JP2004017355A - Method for manufacturing composite material panel and composite material panel - Google Patents

Method for manufacturing composite material panel and composite material panel Download PDF

Info

Publication number
JP2004017355A
JP2004017355A JP2002172914A JP2002172914A JP2004017355A JP 2004017355 A JP2004017355 A JP 2004017355A JP 2002172914 A JP2002172914 A JP 2002172914A JP 2002172914 A JP2002172914 A JP 2002172914A JP 2004017355 A JP2004017355 A JP 2004017355A
Authority
JP
Japan
Prior art keywords
fabric
woven fabric
resin
molding material
panel
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.)
Withdrawn
Application number
JP2002172914A
Other languages
Japanese (ja)
Inventor
Toshinobu Muraki
村木　俊宣
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP2002172914A priority Critical patent/JP2004017355A/en
Publication of JP2004017355A publication Critical patent/JP2004017355A/en
Withdrawn legal-status Critical Current

Links

Images

Abstract

<P>PROBLEM TO BE SOLVED: To provide a method for manufacturing a composite material panel which can easily manufacture even in a large size and which can exhibit a light weight and a high strength and to provide the composite material panel. <P>SOLUTION: The method for manufacturing the composite material panel includes the steps of intervening a molding material 11 between one woven fabric 13 and other woven fabric 14, connecting the one woven fabric 13 to the other woven fabric 14 at a peripheral edge of the molding material 11, and curing a resin 12. In this method, the molding material 11 has an independent space therein. The method further includes the steps of disposing the resin 12 on the side face of the one woven fabric 13 or the other woven fabric 14, filling the molding material 11, the one woven fabric 14, the other woven fabric 14 and the resin 12 in a bag 19, sucking them in the bag 19 by a negative pressure, impregnating the one woven fabric 13 and the other woven fabric 14 with the resin 12 in a high-temperature and high-pressure environment, and curing them. <P>COPYRIGHT: (C)2004,JPO

