbon fiber base fabric impregnated with a polyamideimide resin prepolymer is formed by corrugating a carbon fiber base fabric impregnated with a polyamideimide resin prepolymer and a carbon fiber base fabric impregnated with the polyamideimide resin prepolymer. And a plurality of flat sheets, which are alternately laminated, pressurized and heated to crosslink and cure the resin to form a laminate, impregnating the laminate with a polyamideimide resin prepolymer, and crosslinking and curing. Of manufacturing a carbon honeycomb structure.
Description
【０００１】[0001]
【産業上の利用分野】本発明は、カーボンハニカム構造
体の製造法に関する。The present invention relates to a method for manufacturing a carbon honeycomb structure.
【０００２】[0002]
【従来の技術】ハニカム構造体は、中空柱状のセルの平
面的集合体よりなり、耐熱性のハニカム構造体は、航空
機用のエンジン周り等、高温部位のサンドイッチパネ
ル、航空機・宇宙機器等の圧力加熱を受ける構造部材、
その他において用いられ、２６０℃程度の環境・常用温
度において経時的な耐熱強度を有するものである。従
来、軽量で高い機械的強度を有する重量比強度に優れた
ハニカム構造体の基材としては、アルミニウム箔、クラ
フト紙等が使用されているが、耐熱性を有するものとし
ては、ステンレス、チタン等の金属箔をハニカム状と
し、ロウ付け加工を施したもの、ガラス繊維、炭素繊維
等を基材とし、これにレゾールフェノール樹脂等の耐熱
性樹脂を付着せしめたもの（繊維強化樹脂ハニカム構造
体）、耐熱性芳香族ポリアミド合成紙を基材とし、これ
にレゾールフェノール樹脂等の耐熱性樹脂を付着せしめ
たもの、等が開発されている。2. Description of the Related Art A honeycomb structure is composed of a planar assembly of hollow columnar cells. Structural members to be heated,
It is used in others and has heat resistance over time in an environment and normal temperature of about 260 ° C. Conventionally, aluminum foil, kraft paper, and the like have been used as a base material of a honeycomb structure that is lightweight, has high mechanical strength, and has excellent mechanical strength. Examples of materials having heat resistance include stainless steel and titanium. Metal foil of honeycomb shape, brazed, glass fiber, carbon fiber, etc. as base material, to which heat-resistant resin such as resol phenol resin is adhered (fiber-reinforced resin honeycomb structure) A heat-resistant aromatic polyamide synthetic paper as a base material to which a heat-resistant resin such as a resol phenol resin is adhered has been developed.
【０００３】このうち繊維強化樹脂ハニカム構造体は、
比強度、比剛性に優れているため、従来、航空機部品と
して使用されてきている。これをさらに航空機エンジン
用部品として使用する場合は、高温度域（１２０〜１５
０℃）での機械的強度に優れ、且つ２次及び３次曲面へ
の加熱成形性に優れていることが要求される。従来は高
温度域での機械的強度と、加熱成形性という２つの要求
を満足させるために、２５０℃以上のガラス転移点を有
し（従って、２５０℃以上で樹脂が柔らかくなり容易に
成形ができる）、且つガラス転移点より１００℃低い温
度では、加熱による機械的性能の劣化がないという特性
を持つ熱可塑性樹脂が使用されてきた。しかし、この熱
可塑性樹脂は通常は固体であり、適当な溶媒がないた
め、これを使用してハニカム構造体を製造する際には、
樹脂を３５０℃以上の温度まで加熱して液状にすること
が必要となる。このため、特殊な製造設備が必要とな
り、効率も悪く、コスト高となる。また、熱可塑性樹脂
そのものも高価である。[0003] Among them, the fiber-reinforced resin honeycomb structure is
Because of its excellent specific strength and specific rigidity, it has been conventionally used as an aircraft component. When this is further used as a component for an aircraft engine, the high temperature range (120 to 15)
(0 ° C.) and excellent heat moldability to secondary and tertiary curved surfaces. Conventionally, in order to satisfy the two requirements of mechanical strength in a high temperature range and heat moldability, it has a glass transition point of 250 ° C. or more (the resin becomes soft at 250 ° C. or more and molding is easy At a temperature 100 ° C. lower than the glass transition point, a thermoplastic resin has been used which has the property that the mechanical performance is not deteriorated by heating. However, since this thermoplastic resin is usually solid and there is no suitable solvent, when manufacturing a honeycomb structure using this,
It is necessary to heat the resin to a temperature of 350 ° C. or more to make it liquid. For this reason, special manufacturing equipment is required, the efficiency is low, and the cost is high. Also, the thermoplastic resin itself is expensive.
