JP5745081B2 - Smp装置を用いて一体型複合部品を形成する方法 - Google Patents
Smp装置を用いて一体型複合部品を形成する方法 Download PDFInfo
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- JP5745081B2 JP5745081B2 JP2013538732A JP2013538732A JP5745081B2 JP 5745081 B2 JP5745081 B2 JP 5745081B2 JP 2013538732 A JP2013538732 A JP 2013538732A JP 2013538732 A JP2013538732 A JP 2013538732A JP 5745081 B2 JP5745081 B2 JP 5745081B2
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Description
仮出願でない本特許出願は、「空気袋スタイルの再構成可能なツール類」の名称で2010年11月11日に出願され、出願番号が第61/412,635号であり、参照によってその全内容が本願に組み込まれた先願米国特許仮出願に対する優先権の利益を請求する。本願は、また、「空気袋スタイルの再構成可能なツール類」の名称で2010年12月21日に出願され、出願番号が第61/425,435号であり、参照によってその全内容が本書に組み込まれた先願米国特許仮出願に対する優先権の利益を請求する。更に、本願は、「SMP製のマンドレル/空気袋を用いた複合部品の製造方法及び製造システム」の名称で2011年5月16日に出願され、出願番号が第61/486,539号であり、参照によってその全内容が本書に組み込まれた先願米国特許仮出願に対する優先権の利益を請求する。
技術分野
本発明は、形状記憶高分子(SMP)で作製された再使用可能な装置を使用して、複合部品を製造するシステムと方法に関する。
航空機の製造において使用される複合部品は、フィラメントワインディング法、テーププレイスメント法、オーバーブレイド法、チョップファイバロービング法、コーティング法、ハンドレイアップ法、または他の複合加工技術と硬化プロセスのような様々な生産方式を使用して構築することができる。これらのプロセスのほとんどは、剛性のある硬化ツール/マンドレルを使用し、その上に複合材料が塗布され、その後剛性のある複合部品に硬化される。特に、結果として得られる複合部品が部品の容易な取り外しを妨げるトラップ形状を有する場合には、硬化された複合部品から剛性のある硬化ツールまたはマンドレルを取り外すのは、一般に困難で、コストがかかり、および/または時間がかかる。マンドレルを取り外す公知の1つの方法では、切断、溶解、ビードブラスト、または別の方法でマンドレルを複合部品の内部から取り外すことが可能なより小さな断片にすることによって、マンドレルを犠牲にするか、または破壊する必要がある。マンドレルを破壊することは、それがその後の部品のために再使用されるのを明らかに妨げ、かつ複合部品の内側表面に損傷を与えることがある。
本発明の実施形態は、形状記憶高分子(SMP)装置を使用して複合部品を製造する方法を示す。一例となる方法は、SMP装置の少なくとも一部に対して複合材料を塗布し、剛性のある状態から展性のある状態にSMP装置のモジュラスを変化させるきっかけを与え、複合材料の硬化温度に複合材料を加熱し、剛性のある型に対して複合材料を押し付けるために、硬化前および/または硬化中に、展性のある状態にあるSMP装置を複合材料に向かって動かす圧力差を発生させることを含んでも良い。モジュラスの変化は、SMP装置に対して温度変化、電流、水、および光の内の少なくとも1つを与えることがきっかけとなって起きるかもしれない。硬化が完了した時点で圧力が解放され、結果として得られる硬化された複合部品の内部からSMP装置が取り外されても良い。
本発明の実施形態は、添付された図面を参照して以下に詳細に記載されている。
本発明の以下の詳細な説明は、本発明を実施できる特定の実施形態を示す添付図面を参照する。実施形態には、当業者が本発明を実施できるようにするために十分詳細に、本発明の形態について記載されるように意図される。他の実施形態は、利用可能であり、本発明の範囲から逸脱せずに変更できる。従って、以下の詳細な説明は、限定する意味で受け取られるべきではない。本発明の範囲は、添付された特許請求の範囲によってのみ、その特許請求の範囲が権利化される対応語句の全ての範囲に沿って定義される。
