JP2009513438A - 航空機の外装保護のための環境的に安定したハイブリッド織物システム - Google Patents
航空機の外装保護のための環境的に安定したハイブリッド織物システム Download PDFInfo
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- JP2009513438A JP2009513438A JP2008537860A JP2008537860A JP2009513438A JP 2009513438 A JP2009513438 A JP 2009513438A JP 2008537860 A JP2008537860 A JP 2008537860A JP 2008537860 A JP2008537860 A JP 2008537860A JP 2009513438 A JP2009513438 A JP 2009513438A
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- Y10T442/3228—Materials differ
- Y10T442/3236—Including inorganic strand material
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/30—Woven fabric [i.e., woven strand or strip material]
- Y10T442/3382—Including a free metal or alloy constituent
- Y10T442/339—Metal or metal-coated strand
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
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- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/30—Woven fabric [i.e., woven strand or strip material]
- Y10T442/3472—Woven fabric including an additional woven fabric layer
- Y10T442/3528—Three or more fabric layers
- Y10T442/3569—Woven fabric layers impregnated with a thermosetting resin
- Y10T442/3585—Epoxy resin
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
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- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/30—Woven fabric [i.e., woven strand or strip material]
- Y10T442/3854—Woven fabric with a preformed polymeric film or sheet
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/30—Woven fabric [i.e., woven strand or strip material]
- Y10T442/3854—Woven fabric with a preformed polymeric film or sheet
- Y10T442/3919—Including particulate material other than fiber
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/60—Nonwoven fabric [i.e., nonwoven strand or fiber material]
- Y10T442/654—Including a free metal or alloy constituent
- Y10T442/655—Metal or metal-coated strand or fiber material
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/60—Nonwoven fabric [i.e., nonwoven strand or fiber material]
- Y10T442/659—Including an additional nonwoven fabric
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Laminated Bodies (AREA)
- Reinforced Plastic Materials (AREA)
- Chemical Or Physical Treatment Of Fibers (AREA)
- Treatments For Attaching Organic Compounds To Fibrous Goods (AREA)
- Woven Fabrics (AREA)
Abstract
Description
この発明は概して、航空機の外装のコーティング、層、表面および複合物に関する。より詳細には、この発明は、耐食性、耐雨食性、環境耐久性、構造性能、および避雷を含む電磁気保護を提供する航空機の外装保護のためのシステムに関する。