Description

【０００１】
【発明の属する技術分野】
本発明は、航空機用のサンドイッチ構造をもつ複合材パネルの製造方法、および複合材パネルに関する。
【０００２】
【従来の技術】
従来、航空機用の複合材パネルとして図５、図６に示すものが知られている。図５において、複合材パネル５０は、蜂の巣状に穴のあいたハニカムコア５１と、樹脂で固めたカーボン繊維の第一の織物５２と第二の織物５３とから構成されている。ハニカムコア５１の端部には、傾斜面５４と、切落し部５５とが設けられている。
【０００３】
上記の構成による複合材パネル５０は、図６に示すように、ハニカムコア５１に、プリプレグ５６と呼ばれる、未硬化樹脂を含浸させたカーボン繊維の第一の織物５２と第二の織物５３とを積層させて、オートクレーブ５７の中に入れて、高温高圧の条件下で樹脂を硬化させて製造される。
【０００４】
または、先にプリプレグ５６のみを積層させて、オートクレーブ５７で硬化させて、その後、ハニカムコア５１の上下に接着して製造されることもある。
【０００５】
【発明が解決しようとする課題】
ところで、上記の構成による複合材パネルの製造方法は、未硬化樹脂の含浸物であるプリプレグの取り扱いが難しく、ハニカムコアの上下に積層させるのに手間がかかるという問題があり、プリプレグを先に硬化させた場合でも、ハニカムコアの上下に接着する工程が新たに必要になり、手間がかかる、コストがかかるという問題は残る。
【０００６】
さらに、ハニカムコアの切落し部において、ハニカムコアの上に積層された第一の織物と、ハニカムコアの下に積層された第二の織物との層間に亀裂が生じやすく、層間剥離を起こしやすいという問題があった。
【０００７】
この発明は、このような事情を考慮してなされたもので、その目的は、サイズが大きくても容易に製造することができ、軽くて、高い強度を発揮することができる複合材パネルの製造方法および複合材パネルを提供することにある。
【０００８】
【課題を解決するための手段】
本発明の複合材パネルの製造方法および複合材パネルでは、上記課題を解決するため、以下の手段を採用した。
請求項１にかかる発明は、一方の織物と他方の織物との間に成形材を介在させ、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とを接合させ、
前記一方の織物と前記他方の織物とを、樹脂で硬化させる複合材パネルの製造方法において、前記成形材として、内部に独立した空間を有するものを用い、前記一方の織物または前記他方の織物の側面に樹脂を配置し、前記成形材と、前記一方の織物と、前記他方の織物と、前記樹脂とを袋体に入れ、前記袋体内を負圧吸引して、高温高圧環境下で、前記樹脂を前記一方の織物および前記他方の織物に含浸させ、硬化させることを特徴とする。
【０００９】
この発明にかかる複合材パネルの製造方法によれば、前記成形材に、内部に独立した空間を持つものを用いるため、前記成形材内部への前記樹脂の含浸が防がれ、少ない前記樹脂の量で、前記一方の織物と前記他方の織物とを十分に含浸させ、硬化させることができる。
【００１０】
また、前記成形材内部への前記樹脂の含浸が防がれるため、前記成形材の重量が増加することを防ぐことができる。
【００１１】
さらに、前記一方の織物と前記他方の織物への前記樹脂の含浸と硬化が、同時に行われるので、未硬化のプリプレグを取り扱う工程がなくなり、作業を楽にすることができる。
【００１２】
請求項２にかかる発明は、請求項１記載の複合材パネルの製造方法において、前記成形材に、予め、前記一方の織物側と前記他方の織物側とに開口部を持つ、樹脂通過手段を設けておき、前記樹脂を、前記樹脂通過手段を通って前記一方の織物または前記他方の織物に含浸させることを特徴とする。
【００１３】
この発明にかかる複合材パネルの製造方法によれば、前記樹脂は、前記樹脂通過手段を通って前記一方の織物または前記他方の織物に含浸するため、前記成形材のサイズが大きくなり、前記樹脂が、前記成形材の前記周縁部から回りこんで前記一方の織物または前記他方の織物に十分に含浸されなくなっても、前記樹脂は、前記樹脂通過手段を通って前記一方の織物または前記他方の織物へ十分に含浸されることができる。
【００１４】
請求項３にかかる発明は、一方の織物と他方の織物との間に成形材を介在させ、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とを接合させ、前記一方の織物と前記他方の織物とを、樹脂で硬化させる複合材パネルの製造方法において、前記一方の織物と前記他方の織物とを、前記周縁部にて、緊縛することを特徴とする。
【００１５】
この発明にかかる複合材パネルの製造方法によれば、前記一方の織物と前記他方の織物とを、前記周縁部にて、緊縛するため、前記一方の織物と前記他方の織物との層間に、せん断方向、引っ張り方向の力を緊縛していることで受け止めることができる。
【００１６】
また、前記一方の織物と前記他方の織物との層間に亀裂が発生しても、前記一方の織物と前記他方の織物とを緊縛していることで、亀裂の進展を止めることができる。
【００１７】
請求項４にかかる発明は、一方の織物と他方の織物との間に成形材が介在され、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とが接合され、前記一方の織物と前記他方の織物とは、樹脂で硬化される複合材パネルにおいて、前記成形材は、内部に独立した空間を有し、前記一方の織物と前記成形材と前記他方の織物とが密着されることを特徴とする。
【００１８】
この発明にかかる複合材パネルによれば、前記成形材は、内部に独立した空間を持つため、前記成形材内部への前記樹脂の含浸が防がれるため、少ない前記樹脂の量で、前記一方の織物と前記他方の織物とを十分に含浸させ、硬化させることができる。
【００１９】
また、前記成形材は、前記成形材内部への前記樹脂の含浸が防がれるため、前記成形材の重量が増加することを防ぐことができる。
【００２０】
請求項５にかかる発明は、請求項４記載の複合材パネルにおいて、前記成形材には、前記一方の織物側と前記他方の織物側とに開口部を持つ、樹脂通過手段が設けられていることを特徴とする。
【００２１】
この発明にかかる複合材パネルによれば、前記成形材には、樹脂通過手段が設けられているため、前記成形材のサイズが大きくなり、前記樹脂が、前記成形材の前記周縁部から回りこんで前記一方の織物または前記他方の織物に十分に含浸されなくなっても、前記樹脂は、前記樹脂通過手段を通って前記一方の織物または前記他方の織物へ十分に含浸されることができる。
【００２２】
請求項６にかかる発明は、一方の織物と他方の織物との間に成形材を介在させ、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とを接合させ、前記一方の織物と前記他方の織物とを、樹脂で硬化される複合材パネルにおいて、前記一方の織物と前記他方の織物とは、前記周縁部にて、緊縛手段を用いて緊縛されることを特徴とする。
【００２３】
この発明にかかる複合材パネルによれば、前記一方の織物と前記他方の織物とを、緊縛する緊縛手段が設けられているため、前記一方の織物と前記他方の織物との層間に、せん断方向、引っ張り方向の力を緊縛手段で受け止めることができる。
【００２４】
また、前記一方の織物と前記他方の織物との層間に亀裂が発生しても、前記一方の織物と前記他方の織物とを緊縛手段で緊縛していることで、亀裂の進展を止めることができる。
【００２５】
【発明の実施の形態】
以下、図面を参照し、この発明の実施の形態について説明する。図１から図２はこの発明の一実施形態を示す図である。
図１において複合材パネル１０は、発泡材（成形材）１１と、樹脂１２で固められた第一の織物（一方の織物）１３と、樹脂１２で固められた第二の織物（他方の織物）１４と、第一の織物１３と第二の織物１４とを緊縛する緊縛糸（緊縛手段）１５とを主な構成要素として構成されたものである。
【００２６】
図２に示すように、発泡材１１には、板状の硬質プラスチック独立気泡発泡体（例えば、Ｒｏｅｍ社のＲＯＨＡＣＥＬＬ７１ＸＴ（登録商標）やＲＯＨＡＣＥＬＬ１１０ＸＴ（登録商標））が用いられていて、発泡材１１の端部には、傾斜面１６と、切落し部１７とが形成され、略中央部には、樹脂流路孔（樹脂通過手段）１８が設けられている。
【００２７】
第一の織物１３と第二の織物１４を構成する繊維には、カーボン繊維（例えば、三菱レイヨン社のＭＲ５０Ｋ（登録商標））や、ガラス繊維などが用いられている。また、第一の織物１３と第二の織物１４とを固める樹脂１２には、ビスマレイミド樹脂（例えば、三菱レイヨン社の＃２０５０（登録商標））や、エポキシ樹脂などが用いられている。
【００２８】
第一の織物１３と第二の織物１４とを緊縛する緊縛糸１５には、アラミド繊維（例えば、Ｄｕｐｏｎｔ社のＫＥＶＬＥＲ４９（登録商標））、カーボン繊維や、ガラス繊維などが用いられている。
【００２９】
上記の構成からなる複合材パネル１０においては、図３に示すように、発泡材１１を挟むように第一の織物１３と第二の織物１４とを積層させて、第一の織物１３と第二の織物１４とを、切落し部１７略外側にて、緊縛糸１５を用いて緊縛する。その後、樹脂１２のフィルムを、第二の織物１４の下に配置し、全体を袋（袋体）１９に包み、袋１９の内部を負圧吸引する。
【００３０】
そして、発泡材１１と第一の織物１３と第二の織物１４と樹脂１２のフィルムとが入った袋１９ごとオートクレーブ２０の中に入れて、温度と圧力とを上げて一定時間保持する、１次硬化を行う。１次硬化において、樹脂１２のフィルムは、融けて隣接する第二の織物１４に含浸し、さらに、樹脂流路孔１８を通って、第一の織物１３に含浸して、硬化する。
【００３１】
１次硬化の次に、さらに、温度を上げて、圧力は大気圧にして、一定時間保持する、２次硬化を行う。２次硬化において、樹脂１２は、その耐熱特性が向上される。
【００３２】
上記の構成により、試作した試作品の強度試験結果について述べる。試作品には、発泡材１１に、Ｒｏｅｍ社のＲＯＨＡＣＥＬＬ１１０ＸＴ（登録商標）と、第一の織物１３と第二の織物１４の繊維に、カーボン繊維である三菱レイヨン社のＭＲ５０Ｋ（登録商標）と、樹脂１２に、ビスマレイミド樹脂である三菱レイヨン社の＃２０５０（登録商標）と、緊縛糸１５に、アラミド繊維であるＤｕｐｏｎｔ社のＫＥＶＬＥＲ４９（登録商標）とが用いられている。
【００３３】
試作品の複合材パネル１０のサイズは、縦４６０ｍｍ、横３５０ｍｍ、高さ２３．６ｍｍで、発泡材１１のサイズは、縦約４４４ｍｍ、横約３３４ｍｍ，高さ約２２ｍｍである。発泡材１１の略中央には直径約２ｍｍの樹脂流路孔１８が設けられている。緊縛糸１５は発泡材１１の外側約３ｍｍと約８ｍｍのところで第一の織物１３と第二の織物１４とを緊縛している。
【００３４】
また、１次硬化の条件は、温度が１９１℃、圧力が０．２５ＭＰａ、保持時間が６時間であり、２次硬化の条件は、温度が２２７℃、圧力が大気圧、保持時間が６時間である。
【００３５】
製作された試作品の複合材パネル１０は、図４（ａ）に示すフラットワイズ・テンション強度試験にて、フラットワイズ・テンション強度（引っ張り強度）が評価され、図４（ｂ）に示す曲げ強度試験にて、せん断強度が評価され、図４（ｃ）に示す端部曲げ強度試験にて、切落し部１７の略外側の第一の織物１３と第二の織物１４との層間強度が評価された。
【００３６】
評価の結果、試作品は、フラットワイズ・テンション強度が２．５ＭＰａで強度は十分高く、せん断強度が１．９ＭＰａで強度は十分高く、切落し部１７の織物の層間強度は十分高いという結果が得られた。
【００３７】
上記の構成によれば、発泡材１１に、樹脂１２が内部に含浸されない硬質プラスチック独立気泡発泡体を用いているため、少ない樹脂１２の量で、第一の織物１３と第二の織物１４とを十分に含浸させ、硬化させることができ、複合材パネル１０の重量を軽くして、かつ、強度を高くすることができる。
【００３８】
また、発泡材１１に、硬質プラスチック独立気泡発泡体を用いているため、樹脂１２の発泡材１１内部への含浸による、発泡材１１の重量増加を防ぐことができるため、複合材パネル１０の重量を軽くして、かつ、強度を高くすることができる。
【００３９】
発泡材１１のサイズが大きくなり、樹脂１２が、発泡材１１の周囲から回りこんで第二の織物１４に十分に含浸されなくなっても、樹脂１２は、発泡材１１略中央部の樹脂流路孔１８を通って第一の織物１３へ十分に含浸されることができるため、複合材パネル１０の強度が高くて、かつ、サイズを大きくすることができる。
【００４０】
切落し部１７略外側にて、第一の織物１３と第二の織物１４とを緊縛糸１５で緊縛しているため、切落し部１７略外側の第一の織物１３と第二の織物１４との層間に、せん断方向、引っ張り方向の力が働いても、緊縛糸１５で受け止めることができるため、複合材パネル１０の強度を高くすることができる。
【００４１】
切落し部１７略外側にて、第一の織物１３と第二の織物１４との層間に亀裂が発生しても、切落し部１７略外側にて、第一の織物１３と第二の織物１４とを緊縛糸１５で緊縛していることで、亀裂の進展を止めることができるため、複合材パネル１０の強度を高くすることができる。
【００４２】