本発明の1つの実施形態は、複合部品の作製方法である。本発明のこの実施形態は、図1〜2に最も良く示される形状記憶高分子(SMP)装置12、および/または、本書に後述され、図2に示された剛性のある外側ツール28を用いて実施されても良い。SMP装置12は、図1に示されるように複合材料14をその上に塗布するためのマンドレルまたは剛性のあるツール類、および図2に示されるように複合材料14の硬化中に複合材料14に対して外側への圧力を加えて固められた複合部品を得るための空気袋の両方として使用されても良い。
本発明の別の実施形態は、図13に示されるような一体化された内側補強材24を備えた航空機の胴体15の製造方法である。この実施形態の製造方法は、上述されているように、内側マンドレルツール16、エンドシール18、20、ダミー外板22、内側補強材24、補強用挿入部材26、および剛性のある外側ツール28と共に、図2〜12に最も良く示されるようなSMP装置12を用いて実施されても良い。
本発明の別の実施形態は、図16〜17に最も良く示されるように、上述されている内側補強材24、フレーム、および/またはストリンガのような補強材50の製造方法である。本発明のこの実施形態では、図16に示されるように、製造方法は、SMP装置12、剛性のある成型ツール52、および補強材を製造するための真空バッグのような原材料不浸透性シート54を使用して実施されても良い。
Claims (22)
- 一体化された補強材を備えた複合部品の製造方法であって、
形成されるべき前記複合部品の第1の表面の所望の配置構成に対応するように、SMP(形状記憶高分子)装置を整形し、または注入成形し、
前記補強材を内部に配置するように構成された1つ以上の凹部を含むように、前記SMP装置を整形し、または注入成形し、
前記凹部中に前記補強材を入れ、
前記SMP装置、および前記1つ以上の凹部内にある前記補強材の露出面上に複合材料を塗布し、
圧力と熱によって、前記SMP装置上の前記補強材を前記複合材料と相互硬化または相互結合して、前記複合部品を製造するものであり、
前記SMP装置は、前記複合材料との前記補強材の相互硬化または相互結合の間中ずっと、剛性のある状態に維持され、
前記SMP装置上に形成されるべき前記複合部品の前記第1の表面に対応するように、前記SMP装置を整形する工程は、
剛性と耐久性のある材料で作製された内側マンドレルツールの上方に前記SMP装置を配置し、
外側の型の中に前記SMP装置と前記内側マンドレルツールとを配置し、
前記内側マンドレルツールまたは前記外側の型に対して前記SMP装置の端部を密封し、
前記SMP装置が展性のある状態になり始める温度Tgよりも高温に前記SMP装置を加熱し、かつ前記外側の型に向かって前記SMP装置を膨張させ、
Tgよりも低温に前記SMP装置を冷却し、
前記外側の型から剛性のある状態の前記SMP装置を取り除くものであることを特徴とする方法。 - 前記補強材を前記複合材料と相互硬化または相互結合する工程は、
前記複合材料のまわりに原材料不浸透性シートを密封し、
前記原材料不浸透性シートの外側および/または内側に圧力差を誘導することによって、前記複合材料に対して前記原材料不浸透性シートを押し付け、
前記原材料不浸透性シートが前記複合材料に対して押し付けられている間、前記SMP装置が前記剛性のある状態で、前記複合材料を複合硬化温度に加熱する請求項1に記載の方法。 - 前記補強材は、フレーム、ストリンガ、複合コア、および前記複合材料の追加層の内の少なくとも1つを含む請求項1または2に記載の方法。
- 前記補強材は、前記凹部の中への配置に先立って、予め硬化される請求項1〜3のいずれか1項に記載の方法。
- 前記補強材は、前記凹部の中への配置に先立って硬化されない請求項1〜3のいずれか1項に記載の方法。
- さらに、前記SMP装置を前記剛性のある状態から展性のある状態にさせ、
前記複合部品内から前記SMP装置を取り除くものである請求項1〜5のいずれか1項に記載の方法。 - 前記SMP装置は、温度Tgよりも高温に加熱された時、前記展性のある状態にされるように構成され、前記複合材料の硬化温度は、Tg未満であり、前記SMP装置は、前記複合部品になるまで前記複合材料が硬化している間、剛性のある状態のままである請求項6記載の方法。