【０００４】[0004]
【発明が解決しようとする課題】従って、本発明の目的
は、高温度域（１２０〜１５０℃）での機械的強度に優
れ、且つ曲面への加熱成形性に優れたハニカム構造体
を、安価に製造する方法を提供することである。SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide a honeycomb structure having excellent mechanical strength in a high temperature range (120 to 150 ° C.) and excellent heat moldability on a curved surface at a low cost. To provide a manufacturing method.
【０００５】[0005]
【課題を解決するための手段】本発明は、ポリアミドイ
ミド樹脂プレポリマーを含浸した炭素繊維基布をコルゲ
ート成形し、成形と同時又は成形後、架橋硬化させた波
板シートと、ポリアミドイミド樹脂プレポリマーを含浸
した炭素繊維基布からなる平板シートとを、接着剤を介
して交互に多数枚積層し、加圧加熱して樹脂を架橋硬化
させて積層体を形成し、この積層体にポリアミドイミド
樹脂プレポリマーを含浸し、架橋硬化させることを特徴
とするカーボンハニカム構造体の製造法である。SUMMARY OF THE INVENTION The present invention relates to a corrugated carbon fiber base fabric impregnated with a polyamideimide resin prepolymer, which is corrugated and molded simultaneously with or after molding, and then cross-linked and cured. A plurality of flat sheets made of a carbon fiber base cloth impregnated with a polymer are alternately laminated with an adhesive, and the laminated body is formed by pressurizing and heating to crosslink and cure the resin to form a laminate. This is a method for producing a carbon honeycomb structure, characterized by impregnating with a resin prepolymer and curing by crosslinking.
【０００６】[0006]
【発明の実施の形態】以下、本発明を詳細に説明する。
本発明において使用される炭素繊維基布は、例えば、ポ
リアクリロニトリル系炭素繊維で造られた織布、編布、
不織布等であり、例えば、1K〜12K (50 g/m2〜600g/
m2)、好ましくは3K、200g/m2 平織の炭素繊維織布が挙
げられる。厚みは通常、 0.1〜0.5 mm程度、幅は 250〜
350 mm程度が適当である。この炭素繊維基布にポリアミ
ドイミド樹脂プレポリマーを含浸する。含浸量は固形分
で20〜80重量％、好ましくは50重量％が適当である。ポ
リアミドイミド樹脂プレポリマーは、例えば、下記式
(1) で表されるものが好ましい。DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below in detail.
The carbon fiber base fabric used in the present invention is, for example, a woven fabric, a knitted fabric made of polyacrylonitrile-based carbon fiber,
A nonwoven fabric or the like, for example, 1K~12K (50 g / m 2 ~600g /
m 2 ), preferably 3K, 200 g / m 2 plain weave carbon fiber woven fabric. Thickness is usually about 0.1-0.5 mm, width is 250-
About 350 mm is appropriate. This carbon fiber base fabric is impregnated with a polyamideimide resin prepolymer. The amount of impregnation is suitably 20 to 80% by weight, preferably 50% by weight in solid content. The polyamideimide resin prepolymer is, for example, the following formula
Those represented by (1) are preferred.
【０００７】[0007]
【化２】 Embedded image
【０００８】式中、ｎは１０〜１００の数である。In the formula, n is a number from 10 to 100.
【０００９】式(1) のポリアミドイミド樹脂プレポリマ
ーは、加熱により硬化して下記の式(2) で表される構造
を有するポリアミドイミド樹脂になる。The polyamide-imide resin prepolymer of the formula (1) is cured by heating to give a polyamide-imide resin having a structure represented by the following formula (2).