なお、上記の実施の形態においては、複合材パネルの製造方法と複合材パネルを航空機向けのものに適応して説明したが、この複合材パネルの製造方法と複合材パネルを航空機向けのものに限られることなく、自動車のボンネットや、体育館の屋根等その他各種の使用方法に適応することができるものである。
【００４３】
また、上記の実施の形態においては、緊縛手段を緊縛糸に適応してせつめいしたが、この緊縛糸に限られることなく、ホッチキス等その他各種の緊縛手段に適応することができるものである。
【００４４】
【発明の効果】
以上説明したように、請求項１に係る発明によれば、前記成形材内部への前記樹脂の含浸が防がれるため、少ない前記樹脂の量で、前記一方の織物と前記他方の織物とを十分に含浸させ、硬化させることができ、軽くて、強度の高い複合材パネルを製造できるという効果を奏する。
【００４５】
また、前記成形材内部への前記樹脂の含浸が防がれ、前記成形材の重量が増加することを防ぐことができるため、軽くて、強度の高い複合材パネルを製造できるという効果を奏する。
【００４６】
さらに、前記一方の織物と前記他方の織物への前記樹脂の含浸と硬化が、同時に行われるので、未硬化のプリプレグを取り扱う工程がなくなり、作業を楽にすることができ、複合材パネルを容易に製造できるという効果を奏する。
【００４７】
請求項２に係る発明によれば、前記成形材のサイズが大きくなり、前記樹脂が、前記成形材の前記周縁部から回りこんで前記一方の織物に十分に含浸されなくなっても、前記樹脂は、前記樹脂通過手段を通って前記一方の織物または前記他方の織物へ十分に含浸されることができるため、大きなサイズの複合材パネルの製造ができるという効果を奏する。
【００４８】
請求項３に係る発明によれば、前記一方の織物と前記他方の織物とを、前記周縁部にて、緊縛するため、前記一方の織物と前記他方の織物との層間に、せん断方向、引っ張り方向の力を緊縛していることで受け止めることができるため、強度の高い複合材パネルを製造できるという効果を奏する。
【００４９】
また、前記一方の織物と前記他方の織物との層間に亀裂が発生しても、前記一方の織物と前記他方の織物とを緊縛していることで、亀裂の進展を止めることができるため、強度の高い複合材パネルを製造できるという効果を奏する。
【００５０】
請求項４に係る発明によれば、前記成形材内部への前記樹脂の含浸が防がれるため、少ない前記樹脂の量で、前記一方の織物と前記他方の織物とを十分に含浸させ、硬化させることができるため、複合材パネルの重量を軽くし、強度を高くすることができるという効果を奏する。
【００５１】
また、前記樹脂の前記成形材内部への含浸が防がれ、前記成形材の重量が増加することを防ぐことができるため、複合材パネルの重量を軽くし、強度を高くすることができるという効果を奏する。
【００５２】
請求項５に係る発明によれば、前記成形材のサイズが大きくなり、前記樹脂が、前記成形材の前記周縁部から回りこんで前記一方の織物または前記他方の織物に十分に含浸されなくなっても、前記樹脂は、前記樹脂通過手段を通って前記一方の織物または前記他方の織物へ十分に含浸されることができるため、複合材パネルのサイズを大きくすることができるという効果を奏する。
【００５３】
請求項６に係る発明によれば、前記一方の織物と前記他方の織物とを、緊縛する緊縛手段が設けられているため、前記一方の織物と前記他方の織物との層間に、せん断方向、引っ張り方向の力を緊縛手段で受け止めることができ、複合材パネルの強度を、高くすることができるという効果を奏する。
【００５４】
また、前記一方の織物と前記他方の織物との層間に亀裂が発生しても、前記一方の織物と前記他方の織物とを緊縛手段で緊縛していることで、亀裂の進展を止めることができるため、複合材パネルの強度を、高くすることができるという効果を奏する。
【図面の簡単な説明】
【図１】本発明による複合材パネルの一実施形態を示す斜視図である。
【図２】本発明による複合材パネルの一実施形態を示す断面図である。
【図３】本発明による複合材パネルの製造方法の一実施形態を示す断面図である。
【図４】本発明による複合材パネルの試作試験片の評価方法の一例を示す斜視図である。
【図５】従来の複合材パネルの一例を示す斜視図である。
【図６】従来の複合材パネルの製造方法の一例を示す断面図である。
【符号の説明】
１０　複合材パネル
１１　発泡材（成形材）
１２　樹脂
１３　第一の織物（一方の織物）
１４　第二の織物（他方の織物）
１５　緊縛糸（緊縛手段）
１８　樹脂流路孔（樹脂通過手段）
１９　袋（袋体）[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a method for manufacturing a composite panel having a sandwich structure for an aircraft, and a composite panel.
[0002]
[Prior art]
Conventionally, as shown in FIGS. 5 and 6, a composite panel for an aircraft is known. In FIG. 5, a composite material panel 50 includes a honeycomb core 51 having holes in a honeycomb shape, and a first fabric 52 and a second fabric 53 of carbon fibers fixed with resin. At the end of the honeycomb core 51, an inclined surface 54 and a cut-out portion 55 are provided.
[0003]
As shown in FIG. 6, the composite material panel 50 having the above-described configuration includes a honeycomb core 51 and a first woven fabric 52 and a second woven fabric 53 of a carbon fiber impregnated with an uncured resin called a prepreg 56. It is manufactured by laminating, placing in an autoclave 57, and curing the resin under conditions of high temperature and high pressure.
[0004]
Alternatively, it may be manufactured by first laminating only the prepreg 56, curing it with the autoclave 57, and thereafter bonding the honeycomb core 51 to the upper and lower sides.
[0005]
[Problems to be solved by the invention]
By the way, the method for manufacturing a composite material panel according to the above configuration has a problem that it is difficult to handle a prepreg, which is an impregnated material of an uncured resin, and it takes time to stack the prepreg on and under a honeycomb core. Even in this case, a new process of bonding the honeycomb core to the top and bottom of the honeycomb core is required, and the problem that it is troublesome and costly remains.
[0006]
Furthermore, in the cut-off portion of the honeycomb core, a crack is easily generated between the first fabric laminated on the honeycomb core and the second fabric laminated below the honeycomb core, and delamination is easily caused. There was a problem.
[0007]
The present invention has been made in view of such circumstances, and an object of the present invention is to manufacture a composite panel that can be easily manufactured even if it is large in size, and that is lightweight and exhibits high strength. It is to provide a method and a composite panel.
[0008]
[Means for Solving the Problems]
In order to solve the above-mentioned problems, the following method is employed in the method for manufacturing a composite material panel and the composite material panel of the present invention.
The invention according to claim 1, wherein a molding material is interposed between one fabric and the other fabric, and the one fabric and the other fabric are joined at a peripheral portion of the molding material,
In the method of manufacturing a composite material panel in which the one woven fabric and the other woven fabric are cured with a resin, as the molding material, a material having an independent space inside is used, and the one woven fabric or the other woven fabric is used. Placing a resin on the side, the molding material, the one woven fabric, the other woven fabric, and the resin are put in a bag, and the bag is suctioned at a negative pressure, under a high-temperature and high-pressure environment, The resin is impregnated into the one fabric and the other fabric and cured.
[0009]
According to the method of manufacturing a composite material panel according to the present invention, since the molding material having an independent space inside is used, impregnation of the resin into the molding material is prevented, and a small amount of the resin In an amount, the one fabric and the other fabric can be fully impregnated and cured.
[0010]
Further, since the inside of the molding material is prevented from being impregnated with the resin, an increase in the weight of the molding material can be prevented.
