JP3632176B2 - Method and apparatus for manufacturing aircraft composite panel - Google Patents

Method and apparatus for manufacturing aircraft composite panel Download PDF

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Publication number
JP3632176B2
JP3632176B2 JP2002173242A JP2002173242A JP3632176B2 JP 3632176 B2 JP3632176 B2 JP 3632176B2 JP 2002173242 A JP2002173242 A JP 2002173242A JP 2002173242 A JP2002173242 A JP 2002173242A JP 3632176 B2 JP3632176 B2 JP 3632176B2
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Prior art keywords
prepreg
laminate
release film
prepreg laminate
laminated
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JP2004017370A (en
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俊一 佐名
晃 村井
舜一 板東
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Kawasaki Motors Ltd
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Kawasaki Jukogyo KK
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Priority to US10/458,380 priority patent/US6860957B2/en
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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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Abstract

<P>PROBLEM TO BE SOLVED: To provide a method for efficiently manufacturing a composite panel for an airplane by laminating a wide prepreg, a narrow prepreg or the like in individual areas and also cutting them in separate areas in order to realize the high speed lamination of the prepregs and performing the feed of the prepregs by hanging-up aerial feed, and an apparatus therefor. <P>SOLUTION: A release film is closely brought into contact with a planar table 4 and a planar laminate having a large area is formed by the four-axial control of the wide prepreg 5 of an unidirectional material and/or a cross material on the film. The narrow prepreg 13 is laminated on the film in the same way on another table 12 and the formation of a lattice-like laminate is performed parallelly and, next, the large area laminate and the lattice like laminate are floated along with the release film by blowing off air from the areas under the respective tables. Thereafter, the laminates are aerially fed to be placed on one cutting table 9 and cut into a required shape to form a skin part and a doubler part laminate successively. Both of them are hung up from the cutting table in a curtain state and aerially fed to be placed and laminated on the lamination fixture 22 of a single contour surface to form the composite panel. <P>COPYRIGHT: (C)2004,JPO

Description

【０００１】
【発明の属する技術分野】
本発明は、航空機の胴体や翼さらにはロケットの胴体やフェアリングなどのパネルとして用いるＣＦＲＰなどより成る複合材パネルの製造方法及びその装置に関するものである。
【０００２】
【従来の技術】
