JP6401859B2 - 複合材構造体及び複合材構造体の製造方法 - Google Patents
複合材構造体及び複合材構造体の製造方法 Download PDFInfo
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Description
また、本発明の実施形態に係る複合材構造体は、波型構造のストリンガと前記ストリンガと一体化されたパネルとを有する。ストリンガは、複合材で構成され、横断面がハット型の複数の部分を有する。パネルは、複合材で構成される。前記ストリンガは、前記ストリンガの板厚方向及び前記ストリンガの板厚方向に垂直な方向を含む複数の方向を長さ方向として編み込まれた繊維で強化された複合材で構成される。
(複合材構造体の構造)
図1は本発明の第1の実施形態に係る複合材構造体の構造を示す斜視図であり、図2は図1の位置A−Aにおける複合材構造体の部分断面図である。
次に複合材構造体6の製造方法について説明する。
以上のような複合材構造体6は、コルゲートストリンガ7とパネルとをVaRTM法でコキュア及び一体成形することによって製作したものである。また、樹脂の含浸前におけるコルゲートストリンガ7用の織物21及び硬化前におけるコルゲートストリンガ7に真空圧を負荷する際に、形状を保持できるように発泡コア材8を充填するようにしたものである。
図5は本発明の第2の実施形態に係る複合材構造体の構造を示す縦断面図である。
図5には、複合材構造体6Aを航空機の燃料タンクとして使用できるようにコルゲートストリンガ7の両端を閉塞する例を示したが、発泡コア材8を充填しない構成としてもよい。但し、コルゲートストリンガ7の成形時において発泡コア材8を充填せずに形状を維持することが必要となる。そこで、発泡コア材8に代えて、複合材の硬化後において取外し可能な治具を設置するようにしてもよい。複合材の硬化後において取外し可能な治具の例としては、水溶性のマンドレルやブラダーバッグ等が挙げられる。
以上、特定の実施形態について記載したが、記載された実施形態は一例に過ぎず、発明の範囲を限定するものではない。ここに記載された新規な方法及び装置は、様々な他の様式で具現化することができる。また、ここに記載された方法及び装置の様式において、発明の要旨から逸脱しない範囲で、種々の省略、置換及び変更を行うことができる。添付された請求の範囲及びその均等物は、発明の範囲及び要旨に包含されているものとして、そのような種々の様式及び変形例を含んでいる。
Claims (10)
- 複合材で構成され、横断面がハット型の複数の部分を有する波型構造のストリンガと、
複合材で構成され、前記ストリンガと一体化されたパネルと、
を有し、
前記横断面がハット型の複数の部分の各内側に発泡コア材を充填した複合材構造体。 - 複合材で構成され、横断面がハット型の複数の部分を有する波型構造のストリンガと、
複合材で構成され、前記ストリンガと一体化されたパネルと、
を有し、
前記ストリンガは、前記ストリンガの板厚方向及び前記ストリンガの板厚方向に垂直な方向を含む複数の方向を長さ方向として編み込まれた繊維で強化された複合材で構成される複合材構造体。 - 前記横断面がハット型の複数の部分の各内側に発泡コア材を充填した請求項2記載の複合材構造体。
- 前記ストリンガが、ファスナを使用せずに前記パネルと一体化された請求項1乃至3のいずれか1項に記載の複合材構造体。
- 前記横断面がハット型の複数の部分の両端を閉塞した請求項1又は3記載の複合材構造体。
- 真空圧で繊維に樹脂を含浸させることが可能な脱オートクレーブ成形用のプリプレグの積層体であって硬化前のパネルに対応するプリプレグの積層体の上に、横断面がハット型の複数の部分を有する波型構造のストリンガに対応する構造とした織物をセットするステップと、
前記織物がセットされた前記プリプレグの積層体をバギングフィルムで覆い、前記バギングフィルムで覆われた空間を真空状態にすることによって前記織物に樹脂を含浸させ、かつ前記樹脂を含浸した前記織物がセットされた前記プリプレグの積層体を加熱硬化することによって前記パネルの上に前記ストリンガが取付けられた構造を有する複合材構造体を製作するステップと、
を有する複合材構造体の製造方法。 - 少なくとも前記バギングフィルムで覆われた前記空間を真空状態とする前に、前記横断面がハット型の複数の部分の各内側に発泡コア材を充填するステップを更に有する請求項6記載の複合材構造体の製造方法。
- 前記バギングフィルムで覆われた前記空間を真空状態にして加熱することによって、前記織物と前記プリプレグの積層体との間における接合と、前記織物がセットされた前記プリプレグの積層体の硬化とを行う請求項6又は7記載の複合材構造体の製造方法。
- 前記発泡コア材が各内側に充填された前記横断面がハット型の前記複数の部分の両端を閉塞することによって航空機の燃料タンク用の部品として用いることが可能な複合材構造体を製作する請求項7記載の複合材構造体の製造方法。
- 少なくとも前記バギングフィルムで覆われた前記空間を真空状態とする前に、前記横断面がハット型の複数の部分の各内側に、前記織物がセットされた前記プリプレグの積層体の硬化後において取外し可能な治具であって前記複数の部分を前記各内側から支える治具を設置し、前記織物がセットされた前記プリプレグの積層体の硬化後において前記治具を取外すようにした請求項6記載の複合材構造体の製造方法。
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