[0011]
Furthermore, since the impregnation and curing of the resin into the one woven fabric and the other woven fabric are performed at the same time, the step of handling the uncured prepreg is eliminated, and the work can be facilitated.
[0012]
According to a second aspect of the present invention, in the method for manufacturing a composite material panel according to the first aspect, the molding material further includes a resin passage unit having openings on the one fabric side and the other fabric side in advance. It is characterized in that the resin is impregnated into the one fabric or the other fabric through the resin passage means.
[0013]
According to the method of manufacturing a composite material panel according to the present invention, the resin is impregnated into the one woven fabric or the other woven fabric through the resin passage means, so that the size of the molding material increases, However, even if the one woven fabric or the other woven fabric is not sufficiently impregnated around the peripheral portion of the molding material and is not sufficiently impregnated with the one woven fabric or the other woven fabric, the one woven fabric or the other woven fabric passes through the resin passing means. The fabric can be fully impregnated.
[0014]
The invention according to claim 3, wherein a molding material is interposed between one fabric and the other fabric, and the one fabric and the other fabric are joined at a peripheral portion of the molding material. In the method for producing a composite panel in which the woven fabric and the other woven fabric are cured with a resin, the one woven fabric and the other woven fabric are bound at the peripheral portion.
[0015]
According to the method for manufacturing a composite material panel according to the present invention, in order to bind the one woven fabric and the other woven fabric at the peripheral portion, between the layers of the one woven fabric and the other woven fabric, The force in the shearing direction and the pulling direction can be received by tightening.
[0016]
Further, even if a crack occurs between the layers of the one fabric and the other fabric, the crack can be stopped from growing by tightening the one fabric and the other fabric.
[0017]
The invention according to claim 4 is such that a molding material is interposed between one textile and the other textile, and the one textile and the other textile are joined to each other at a peripheral portion of the molding material. The woven fabric and the other woven fabric are in a composite panel cured with a resin, wherein the molding material has an independent space inside, and the one woven fabric, the molding material, and the other woven fabric are in close contact with each other. It is characterized by being performed.
[0018]
According to the composite material panel of the present invention, since the molding material has an independent space inside, the impregnation of the resin into the molding material is prevented. And the other fabric can be sufficiently impregnated and cured.
[0019]
In addition, since the molding material is prevented from impregnating the inside of the molding material with the resin, it is possible to prevent the weight of the molding material from increasing.
[0020]
The invention according to claim 5 is the composite material panel according to claim 4, wherein the molding material is provided with resin passage means having openings on the one fabric side and the other fabric side. It is characterized by the following.
[0021]
According to the composite material panel of the present invention, since the molding material is provided with the resin passage means, the size of the molding material is increased, and the resin wraps around the periphery of the molding material. Even if the one fabric or the other fabric is not sufficiently impregnated, the resin can be sufficiently impregnated into the one fabric or the other fabric through the resin passage means.
[0022]
The invention according to claim 6, wherein a molding material is interposed between one fabric and the other fabric, and the one fabric and the other fabric are joined at a peripheral portion of the molding material. In the composite material panel, wherein the woven fabric and the other woven fabric are cured with a resin, the one woven fabric and the other woven fabric are tied up using a tying means at the peripheral portion. I do.
[0023]
According to the composite material panel of the present invention, since the tying means for tying the one woven fabric and the other woven fabric is provided, a shear direction is provided between the layers of the one woven fabric and the other woven fabric. The force in the pulling direction can be received by the binding means.
[0024]
Further, even if a crack occurs between the layers of the one woven fabric and the other woven fabric, the growth of the crack can be stopped by tying the one woven fabric and the other woven fabric with the binding means. it can.
[0025]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, embodiments of the present invention will be described with reference to the drawings. 1 and 2 are views showing an embodiment of the present invention.
In FIG. 1, a composite panel 10 includes a foam material (molded material) 11, a first fabric (one fabric) 13 fixed with a resin 12, and a second fabric (the other fabric) fixed with a resin 12. ) 14 and a binding thread (binding means) 15 for binding the first fabric 13 and the second fabric 14 as main components.
[0026]
As shown in FIG. 2, a plate-shaped rigid plastic closed-cell foam (for example, ROHACELL71XT (registered trademark) or ROHACELL110XT (registered trademark) from Roem) is used for the foam material 11. An inclined surface 16 and a cut-out portion 17 are formed at the end, and a resin flow passage hole (resin passage means) 18 is provided at a substantially central portion.