従来より航空機の軽量化のために胴体や翼を始めとして種々の部品の外壁面に、金属パネルに代ってＣＦＲＰなどより成る複合材パネルが用いられることが多くなってきた。この複合材パネルを製造するには、従来、上面をコンター面となした積層型に直接プリプレグを積層するプリプレグ自動積層機（通称：ＡＴＬ）が開発され、使用されてきた。
このプリプレグ自動積層機は、３または６インチ幅の一方向材プリプレグをＮＣ制御にて積層する機能を有するが、常に細幅単位でしか積層できないため、大面積の積層や厚板積層には時間がかかり、効率が悪かった。
【０００３】
また、近年開発されたファイバープレースメント装置（通称：ＦＰＭ）は、複雑なコンター面を有する積層型へのプリプレグの積層が可能で、３〜１０ｍｍの細幅プリプレグを何１０本も同時積層できることを特徴とするが、何分にもプリプレグ幅が細すぎるため、単位面積当りの積層時間は前記プリプレグ自動積層機よりもさらに多くかかり、非常に効率が悪かった。
【０００４】
そして上記いずれも積層型に直接プリプレグを積層する方法は、プリプレグ自動積層に積層型が拘束されるため、プリプレグの自動積層中は型上にて他の仕事ができず、生産レートの高いパネルの製造には向かなかった。
【０００５】
また、上記いずれも３次元コンター面を有する積層型へのプリプレグ積層を可能にするため、積層ヘッドに全ての機能を持たせた１０軸制御機能とプリプレグを切断できる機能を備えさせているため、積層ヘッドが非常に重く、装置全体が大がかりなものとなっていた。
【０００６】
さらに、プリプレグの切断機能は直線切断しかできないものであるため、細かな形状切断に対応できなかった。
【０００７】
さらにまた、複雑なコンター面を有する積層型へのプリプレグ積層を行うには、積層ヘッドを制御するために非常に高い演算能力が必要で、制御にも時間がかかることから、積層時間も長くなり、効率的なプリプレグ積層ができなかった。
【０００８】
【発明が解決しようとする課題】
そこで本発明は、従来のオールインワンタイプのプリプレグ自動積層機の機能を分解し、夫々個別機能として稼動させることで、プリプレグの高速積層を実現するために、幅広プリプレグの平面積層、細幅プリプレグの平面積層、さらには細幅プリプレグの点在平面積層を個別のエリアで行うようにし、これらを行って得たプリプレグ積層体の形状裁断を別のエリアで順次行うようにし、形状裁断した各プリプレグ積層体をさらに別のエリアで順次積層するようにし、各平面積層エリアから裁断エリアへのプリプレグ積層体の搬送及び裁断エリアから積層治具へのプリプレグ積層体の搬送は吊り上げ空中搬送することで、効率的なプリプレグ積層による航空機用複合材パネルの製造を行うことのできる方法及びその装置を提供しようとするものである。
【０００９】
【課題を解決するための手段】
上記課題を解決するための本発明の航空機用複合材パネルの製造方法の１つは、平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により平面積層し、大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することを並行して行い、次に大面積のプリプレグ積層体と格子状のプリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次スライド式に空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次スキン部プリプレグ積層体，ダブラー部プリプレグ積層体を形成し、次いでこれらスキン部プリプレグ積層体，ダブラー部プリプレグ積層体を順次裁断テーブルからカーテン状に吊り上げ空中搬送してシングルコンター面の積層治具上に載置し、積層して、複合材パネルとなすことを特徴とするものである。
【００１０】
この航空機用複合材パネルの製造方法において、シングルコンター面の積層治具上に載置するスキン部プリプレグ積層体は、裁断テーブルから吊り上げる際、離型フィルムを裁断テーブルに真空吸引したまま離型フィルムから引き剥がす方法とり、シングルコンター面の積層治具上に載置したスキン部プリプレグ積層体の上に積層するダブラー部プリプレグ積層体は、裁断テーブルから吊り上げ空中搬送して積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にしてスキン部プリプレグ積層体に積層し、その後離型フィルムを除去する方法をとることが必要である。
【００１１】
本発明の航空機用複合材パネルの製造方法の他の１つは、平面積層テーブル上に離型フィルムを真空引きにより密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により隙間をあけて平面積層し、断続大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空引きにより密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することを並行して行い、次に断続大面積のプリプレグ積層体と格子状プリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次スライド式に空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次断続スキン部プリプレグ積層体，ダブラー部プリプレグ積層体を形成し、次いで断続スキン部プリプレグ積層体を裁断テーブルからカーテン状に吊り上げ空中搬送してダブルコンター面の積層治具上に載置し、断続スキン部プリプレグ積層体をダブルコンター面になじませた上、断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層し、次にこの隙間無しのスキン部プリプレグ積層体上にダブラー部プリプレグ積層体を裁断テーブルからカーテン状に吊り上げ空中搬送して載置し、積層して、複合材パネルとなすことを特徴とするものである。
【００１２】