- さらに、前記SMP装置に前記複合材料を塗布するのに先立って、前記SMP装置と前記補強材との間の前記凹部に剛性のある補強用挿入部材を配置するものであり、
前記凹部は、前記剛性のある補強用挿入部材と前記補強材の両方がその中にあることを可能にするサイズと形状である請求項1〜7のいずれか1項に記載の方法。 - 一体化された補強材を備えた複合部品の製造方法であって、
SMP(形状記憶高分子)装置を展性のある状態にさせ、
形成されるべき前記複合部品の第1の表面の所望の配置構成に対応するように、前記展性のある状態で前記SMP装置を整形し、
前記補強材を内部に配置するように構成された1つ以上の凹部を含むように、前記SMP装置を整形し、
前記SMP装置を剛性のある状態にさせ、
前記凹部内に前記補強材を配置し、
前記SMP装置と、前記凹部内にある前記補強材の露出面との上に複合材料を塗布し、
前記複合部品を製造するために、圧力と熱によって、前記SMP装置上の前記複合材料と前記補強材を相互硬化または相互結合するものであり、
前記相互硬化または相互結合する工程は、
前記複合材料のまわりに原材料不浸透性シートを密封し、
前記原材料不浸透性シートの外側および/または内側に圧力差を誘導することによって、前記複合材料に対して前記原材料不浸透性シートを押し付け、
前記原材料不浸透性シートが前記複合材料に対して押し付けられている間、前記SMP装置が前記剛性のある状態で、前記複合材料を複合硬化温度に加熱し、
前記SMP装置上に形成されるべき前記複合部品の前記第1の表面に対応するように、前記SMP装置を整形する工程は、
剛性と耐久性のある材料で作製された内側マンドレルツールの上方に前記SMP装置を配置し、
外側の型の中に前記SMP装置と前記内側マンドレルツールとを配置し、
前記内側マンドレルツールまたは前記外側の型に対して前記SMP装置の端部を密封し、
前記SMP装置が展性のある状態になり始める温度Tgよりも高温に前記SMP装置を加熱し、かつ前記外側の型に向かって前記SMP装置を膨張させ、
Tgよりも低温に前記SMP装置を冷却し、
前記外側の型から剛性のある状態の前記SMP装置を取り除くものであることを特徴とする方法。 - 前記補強材は、内側補強材である請求項9に記載の方法。
- 前記補強材は、フレーム、ストリンガ、コア、および前記複合材料の追加層の内の少なくとも1つを含む請求項9または10に記載の方法。
- 前記複合部品は、航空機の一体構造の胴体、翼、ナセル、航空機のパネル、航空機のダクト、航空機の構造用支持材、硬質な積層板で作製された航空機の部品、一体的に補強された積層板、またはコアが補強されたサンドイッチ構造体、または航空機の部品用の内側補強材である請求項9〜11のいずれか1項に記載の方法。
- 前記補強材は、前記凹部の中への配置に先立って、予め硬化される請求項9〜12のいずれか1項に記載の方法。
- 前記補強材は、前記凹部の中への配置に先立って硬化されない請求項9〜12のいずれか1項に記載の方法。
- さらに、前記複合材料の硬化後に前記原材料不浸透性シートを取り除き、
前記SMP装置を前記剛性のある状態から前記展性のある状態にさせ、
前記SMP装置が前記展性のある状態にある間に、前記複合部品内から前記SMP装置を取り除くものである請求項9〜14のいずれか1項に記載の方法。 - 前記SMP装置は、温度Tgよりも高温に加熱された時、前記展性のある状態にされるように構成され、前記複合材料の硬化温度は、Tg未満であり、前記SMP装置は、前記複合部品になるまで前記複合材料が硬化している間、剛性のある状態のままである請求項9〜15のいずれか1項に記載の方法。
- さらに、前記複合材料のまわりに前記原材料不浸透性シートを密封する工程の前に、前記複合材料の輪郭と表面仕上げをコントロールするために、前記複合材料の上方に当て板シートを配置し、前記当て板シートのまわりに前記原材料不浸透性シートを密封する請求項9〜16のいずれか1項に記載の方法。
- さらに、前記SMP装置に前記複合材料を塗布するのに先立って、前記SMP装置と前記補強材との間の前記凹部内に剛性のある補強用挿入部材を配置するものであり、
前記凹部は、前記剛性のある補強用挿入部材と前記補強材の両方がその中にあることを可能にするようなサイズと形状である請求項9〜17のいずれか1項に記載の方法。 - 一体化された硬化特徴を備えた複合部品の製造方法であって、