[0027]
Carbon fibers (for example, MR50K (registered trademark) of Mitsubishi Rayon Co., Ltd.), glass fibers, and the like are used for the fibers constituting the first fabric 13 and the second fabric 14. As the resin 12 for solidifying the first fabric 13 and the second fabric 14, a bismaleimide resin (for example, # 2050 (registered trademark) of Mitsubishi Rayon Co., Ltd.), an epoxy resin, or the like is used.
[0028]
Aramid fiber (for example, KEVLER49 (registered trademark) of Dupont), carbon fiber, glass fiber, or the like is used as the binding yarn 15 for binding the first fabric 13 and the second fabric 14.
[0029]
In the composite panel 10 having the above configuration, as shown in FIG. 3, the first fabric 13 and the second fabric 14 are laminated so as to sandwich the foam material 11, and the first fabric 13 and the second fabric 13 are laminated. The second fabric 14 is tied with the tying thread 15 almost outside the cut-off portion 17. Thereafter, a film of the resin 12 is placed under the second fabric 14, the whole is wrapped in a bag (bag body) 19, and the inside of the bag 19 is subjected to negative pressure suction.
[0030]
Then, the bag 19 containing the foam material 11, the first fabric 13, the second fabric 14, and the film of the resin 12 is put into the autoclave 20, and the temperature and the pressure are increased and held for a certain time. Next curing is performed. In the primary curing, the film of the resin 12 is melted and impregnated into the adjacent second fabric 14, further impregnated into the first fabric 13 through the resin flow passage hole 18, and cured.
[0031]
After the primary curing, a secondary curing is performed in which the temperature is further increased, the pressure is set to the atmospheric pressure, and the pressure is maintained for a certain period of time. In the secondary curing, the heat resistance of the resin 12 is improved.
[0032]
The strength test result of the prototype manufactured by the above configuration will be described. In the prototype, the foam material 11 is ROHACELL110XT (registered trademark) from Roem, and the fibers of the first fabric 13 and the second fabric 14 are MR50K (registered trademark) of Mitsubishi Rayon Co., which is carbon fiber. The resin 12 uses # 2050 (registered trademark) of Mitsubishi Rayon Co., Ltd., which is a bismaleimide resin, and the binding yarn 15, KEVLER49 (registered trademark) of Dupont, which is an aramid fiber.
[0033]
The size of the prototype composite material panel 10 is 460 mm in height, 350 mm in width, and 23.6 mm in height, and the size of the foam material 11 is about 444 mm in length, about 334 mm in width, and about 22 mm in height. A resin flow passage hole 18 having a diameter of about 2 mm is provided substantially at the center of the foam material 11. The binding yarn 15 binds the first fabric 13 and the second fabric 14 at about 3 mm and about 8 mm outside the foam material 11.
[0034]
The conditions of the primary curing were as follows: temperature 191 ° C., pressure 0.25 MPa, holding time 6 hours, and secondary curing conditions: temperature 227 ° C., pressure atmospheric pressure, holding time 6 hours. It is.
[0035]
The manufactured composite material panel 10 was evaluated for flat wise tension strength (tensile strength) in a flat wise tension strength test shown in FIG. 4A, and a bending strength shown in FIG. 4B. In the test, the shear strength was evaluated, and in the end bending strength test shown in FIG. 4C, the interlayer strength between the first fabric 13 and the second fabric 14 substantially outside the cut-off portion 17 was evaluated. Was done.
[0036]
As a result of the evaluation, the prototype showed that the flat wise tension strength was 2.5 MPa and the strength was sufficiently high, the shear strength was 1.9 MPa, the strength was sufficiently high, and the interlaminar strength of the cutout 17 woven fabric was sufficiently high. Obtained.
[0037]
According to the above configuration, since the rigid plastic closed cell foam in which the resin 12 is not impregnated therein is used for the foam material 11, the first fabric 13 and the second fabric 14 can be formed with a small amount of the resin 12. Can be sufficiently impregnated and cured, and the weight of the composite panel 10 can be reduced and the strength can be increased.
[0038]
In addition, since the rigid plastic closed cell foam is used for the foam material 11, an increase in the weight of the foam material 11 due to impregnation of the resin 12 into the foam material 11 can be prevented. And the strength can be increased.
[0039]
Even if the size of the foam material 11 increases and the resin 12 wraps around from the periphery of the foam material 11 and is not sufficiently impregnated into the second fabric 14, the resin 12 remains in the resin flow path substantially in the center of the foam material 11. Since the first fabric 13 can be sufficiently impregnated through the holes 18, the strength and the size of the composite panel 10 can be increased.
[0040]
Since the first fabric 13 and the second fabric 14 are tightly bound by the binding thread 15 almost outside the cutout portion 17, the first fabric 13 and the second fabric 14 almost outside the cutout portion 17 are provided. Even if a force in the shearing direction or the pulling direction acts between the layers, the strength of the composite material panel 10 can be increased because the binding yarn 15 can receive the force.
[0041]