この航空機用複合材パネルの製造方法において、ダブルコンター面の積層治具上に載置する断続スキン部プリプレグ積層体、及びこの断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層後この隙間無しのスキン部プリプレグ積層体上に積層するダブラー部プリプレグ積層体は、夫々１つの裁断テーブルから吊り上げ空中搬送して積層治具上に載置積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にして各々載置，積層し、その後離型フィルムを除去する方法をとることが必要である。
【００１３】
本発明の航空機用複合材パネルの製造方法の別の１つは、平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により平面積層し、大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することと、さらに別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材及びクロス材細幅プリプレグを複数の所要位置に手積み又は４軸制御により平面積層し、点在プリプレグ積層体を形成することを並行して行い、次に大面積のプリプレグ積層体と格子状のプリプレグ積層体と点在プリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次スライド式に空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次スキン部プリプレグ積層体，ダブラー部プリプレグ積層体，局所補強プリプレグ積層体を形成し、次いでこれらを順次裁断テーブルからカーテン状に吊り上げて空中搬送してシングルコンター面の積層治具上に載置し、積層して、複合材パネルとなすことを特徴とするものである。
【００１４】
この航空機用複合材パネルの製造方法において、シングルコンター面の積層治具上に載置するスキン部プリプレグ積層体は、裁断テーブルから吊り上げる際、離型フィルムを裁断テーブルに真空吸引したまま離型フィルムから引き剥がす方法をとり、積層治具上のスキン部プリプレグ積層体上に積層するダブラー部プリプレグ積層体及びそのダブラー部積層体上に積層する局所補強プリプレグ積層体は、裁断テーブルから吊り上げ空中搬送して積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にして各々スキン部プリプレグ積層体，ダブラー部プリプレグ積層体に積層の都度、離型フィルムを除去する方法をとることが必要である。
【００１５】
本発明の航空機用複合材パネルの製造方法のさらに別の１つは、平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により隙間をあけて平面積層し、断続大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空引きにより密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することと、さらに別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の細幅プリプレグを複数の所要位置に手積み又は４軸制御により平面積層し、点在プリプレグ積層体を形成することとを並行して行い、次に断続大面積のプリプレグ積層体と格子状のプリプレグ積層体と点在プリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次断続スキン部プリプレグ積層体，ダブラー部プリプレグ積層体，局所補強プリプレグ積層体を形成し、次いで断続スキン部プリプレグ積層体を裁断テーブルから吊り上げ空中搬送してダブルコンター面の積層治具上に載置し、断続スキン部プリプレグ積層体をダブルコンター面になじませた上、断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層し、次にこの隙間無しのスキン部プリプレグ積層体にダブラー部プリプレグ積層体，局所補強プリプレグ積層体を順次裁断テーブルからカーテン状に吊り上げ空中搬送して載置し、積層して、複合材パネルとなすことを特徴とするものである。
【００１６】
この航空機用複合材パネルの製造方法において、ダブルコンター面の積層治具上に載置する断続スキン部プリプレグ積層体、この断続スキン部プリプレグ積層体の隙間に幅広のプリプレグを追加積層後この隙間無しのスキン部プリプレグ積層体上に積層するダブラー部プリプレグ積層体及びこのダブラー部プリプレグ積層体上に積層する局所補強プリプレグ積層体は、夫々１つの裁断テーブルから吊り上げ空中搬送して積層治具上に載置積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にして各々載置，積層し、その後離型フィルムを除去する方法をとることが必要である。
【００１７】
上記の各製造方法を実施するための本発明の航空機用複合材パネルの製造装置は、上面に真空吸引，空気吹き出しの***を多数設けた平面積層テーブルの上方に、一方向材又は／及びクロス材の幅広プリプレグを平面積層する４軸制御の積層ヘッドを有する自動積層機を備えた幅広プリプレグ積層装置と、同じく上面に真空吸引，空気吹き出しの***を多数設けた別の平面積層テーブルの上方に、一方向材又は／及びクロス材の細幅プリプレグを格子状に平面積層する４軸制御の積層ヘッドを有する自動積層機を備えた細幅プリプレグ積層装置と、同じく上面に真空吸引，空気吹き出しの***を多数設けたさらに別の平面積層テーブルの上方に細幅プリプレグ手積み位置検出用テンプレートを備えるか、または細幅プリプレグを平面積層する４軸制御の積層ヘッドを有する自動積層機を備えたプリプレグ点在積層装置と、前記幅広プリプレグ積層装置と細幅プリプレグ積層装置とプリプレグ点在積層装置とで三方より囲まれる位置に設けられ上面に真空吸引，空気吹き出しの***を多数設けた裁断テーブルの上方に自動裁断機を備えたプリプレグ積層体裁断装置と、このプリプレグ積層体裁断装置を挾むようにプリプレグ点在積層装置と対向する位置に設けられシングルコンター面又はダブルコンター面を有するプリプレグ積層体積層治具と、前記幅広プリプレグ積層装置，細幅プリプレグ積層装置，プリプレグ点在積層装置とプリプレグ積層体裁断装置とを往来してプリプレグ積層体をスライド式に空中搬送するスライド式搬送装置と、前記プリプレグ積層体裁断装置とプリプレグ積層体積層治具とを往来してプリプレグ積層体をカーテン状に吊り上げて空中搬送するハンガー付きクレーンとより成るものである。