【００１０】[0010]
【化３】 Embedded image
【００１１】式(1) のポリアミドイミド樹脂プレポリマ
ーは、旭チバ社からローデフタールという商品名で市販
されており容易に入手できる。また、Die Angewandte M
akromolekulare Chemie 40/41 (1974) 139-158記載の方
法で容易に製造できる。このポリアミドイミド樹脂プレ
ポリマーを含浸した炭素繊維基布を、波形ロールを用い
てコルゲート成形する。波形の波の高さ及び幅は２〜３
mm、波のピッチは８〜９mmが適当である。ポリアミドイ
ミド樹脂プレポリマーを含浸した炭素繊維基布（平板）
を、0.1 〜10kgf/cm2 、好ましくは5.0kgf/cm2の圧力を
かけながら、樹脂の粘着性を利用して、コルゲートラッ
クに張り付かせる。次いで同型のラックを、基布の上面
にかぶせ、温度 150〜450 ℃、好ましくは 250〜300
℃、圧力 0.1〜20kgf/cm2 、好ましくは6.0kgf/cm2で、
0.5〜24時間、好ましくは 6時間、加熱加圧して樹脂を
架橋硬化させ、コルゲートシートを製造する。このコル
ゲートシート（波板）に、同様のポリアミドイミド樹脂
プレポリマーからなる接着剤を10〜300g/m2 塗布し、ポ
リアミドイミド樹脂プレポリマーを含浸した炭素繊維基
布（平板）を重ね合わせ、波板と平板を接着剤を介して
多数枚（例えば、それぞれ 150〜400 枚程度）重ね合わ
せ、温度 150〜450 ℃、好ましくは 250℃、圧力 0.1〜
10kgf/cm2 、好ましくは1.0kgf/cm2で、 0.5〜24時間、
好ましくは 6時間、加熱加圧してプレポリマー樹脂を架
橋硬化させ、ハニカム構造体を得る。さらにこれに、ポ
リアミドイミド樹脂プレポリマーを含浸し、同様の条件
で加熱加圧して架橋し、ハニカム構造体を補強してもよ
い。ポリアミドイミド樹脂プレポリマーは、プレポリマ
ーのみからなるものでもよいし、これを適当な溶媒、例
えば、N-メチルピロリドン、ジメチルホルムアミド等に
溶解し、固形分濃度５〜２５重量％にしたものを使用し
てもよい。特に、ポリアミドイミド樹脂プレポリマーを
含浸して、ハニカム構造体を補強する場合には、プレポ
リマーの溶液を使用することが好ましい。この場合、プ
レポリマーの含浸・蒸発・硬化処理はプレポリマーの含
浸量が固形分として１〜１００kg/m3、望ましくは５０k
g/m3 程度になるまで繰り返す。そして、その後所望の
厚み、例えば 0.3〜3 インチ（7.6 〜38mm）の厚みに裁
断して、本発明のハニカム構造体を得る。The polyamide-imide resin prepolymer of the formula (1) is commercially available from Asahi Ciba under the trade name Rohdephthal and is readily available. Also, Die Angewandte M
It can be easily produced by the method described in Akromolekulare Chemie 40/41 (1974) 139-158. The carbon fiber base fabric impregnated with the polyamide-imide resin prepolymer is corrugated using a corrugated roll. Wave height and width are 2-3
mm and a wave pitch of 8 to 9 mm are appropriate. Carbon fiber base fabric impregnated with polyamide-imide resin prepolymer (flat plate)
The, 0.1 ~10kgf / cm 2, while preferably applying a pressure of 5.0 kgf / cm 2, using the adhesion of the resin, thereby stick the corrugated rack. Next, the same type of rack is placed on the upper surface of the base cloth, and the temperature is 150 to 450 ° C, preferably 250 to 300 ° C.
° C., a pressure 0.1~20kgf / cm 2, preferably 6.0 kgf / cm 2,
The resin is crosslinked and cured by heating and pressing for 0.5 to 24 hours, preferably 6 hours, to produce a corrugated sheet. An adhesive made of the same polyamide-imide resin prepolymer is applied to the corrugated sheet (corrugated sheet) in an amount of 10 to 300 g / m 2 , and a carbon fiber base cloth (flat plate) impregnated with the polyamide-imide resin prepolymer is laminated on the corrugated sheet. A large number of plates and flat plates are laminated with an adhesive (for example, about 150 to 400 sheets each), and the temperature is 150 to 450 ° C, preferably 250 ° C, and the pressure is 0.1 to
10 kgf / cm 2, preferably 1.0 kgf / cm 2, 0.5 to 24 hours,
Preferably, the prepolymer resin is crosslinked and cured by heating and pressing for preferably 6 hours to obtain a honeycomb structure. Further, the honeycomb structure may be impregnated with a polyamideimide resin prepolymer and crosslinked by heating and pressing under the same conditions to reinforce the honeycomb structure. The polyamide-imide resin prepolymer may be composed of only the prepolymer or a solution prepared by dissolving the prepolymer in an appropriate solvent, for example, N-methylpyrrolidone, dimethylformamide, or the like, to a solid concentration of 5 to 25% by weight. May be. In particular, when the honeycomb structure is reinforced by impregnation with a polyamideimide resin prepolymer, it is preferable to use a solution of the prepolymer. In this case, the impregnation / evaporation / curing treatment of the prepolymer is carried out when the impregnation amount of the prepolymer is 1 to 100 kg / m 3 as a solid content, preferably 50 k / m 3 .