Even if a crack occurs between the layers of the first fabric 13 and the second fabric 14 substantially outside the cutout portion 17, the first fabric 13 and the second fabric 13 are substantially formed outside the cutout portion 17. Since the crack 14 can be stopped by binding with the binding thread 15, the strength of the composite panel 10 can be increased.
[0042]
In the above embodiment, the method of manufacturing a composite material panel and the composite material panel have been described as being applied to an aircraft. However, the method of manufacturing a composite material panel and the method of manufacturing a composite material panel have been applied to an aircraft. The present invention is not limited to the above, and can be adapted to various usages such as a hood of a car, a roof of a gymnasium, and the like.
[0043]
In the above-described embodiment, the binding means is adapted to the binding thread. However, the present invention is not limited to the binding thread and can be applied to various other binding means such as a stapler.
[0044]
【The invention's effect】
As described above, according to the invention of claim 1, since the impregnation of the resin into the molding material is prevented, the one woven fabric and the other woven fabric can be formed with a small amount of the resin. This is effective in that it can be sufficiently impregnated and cured, and a lightweight, high-strength composite material panel can be manufactured.
[0045]
In addition, since the inside of the molding material is prevented from being impregnated with the resin and an increase in the weight of the molding material can be prevented, a light and high-strength composite material panel can be produced.
[0046]
Furthermore, since the one fabric and the other fabric are impregnated and cured with the resin at the same time, there is no need to process an uncured prepreg, and the work can be facilitated, and the composite material panel can be easily manufactured. This has the effect that it can be manufactured.
[0047]
According to the invention according to claim 2, even if the size of the molding material is increased and the resin is not sufficiently impregnated in the one woven fabric from the peripheral portion of the molding material, Since one of the fabrics or the other fabric can be sufficiently impregnated through the resin passage means, a large-sized composite panel can be manufactured.
[0048]
According to the invention according to claim 3, in order to bind the one woven fabric and the other woven fabric at the peripheral portion, a shear direction and a tensile force are applied between the layers of the one woven fabric and the other woven fabric. Since the force in the direction can be received by being restrained, the composite panel having high strength can be manufactured.
[0049]
In addition, even if a crack occurs between the layers of the one fabric and the other fabric, since the one fabric and the other fabric are tightly bound, the growth of the crack can be stopped, This produces an effect that a composite panel having high strength can be manufactured.
[0050]
According to the invention according to claim 4, since the impregnation of the resin into the molding material is prevented, the one fabric and the other fabric are sufficiently impregnated with a small amount of the resin and cured. Therefore, there is an effect that the weight of the composite material panel can be reduced and the strength can be increased.
[0051]
Further, since the resin is prevented from impregnating the inside of the molding material and the weight of the molding material can be prevented from increasing, the weight of the composite material panel can be reduced and the strength can be increased. It works.
[0052]
According to the invention according to claim 5, the size of the molding material is increased, and the resin is not sufficiently impregnated into the one woven fabric or the other woven fabric from the periphery of the molding material. In addition, the resin can be sufficiently impregnated into the one fabric or the other fabric through the resin passage means, so that the size of the composite panel can be increased.
[0053]
According to the invention according to claim 6, since the binding means for binding the one woven fabric and the other woven fabric is provided, a shear direction is provided between the layers of the one woven fabric and the other woven fabric. The force in the pulling direction can be received by the binding means, so that the strength of the composite panel can be increased.
[0054]
Further, even if a crack occurs between the layers of the one woven fabric and the other woven fabric, the growth of the crack can be stopped by tying the one woven fabric and the other woven fabric with the binding means. Therefore, there is an effect that the strength of the composite material panel can be increased.
[Brief description of the drawings]
FIG. 1 is a perspective view showing an embodiment of a composite panel according to the present invention.
FIG. 2 is a cross-sectional view showing one embodiment of a composite panel according to the present invention.
FIG. 3 is a cross-sectional view showing one embodiment of a method for manufacturing a composite panel according to the present invention.
FIG. 4 is a perspective view showing an example of a method for evaluating a prototype test piece of a composite panel according to the present invention.
FIG. 5 is a perspective view showing an example of a conventional composite panel.
FIG. 6 is a cross-sectional view illustrating an example of a conventional method for manufacturing a composite material panel.
[Explanation of symbols]
10 Composite panel 11 Foam (molded material)
12 Resin 13 First fabric (one fabric)
14 Second fabric (other fabric)
15 Tightening thread (Tightening means)
18 Resin channel hole (resin passage means)
19 bags (bags)