伝統的に、雷から保護する目的で、航空機の方法は電気エネルギを放散させるために胴体の金属製部分の至るところに抵抗が低い経路を含んでいた。媒体を設けて迅速にエネルギを放散させるために、複合部品の外面に沿って金属化繊維強化構造材料が使用されてきた。現在の避雷構造の中には、宇宙船およびいくつかの航空機での使用には適しているが頻繁に使用される民間航空機での使用には適していないものもある。これは、民間航空機が経験する圧力、湿度および温度環境が過酷でかつ絶えず変化するためであり、それらに関連付けられるコストおよびメンテナンス制約が異なるためである。
に、空隙などの製造上の欠陥がない状態で加工するのが困難である。アルミニウムフレーム溶射などの噴霧プロセスには、有資格者および典型的には航空会社の施設では利用可能でない機器が必要であるという追加の問題がある。
この発明の1つの実施例は、キャリアを有する装填したサーフェイサをハイブリッドプリプレグ基板に接合することによって航空機用の外面保護層を形成する方法を提供する。ハイブリッドプリプレグ基板は、ベース基板に接合された一体型の導電性構成要素を有する炭素織物を含む。装填したサーフェイサとハイブリッドプリプレグ基板との間に界面接着物質を含む、装填したサーフェイサおよびハイブリッドプリプレグ基板は、同時に硬化される。ベース基板と共に硬化されると、処理コストが低減する。
頻繁に使用される航空機の動作条件下で、エポキシ樹脂内に配置された、金属ワイヤを有する炭素繊維を含む避雷構造が基板の微小割れおよび仕上塗料の亀裂を経験する傾向があることが試験を通じて明らかになった。この発明はこれを克服し、この発明について以下で詳細に説明する。この発明は、主に航空機用の外装保護構造の形成に関して記載されるが、種々の用途に適用および適合され得る。この発明は、最小限の織りのテレグラフィングを示すまたは織りのテレグラフィングを示さない耐久性のある避雷構造の必要性が求められる場合、および特に重量または人件費が問題であるときに、航空での用途、電力での用途、船舶での用途、鉄道での用途、自動車での用途、医学での用途、ならびに商業上および居住用の用途において適用され得る。また、この発明の以下に記載する特徴の異なる組合せを有するさまざまな他の実施例、本明細書に記載する特徴以外の特徴を有するさまざまな他の実施例、またはそれらの特徴のうちの1つ以上を欠いてさえいるさまざまな他の実施例が企図される。したがって、この発明は種々の他の好適なモードで実行できることが理解される。
の形態をしていてもよい。構造支持層38の配置角度は変化し得る。たとえば、層40、41および42などの隣接する各層は、ベース基板30の構造性能および全体的な耐久性を上げるために、0°、+45°および90°などの異なる向きに単方向炭素テープを有していてもよい。ベース基板30は航空機部品の内部部分である。航空機部品は、積層物、サンドイッチ構造、またはそれらの組合せを有する構造であってもよく、種々の金属製または非金属製の材料で形成されてもよい。ベース基板30は、この発明の1つの想定される実施例では炭素/エポキシ複合胴体にあてがわれるが、当該技術分野において公知の種々の材料で形成された何か他の複合部品またはハイブリッド部品にあてがわれてもよい。
炭素/樹脂の割合は、構成要素のタイプおよびサービス環境に依存する。利用される樹脂の量は予め定められた範囲内に維持されて、微小割れを防ぎ、間隙率レベルを約2%未満に維持し、所望の構造的完全性をもたらす。使用される量は、超音波検査機器で測定され得る。微小割れおよび間隙率レベルは、範囲の下端を設定する。所望の構造的完全性は、範囲の上端を設定する。
、および全体的な耐久性などの環境保護の量は、避雷の量と引換えになる。一般に、装填したサーフェイサ52が厚くなればなるほど、避雷は小さくなるが、与えられる環境保護は大きくなり、逆の場合も同様である。上の例から引続いて、樹脂含有量が約40%であり、約196g/m2の炭素および約63g/m2の金属からなるドライプリフォームを有するハイブリッドプリプレグ基板と組合せるときにサーフェイス・マスター905を使用する0.0325lb/ft2のサーフェイサのバージョンは、典型的な航空機の構成について最初の落雷が原因の孔を防ぐことができる。典型的な航空機の構成とは、標準的な生産仕上塗料を有する構成であり、航空機の認可が連邦航空規則(Federal Aviation Regulation)(FAR)のパート25を満たすのに必要なレベルに試験される構成である。
度未満である。型がオートクレーブ内にある時間の長さは、利用される材料の硬化特性に依存する。硬化プロセス中、装填したサーフェイサは、完全にプリプレグ基板の上に残るのではなく、ハイブリッドプリプレグ基板に界面接着される。装填したサーフェイサおよびプリプレグ基板における物質または樹脂は混ざり合って硬化し、それによって、互いに界面接着する。
Claims (25)
- 航空機用の外面保護構造を形成する方法であって、
キャリアを備える装填したサーフェイサをハイブリッドプリプレグ基板に接合することと、
一体型の導電性構成要素を有する炭素織物を備える前記ハイブリッドプリプレグ基板をベース基板に接合することと、
前記装填したサーフェイサと前記プリプレグ基板との間に界面接着物質を備える、前記装填したサーフェイサおよび前記ハイブリッドプリプレグ基板を硬化させることとを備える、方法。 - 前記硬化させることは、前記プリプレグ基板上で前記装填したサーフェイサを均一に分散させて、前記炭素織物内の複数のワイヤのかなりの部分を覆う層を形成することを備える、請求項1に記載の方法。
- 前記硬化させることは、前記プリプレグ基板上で前記装填したサーフェイサを均一に分散させて、厚さが約0.004インチの層を形成することを備える、請求項1に記載の方法。
- 前記硬化させることは、約250〜350°Fの間の温度で前記装填したサーフェイサおよび前記プリプレグ基板を焼き固めることを備える、請求項1に記載の方法。
- 前記プリプレグ基板を接合することは、織り合わされたワイヤ織物を前記ベース基板に接合することを備える、請求項1に記載の方法。