SMP(形状記憶高分子)装置を展性のある状態にさせ、
形成されるべき前記複合部品の第1の表面の所望の配置構成に略対応するように、前記展性のある状態で前記SMP装置を整形し、
内側補強材を配置するように構成された1つ以上の凹部を含むように、前記SMP装置を整形し、
前記SMP装置を剛性のある状態にさせ、
前記凹部内に前記内側補強材を配置し、
前記SMP装置と、前記凹部内にある前記内側補強材の露出面との上に複合材料を塗布し、
前記複合部品を製造するために、圧力と熱によって、前記SMP装置上の前記複合材料と前記内側補強材を相互硬化または相互結合するものであり、
前記相互硬化または相互結合する工程は、
前記複合材料のまわりに原材料不浸透性シートを密封し、
前記原材料不浸透性シートの外側および/または内側に圧力差を誘導することによって、前記複合材料に対して前記原材料不浸透性シートを押し付け、
前記原材料不浸透性シートが前記複合材料に対して押し付けられている間、前記SMP装置が前記剛性のある状態で、前記複合材料を複合硬化温度に加熱し、
前記複合部品から前記原材料不浸透性シートを取り外し、
前記SMP装置を前記剛性のある状態から前記展性のある状態にさせ、
前記SMP装置が前記展性のある状態にある間に、前記複合部品内から前記SMP装置を取り除くものであり、
前記SMP装置上に形成されるべき前記複合部品の前記第1の表面に対応するように、前記SMP装置を整形する工程は、
剛性と耐久性のある材料で作製された内側マンドレルツールの上方に前記SMP装置を配置し、
外側の型の中に前記SMP装置と前記内側マンドレルツールとを配置し、
前記内側マンドレルツールまたは前記外側の型に対して前記SMP装置の端部を密封し、
前記SMP装置が展性のある状態になり始める温度Tgよりも高温に前記SMP装置を加熱し、かつ前記外側の型に向かって前記SMP装置を膨張させ、
Tgよりも低温に前記SMP装置を冷却し、
前記外側の型から剛性のある状態の前記SMP装置を取り除くものであることを特徴とする方法。 - 前記内側補強材は、フレーム、ストリンガ、コア、および前記複合材料の追加層の内の少なくとも1つを含む請求項19に記載の方法。
- 前記SMP装置は、温度Tgよりも高温に加熱された時、前記展性のある状態に変化し始めるように構成され、前記複合材料の硬化温度はTg未満であり、前記SMP装置は、前記複合部品になるまで前記複合材料が硬化している間、剛性のある状態のままである請求項19または20に記載の方法。
- さらに、前記SMP装置に前記複合材料を塗布するのに先立って、前記SMP装置と前記内側補強材との間の前記凹部に剛性のある補強用挿入部材を配置するものであり、
前記凹部は、前記剛性のある補強用挿入部材と前記内側補強材の両方がその中にあることを可能にするサイズと形状である請求項19〜21のいずれか1項に記載の方法。
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KR20130118888A (ko) | 2013-10-30 |
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EP2637838A2 (en) | 2013-09-18 |
EP2637838B1 (en) | 2015-08-26 |
CN103180123B (zh) | 2015-07-08 |
EP2637838A4 (en) | 2014-07-23 |
CN103180123A (zh) | 2013-06-26 |
US8945325B2 (en) | 2015-02-03 |
WO2012064443A2 (en) | 2012-05-18 |
ES2548827T3 (es) | 2015-10-21 |
BR112013005430B1 (pt) | 2020-10-27 |
BR112013005430A2 (pt) | 2016-06-07 |
US20120118487A1 (en) | 2012-05-17 |
US20120118486A1 (en) | 2012-05-17 |
WO2012064443A8 (en) | 2013-10-31 |
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