Claims (6)

一方の織物と他方の織物との間に成形材を介在させ、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とを接合させ、
前記一方の織物と前記他方の織物とを、樹脂で硬化させる複合材パネルの製造方法において、
前記成形材として、内部に独立した空間を有するものを用い、
前記一方の織物または前記他方の織物の側面に樹脂を配置し、前記成形材と、前記一方の織物と、前記他方の織物と、前記樹脂とを袋体に入れ、
前記袋体内を負圧吸引して、高温高圧環境下で、前記樹脂を前記一方の織物および前記他方の織物に含浸させ、硬化させることを特徴とする複合材パネルの製造方法。A molding material is interposed between one fabric and the other fabric, and the one fabric and the other fabric are joined at a peripheral portion of the molding material,
In the method for producing a composite panel, wherein the one woven fabric and the other woven fabric are cured with a resin,
As the molding material, a material having an independent space inside is used,
Placing a resin on the side of the one woven fabric or the other woven fabric, placing the molding material, the one woven fabric, the other woven fabric, and the resin in a bag,
A method of manufacturing a composite material panel, comprising: suctioning the bag body under a negative pressure, impregnating the one fabric and the other fabric with the resin in a high-temperature and high-pressure environment, and curing the resin. 請求項１記載の複合材パネルの製造方法において、
前記成形材に、予め、前記一方の織物側と前記他方の織物側とに開口部を持つ、樹脂通過手段を設けておき、
前記樹脂を、前記樹脂通過手段を通って前記一方の織物または前記他方の織物に含浸させることを特徴とする複合材パネルの製造方法。The method for manufacturing a composite panel according to claim 1,
The molding material has, in advance, an opening on the one fabric side and the other fabric side, a resin passing means is provided,
A method of manufacturing a composite panel, comprising: impregnating the one fabric or the other fabric with the resin through the resin passage means. 一方の織物と他方の織物との間に成形材を介在させ、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とを接合させ、
前記一方の織物と前記他方の織物とを、樹脂で硬化させる複合材パネルの製造方法において、
前記一方の織物と前記他方の織物とを、前記周縁部にて、緊縛することを特徴とする複合材パネルの製造方法。A molding material is interposed between one fabric and the other fabric, and the one fabric and the other fabric are joined at a peripheral portion of the molding material,
In the method for producing a composite panel, wherein the one woven fabric and the other woven fabric are cured with a resin,
A method of manufacturing a composite panel, wherein the one woven fabric and the other woven fabric are tied together at the peripheral portion. 一方の織物と他方の織物との間に成形材が介在され、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とが接合され、
前記一方の織物と前記他方の織物とは、樹脂で硬化される複合材パネルにおいて、
前記成形材は、内部に独立した空間を有し、
前記一方の織物と前記成形材と前記他方の織物とが密着されることを特徴とする複合材パネル。A molding material is interposed between one textile and the other textile, and at one edge of the molding, the one textile and the other textile are joined,
The one woven fabric and the other woven fabric are in a composite panel cured with a resin,
The molding material has an independent space inside,
A composite panel, wherein the one woven fabric, the molding material, and the other woven fabric are adhered to each other. 請求項４記載の複合材パネルにおいて、
前記成形材には、前記一方の織物側と前記他方の織物側とに開口部を持つ、樹脂通過手段が設けられていることを特徴とする複合材パネル。The composite panel according to claim 4,
A composite panel, wherein the molding material is provided with resin passage means having openings on the one textile side and the other textile side. 一方の織物と他方の織物との間に成形材を介在させ、前記成形材の周縁部にて、前記一方の織物と前記他方の織物とを接合させ、
前記一方の織物と前記他方の織物とを、樹脂で硬化される複合材パネルにおいて、
前記一方の織物と前記他方の織物とは、前記周縁部にて、緊縛手段を用いて緊縛されることを特徴とする複合材パネル。A molding material is interposed between one fabric and the other fabric, and the one fabric and the other fabric are joined at a peripheral portion of the molding material,
The one fabric and the other fabric, in a composite panel cured with resin,
The composite material panel according to claim 1, wherein the one woven fabric and the other woven fabric are tied by a tying means at the peripheral portion.
JP2002172914A 2002-06-13 2002-06-13 Method for manufacturing composite material panel and composite material panel Withdrawn JP2004017355A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2002172914A JP2004017355A (en) 2002-06-13 2002-06-13 Method for manufacturing composite material panel and composite material panel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2002172914A JP2004017355A (en) 2002-06-13 2002-06-13 Method for manufacturing composite material panel and composite material panel