Repeat until g / m 3 is reached. Then, the honeycomb structure is cut to a desired thickness, for example, 0.3 to 3 inches (7.6 to 38 mm) to obtain the honeycomb structure of the present invention.
【発明の効果】本発明ではポリアミドイミド樹脂プレポ
リマーを使用しているため、比較的低温で架橋させるこ
とができる。また、プレポリマー自体が優れた粘着力を
持っているため、一般的なハニカム構造体の製造法であ
るラック& ギア法を利用して容易にハニカム構造体の製
造ができる。According to the present invention, since a polyamideimide resin prepolymer is used, crosslinking can be performed at a relatively low temperature. In addition, since the prepolymer itself has excellent adhesive strength, the honeycomb structure can be easily manufactured by using a rack and gear method, which is a general method for manufacturing a honeycomb structure.
【実施例１】幅１ｍ、長さ１００ｍの炭素繊維織布（平
織3K、密度（打ち込み本数）縦横共492 本／m 、厚み0.
25mm）に式(1) で表されるポリアミドイミド樹脂プレポ
リマー（液状）を40重量％となるように含浸した。この
ポリアミドイミド樹脂プレポリマーを含浸した炭素繊維
基布を、波形ロールを用いてコルゲート成形した。波形
の波の高さ及び幅は2.7 mm、波のピッチは8.3 mmとし
た。ポリアミドイミド樹脂プレポリマーを含浸した炭素
繊維基布（平板）を、5.0 kgf/cm2 の圧力をかけなが
ら、樹脂の粘着性を利用して、コルゲートラックに張り
付かせた。次いで同型のラックを、基布の上面にかぶ
せ、温度250 ℃、圧力6.0 kgf/cm2 で、６時間、加熱加
圧して樹脂を架橋硬化させ、コルゲートシートを製造し
た。このコルゲートシート（波板）に、同様のポリアミ
ドイミド樹脂プレポリマーからなる接着剤を50g/m2塗布
し、ポリアミドイミド樹脂プレポリマーを含浸した炭素
繊維基布（平板）を重ね合わせ、波板と平板を接着剤を
介して300 枚重ね合わせ、温度250 ℃、圧力1.0 kgf/cm
2 で、６時間、加熱加圧してプレポリマー樹脂を架橋硬
化させ、ハニカム構造体を得た。さらにこれに、ポリア
ミドイミド樹脂プレポリマーをN-メチルピロリドンに溶
解した10重量％溶液を含浸し、205 ℃で１時間加熱して
溶媒を蒸発させ、同様の条件で加熱加圧して架橋し、ハ
ニカム構造体を補強した。この含浸・蒸発・硬化処理を
10回繰り返し、プレポリマーの含浸量を固形分として50
kg/m3 とした。これを厚み12.7mmに裁断し、本発明のハ
ニカム構造体を得た。Example 1 A carbon fiber woven fabric having a width of 1 m and a length of 100 m (plain woven 3K, density (number of shots): 492 lines / m in both length and width, thickness: 0.