- 前記ハイブリッドプリプレグ基板を接合することは、炭素織物に織り込まれかつエポキシを含浸させた炭素繊維を前記ベース基板に接合することを備える、請求項1に記載の方法。
- 前記プリプレグ基板を接合することは、金属スクリーンのない織り合わされたワイヤ織物を与えることを備える、請求項1に記載の方法。
- 航空機の外装のための保護織物システムであって、
ベース基板と、
一体型の導電性構成要素を有する炭素織物を備え、金属導電性範囲の範囲内の導電性を有し、前記ベース基板に結合されたハイブリッドプリプレグ基板と、
前記プリプレグ基板に界面接着された、キャリアを備える装填したサーフェイサとを備える、システム。 - 前記ベース基板は、複数の構造支持層を備える、請求項8に記載のシステム。
- 前記ハイブリッドプリプレグ基板は、炭素繊維、プリプレグ、および樹脂を有する乾式ハイブリッド織物から選択される少なくとも1つの材料を備える、請求項8に記載のシステム。
- 前記プリプレグ基板は、織り合わされたワイヤ織物である、請求項8に記載のシステム。
- 前記織り合わされたワイヤ織物は、エポキシを含浸させた平織りを備える、請求項11に記載のシステム。
- 前記織り合わされたワイヤ織物は、複数のトウとともに配置された複数のワイヤを備える、請求項11に記載のシステム。
- 前記複数のワイヤは、リン青銅、ニッケル被覆銅、銅、アルミニウムおよびステンレス鋼から選択される少なくとも1つの材料で形成される、請求項13に記載のシステム。
- 前記トウの各々の直径は約0.004インチである、請求項11に記載のシステム。
- 前記装填したサーフェイサは、無機充填剤を備える、請求項11に記載のシステム。
- 前記有機充填剤は、シリカ、アルミナおよびポリマーのうちの少なくとも1つから選択される材料である、請求項16に記載のシステム。
- 前記装填したサーフェイサは、硬化温度が約250〜350°Fの間であるエポキシを備える、請求項8に記載のシステム。
- 前記装填したサーフェイサは、硬化温度が約350°Fであるエポキシを有する、請求項8に記載のシステム。
- 前記装填したサーフェイサは、厚さが約0.004インチの層を形成する、請求項8に記載のシステム。
- 前記装填したサーフェイサは、前記一体型の導電性構成要素上の厚さが約0.004インチである状態で、関連付けられる重量が約0.02〜0.06lb/ft2の間である、請求項8に記載のシステム。
- 前記キャリアは、ポリエステル、炭素、金属化炭素およびガラスのうちの少なくとも1つから選択される材料で形成される、請求項8に記載のシステム。
- 航空機であって、
航空機部品と、
前記胴体に結合された金属製織物を備えるハイブリッドプリプレグ基板と、
キャリアを備え、前記プリプレグ基板に界面接着される装填したサーフェイサとを備える、航空機。 - 前記プリプレグ基板は、胴体に構造支持を与える、請求項23に記載の航空機。
- 前記プリプレグ基板は、織り合わされたワイヤ織物の形態をしており、前記装填したサーフェイサは、無機充填剤を備え、前記プリプレグ基板上に連続的な層を形成する、請求項23に記載の航空機。
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PCT/US2006/041388 WO2007120188A2 (en) | 2005-10-25 | 2006-10-24 | Environmentally stable hybrid fabric system for exterior protection of an aircraft |
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JP2012509461A (ja) * | 2008-11-19 | 2012-04-19 | ザ・ボーイング・カンパニー | 近赤外線及び中赤外線分光法による複合材料中の水分量の測定 |
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KR101745088B1 (ko) * | 2015-05-15 | 2017-06-08 | 현대자동차주식회사 | 전도성이 우수한 탄소섬유 복합재 및 이의 제조방법 |
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Publication number | Publication date |
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CN102658687B (zh) | 2015-08-19 |
WO2007120188A3 (en) | 2008-02-21 |
EP2610057A1 (en) | 2013-07-03 |
ES2573903T3 (es) | 2016-06-13 |
US20070093163A1 (en) | 2007-04-26 |
CN101282834B (zh) | 2012-07-04 |
US8276850B2 (en) | 2012-10-02 |
EP1940610B1 (en) | 2016-05-18 |
US8524620B2 (en) | 2013-09-03 |
CN102658687A (zh) | 2012-09-12 |
US7402269B2 (en) | 2008-07-22 |
EP1940610A2 (en) | 2008-07-09 |
US20090032643A1 (en) | 2009-02-05 |
CN101282834A (zh) | 2008-10-08 |
JP4964245B2 (ja) | 2012-06-27 |
US20090039199A1 (en) | 2009-02-12 |
WO2007120188A2 (en) | 2007-10-25 |
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