Publications (1)

Publication Number Publication Date
JP2004017355A true JP2004017355A (en) 2004-01-22

Family

ID=31172350

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2002172914A Withdrawn JP2004017355A (en) 2002-06-13 2002-06-13 Method for manufacturing composite material panel and composite material panel

Country Status (1)

Country Link
JP (1) JP2004017355A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008080748A (en) * 2006-09-28 2008-04-10 Mitsubishi Rayon Co Ltd Laminate and bonnet for automobile using it
KR20160084684A (en) * 2015-01-06 2016-07-14 에스케이케미칼주식회사 Composite material panel for ship and menufacturing method thereof
JP2017520440A (en) * 2014-06-04 2017-07-27 ブライト ライト ストラクチャーズ エルエルシー Reinforced composite structure
JP2019209520A (en) * 2018-05-31 2019-12-12 川崎重工業株式会社 Method of manufacturing composite material structure and manufacturing fixture for composite material structure
JP2019217651A (en) * 2018-06-18 2019-12-26 日産自動車株式会社 Method for forming composite material structure
JP2020525317A (en) * 2017-07-06 2020-08-27 ブリュックナー・マシーネンバウ・ゲーエムベーハー・ウント・コー・カーゲー In particular, a sliding piece for a stretching device and/or a transport chain and related stretching device or transport chain
US10967583B2 (en) 2015-04-03 2021-04-06 Bright Lite Structures Llc Apparatus for controllably cutting fibers and related methods

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008080748A (en) * 2006-09-28 2008-04-10 Mitsubishi Rayon Co Ltd Laminate and bonnet for automobile using it
US10786977B2 (en) 2014-06-04 2020-09-29 Bright Lite Structures Llc Composite sandwich having a high bending stiffness
JP2017520440A (en) * 2014-06-04 2017-07-27 ブライト ライト ストラクチャーズ エルエルシー Reinforced composite structure
US10399307B2 (en) 2014-06-04 2019-09-03 Bright Lite Structures Llc Reinforced composite structure
US10406789B2 (en) 2014-06-04 2019-09-10 Bright Lite Structures Llc Multicomponent polymer resin, methods for applying the same, and composite laminate structure including the same
US10780677B2 (en) 2014-06-04 2020-09-22 Bright Lite Structures Llc Composite structure exhibiting energy absorption and/or including a defect free surface
US11241867B2 (en) 2014-06-04 2022-02-08 Bright Lite Structures Llc Multicomponent polymer resin, methods for applying the same, and composite laminate structure including the same
KR20160084684A (en) * 2015-01-06 2016-07-14 에스케이케미칼주식회사 Composite material panel for ship and menufacturing method thereof
KR102213059B1 (en) * 2015-01-06 2021-02-05 에스케이케미칼 주식회사 Composite material panel for ship and menufacturing method thereof
US10967583B2 (en) 2015-04-03 2021-04-06 Bright Lite Structures Llc Apparatus for controllably cutting fibers and related methods
JP2020525317A (en) * 2017-07-06 2020-08-27 ブリュックナー・マシーネンバウ・ゲーエムベーハー・ウント・コー・カーゲー In particular, a sliding piece for a stretching device and/or a transport chain and related stretching device or transport chain
JP2019209520A (en) * 2018-05-31 2019-12-12 川崎重工業株式会社 Method of manufacturing composite material structure and manufacturing fixture for composite material structure
JP2019217651A (en) * 2018-06-18 2019-12-26 日産自動車株式会社 Method for forming composite material structure

Similar Documents

Publication Publication Date Title
US8052831B2 (en) Low temperature, vacuum cure fabrication process for large, honeycomb core stiffened composite structures
US8312827B1 (en) Inter/pre-cured layer/pre-cured embroidered composite laminate and method of producing same
KR101675167B1 (en) Reinforced stiffeners and method for making the same
JP4856327B2 (en) Method for manufacturing composite panel
JP4206454B2 (en) Multi-axis reinforced laminated molded product and manufacturing method thereof
KR101260088B1 (en) Reinforcing woven fabric and process for producing the same
JP5311444B2 (en) Manufacturing method of resin prepreg, fiber sheet for resin prepreg, resin prepreg and composite material thereof
KR100759595B1 (en) Manufacturing method of carbon-glass fiber hybrid composites for wind turbine blade
US20080011756A1 (en) Liquid tight sealing of heat-insulating walls of a liquefied natural gas carrier
US20120263818A1 (en) Device for tensioning a preform
JP5029601B2 (en) Laminate manufacturing apparatus and method
JPH11107105A (en) Carbon fiber woven fabric and fiber-reinforced plastic and molding of fiber-reinforced plastic
WO2014030632A1 (en) Three-dimensional fiber-reinforced composite and method for producing three-dimensional fiber-reinforced composite
US20200070429A1 (en) Bond construction and bonding method of frp material to structure
JP2012153068A (en) Sandwich panel having insert structure, and method for manufacturing the same
JP2008162282A (en) Method of manufacturing composite structure equipped with flange having tethering type corner part
JP2004017355A (en) Method for manufacturing composite material panel and composite material panel
JP2008162281A (en) Tethering type corner part and flange, and article equipped with them
JP2009179065A (en) Method of manufacturing frp structure
JP2006123404A (en) Shaping method of reinforced fiber substrate for frp shaping
JPH11107107A (en) Carbon fiber woven fabric and fiber-reinforced plastic and molding of fiber-reinforced plastic
JP2018154675A (en) Manufacturing method of reinforced fiber substrate, manufacturing method of reinforced fiber preform and manufacturing method of fiber reinforced composite material molded body
JP4338550B2 (en) Method for manufacturing FRP structure
JP2000238139A (en) Manufacture of frp structure
JP2004058609A (en) Method for manufacturing laminated sheet

Legal Events

Date Code Title Description
A300 Withdrawal of application because of no request for examination

Free format text: JAPANESE INTERMEDIATE CODE: A300

Effective date: 20050906