25 mm) with a polyamide-imide resin prepolymer (liquid) represented by the formula (1) so as to be 40% by weight. The carbon fiber base fabric impregnated with the polyamide-imide resin prepolymer was corrugated using a corrugated roll. The height and width of the wave of the waveform were 2.7 mm, and the pitch of the wave was 8.3 mm. A carbon fiber base fabric (flat plate) impregnated with a polyamide-imide resin prepolymer was adhered to a corrugated rack using the adhesiveness of the resin while applying a pressure of 5.0 kgf / cm 2 . Next, a rack of the same type was placed on the upper surface of the base cloth, and heated and pressed at a temperature of 250 ° C. and a pressure of 6.0 kgf / cm 2 for 6 hours to crosslink and cure the resin, thereby producing a corrugated sheet. To this corrugated sheet (corrugated sheet), an adhesive made of the same polyamide-imide resin prepolymer is applied at 50 g / m 2 , and a carbon fiber base cloth (flat sheet) impregnated with the polyamide-imide resin prepolymer is laminated, and the corrugated sheet is corrugated. Laminate 300 plates with adhesive, temperature 250 ℃, pressure 1.0 kgf / cm
In 2 above , the prepolymer resin was cross-linked and cured by heating and pressing for 6 hours to obtain a honeycomb structure. Further, this was impregnated with a 10% by weight solution of a polyamideimide resin prepolymer dissolved in N-methylpyrrolidone, heated at 205 ° C. for 1 hour to evaporate the solvent, and cross-linked by heating and pressing under the same conditions. The structure was reinforced. This impregnation / evaporation / hardening treatment
Repeat 10 times, the prepolymer impregnation amount is 50
kg / m 3 . This was cut to a thickness of 12.7 mm to obtain a honeycomb structure of the present invention.
Claims (4)
浸した炭素繊維基布をコルゲート成形し、成形と同時又
は成形後、架橋硬化させた波板シートと、ポリアミドイ
ミド樹脂プレポリマーを含浸した炭素繊維基布からなる
平板シートとを、接着剤を介して交互に多数枚積層し、
加圧加熱して樹脂を架橋硬化させて積層体を形成し、こ
の積層体にポリアミドイミド樹脂プレポリマーを含浸
し、架橋硬化させることを特徴とするカーボンハニカム
構造体の製造法。1. A corrugated sheet obtained by corrugating a carbon fiber base cloth impregnated with a polyamide-imide resin prepolymer, and cross-linking and hardening simultaneously with or after the forming, and a carbon fiber base cloth impregnated with the polyamide-imide resin prepolymer And a flat sheet composed of a large number of layers alternately laminated with an adhesive,
A method for producing a carbon honeycomb structure, comprising forming a laminate by crosslinking the resin by heating under pressure to form a laminate, impregnating the laminate with a polyamideimide resin prepolymer, and crosslinking and curing the laminate.
炭素繊維基布である請求項１記載の製造法。2. The method according to claim 1, wherein the carbon fiber base fabric is a polyacrylonitrile-based carbon fiber base fabric.
２記載の製造法。3. The method according to claim 1, wherein the carbon fiber base fabric is a woven fabric.
記式 (1)で表される繰り返し単位を有する請求項１又は
２又は３記載の製造法。 【化１】 式中、ｎは１０〜１００の数である。4. The method according to claim 1, wherein the polyamide-imide resin prepolymer has a repeating unit represented by the following formula (1). Embedded image In the formula, n is a number from 10 to 100.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP06236798A JP3561407B2 (en) | 1998-03-13 | 1998-03-13 | Method for manufacturing carbon honeycomb structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP06236798A JP3561407B2 (en) | 1998-03-13 | 1998-03-13 | Method for manufacturing carbon honeycomb structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH11254564A true JPH11254564A (en) | 1999-09-21 |
| JP3561407B2 JP3561407B2 (en) | 2004-09-02 |
Family
ID=13198088
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP06236798A Expired - Fee Related JP3561407B2 (en) | 1998-03-13 | 1998-03-13 | Method for manufacturing carbon honeycomb structure |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3561407B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20160002224U (en) | 2014-12-18 | 2016-06-28 | 에스엘 주식회사 | Shift lever of automotive transmission |
| CN108840697A (en) * | 2018-06-29 | 2018-11-20 | 航天材料及工艺研究所 | A kind of carbon/carbon compound material honeycomb and preparation method thereof |
-
1998
- 1998-03-13 JP JP06236798A patent/JP3561407B2/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20160002224U (en) | 2014-12-18 | 2016-06-28 | 에스엘 주식회사 | Shift lever of automotive transmission |
| CN108840697A (en) * | 2018-06-29 | 2018-11-20 | 航天材料及工艺研究所 | A kind of carbon/carbon compound material honeycomb and preparation method thereof |
| CN108840697B (en) * | 2018-06-29 | 2021-07-13 | 航天材料及工艺研究所 | A kind of carbon/carbon composite honeycomb and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3561407B2 (en) | 2004-09-02 |
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