【００１８】
この航空機用複合材パネルの製造装置において、細幅プリプレグ積層装置には、その自動積層機の積層ヘッドに着脱させる各種幅寸法の細幅プリプレグを繰り出し可能に収容した複数のプリプレグカセットを備えていることが好ましい。
【００１９】
【発明の実施の形態】
本発明の航空機用複合材パネルの製造方法及びその装置の実施形態を図によって説明する。先ず、航空機用複合材パネルの製造方法を行うための装置を図１〜図３によって説明すると、１は幅広プリプレグ積層装置で、この幅広プリプレグ積層装置１は、上面に真空吸引，空気吹き出しの***２を多数開口し下部に空気給排空間３を設けた幅１０ｍ，長さ１５ｍの平面積層テーブル４と、その上方に設けられ幅寸法が１ｍを超える一方向材又は／及びクロス材の幅広プリプレグ５を平面積層する４軸制御の積層ヘッド６を有する自動積層機７とより成るものである。８は前記幅広プリプレグ積層装置１に隣接して設けたプリプレグ積層体裁断装置で、このプリプレグ積層体裁断装置８は、上面に真空吸引，空気吹き出しの***２を多数設け下部に空気給排空間３を設けた幅１０ｍ，長さ１５ｍの裁断テーブル９と、その上方に設けた自動裁断機１０とより成るものである。１１は前記プリプレグ積層体裁断装置８に隣接して設けた細幅プリプレグ積層装置で、この細幅プリプレグ積層装置１１は、上面に真空吸引，空気吹き出しの***２を多数開口し下部に空気給排空間３を設けた幅１０ｍ，長さ１５ｍの平面積層テーブル１２と、その上方に設けられ幅寸法が１〜２０ｃｍの一方材又は／及びクロス材の細幅プリプレグテープ１３を格子状に平面積層する４軸制御の積層ヘッド１４を有する自動積層機１５とより成るものである。この細幅プリプレグ積層装置１１には各種幅寸法にスリットされた一方材やクロス材の細幅プリプレグテープ１３を収容した複数のプリプレグカセット１６が装備されていて、このプリプレグカセット１６は積層ヘッド１４に取替え装着できるようになっている。１７は前記幅広プリプレグ積層装置１と細幅プリプレグ積層装置１１の方向とは直角の方向でプリプレグ積層体裁断装置８に隣接して設けたプリプレグ点在積層装置で、このプリプレグ点在積層装置１７の一例は、上面に真空吸引，空気吹き出しの***２を多数設け下部に空気給排空間３を設けた幅１０ｍ，長さ１５ｍの平面積層テーブル１８と、その上方に設けた細幅プリプレグ手積み位置検出用テンプレート１９とより成るものである。プリプレグ点在積層装置１７の他の例は、図４に示すように平面積層テーブル１８の上方に、１０〜２０ｍｍの一方向材又はクロス材の細幅プリプレグを点在して平面積層する４軸制御の積層ヘッド２０を有する自動積層機２１を備えたものである。図１〜図３において、２２は前記プリプレグ積層体裁断装置８を挾んでプリプレグ点在積層装置１７と対向する位置に設けられたプリプレグ積層体積層治具で、このプリプレグ積層体積層治具２２は、上面が図３に示すようにシングルコンター面２３のものと図５に示すようにダブルコンター面２４のものとがある。図１〜図３において、２５は前記プリプレグ積層体裁断装置８とプリプレグ積層体積層治具２２とを往来して、プリプレグ積層体裁断装置８で裁断したプリプレグ積層体をカーテン状に吊り上げてプリプレグ積層体積層治具２２に空中搬送するハンガー２６付きクレーンである。２７，２７′は、幅広プリプレグ積層装置１、細幅プリプレグ積層装置１１からプリプレグ積層体裁断装置８にプリプレグ積層体を搬送するスライド式搬送装置である。このスライド式搬送装置２７，２７′は、図６、図７に示すように積層装置１、１１の平面積層テーブル４、１２の両側端のレール２８，２８′から裁断装置８の裁断テーブルの両側端のレール２９にかけて走行する走行装置３０，３０′に、平面積層テーブル４、１２上に配された離型フィルムＦの両側端を把持する開閉可能なチャック３１を備えたものである。
【００２０】
上記構成の航空機用複合材パネルの製造装置における細幅プリプレグ積層装置１１に装備される複数のプリプレグカセット１６は、例えば図８に示すようにケース３２内に繰り出しロール３３と巻き込みロール３４とを設け、繰り出しロール３３に例えば図９に示すように４５°方向の細幅プリプレグ３５と０°方向の細幅プリプレグ３６と組み合わせてばらけないようにした１〜２０ｃｍの細幅プリプレグテープ１３を巻き上げ紙３７と一緒に巻き込み、巻き上げ紙３７の一端を巻き込みロール３４に固定したものであって、このプリプレグカセット１６は図１〜図３に示される積層ヘッド１４に適宜交換して装着され、該積層ヘッド１４が４軸制御による移行時に繰り出しロール３３が回転されて細幅プリプレグテープ１３が繰り出されて積層されるようになっている。
【００２１】
次に上記のように構成された実施形態の製造装置による航空機用複合材パネルの製造方法の種々の実施形態について説明する。窓などの開口部を作らない胴体パネルに用いるシングルコンター形状の複合材パネルの製造方法の実施形態においては、製造装置のプリプレグ点在装置１７は使用せず、プリプレグ積層体積層治具２２は上面が図３に示すようにシングルコンター面２３のものが使用される。以下、本製造方法の工程について説明する。幅広プリプレグ積層装置１の平面積層テーブル４上に図２に示すように離型フィルムＦを載せ、上面に開口した***２から下部の空気給排空間３を通して真空吸引し、離型フィルムＦを平面積層テーブル４上に密着させた後、その離型フィルムＦ上で図３に示すように一方向材及びクロス材の幅寸法１ｍの幅広プリプレグ５を４軸制御の自動積層機７の積層ヘッド６により平面積層し、大面積のプリプレグ積層体Ｐ１ を形成する。これと並行して細幅プリプレグ積層装置１１の平面積層テーブル１２上に図２に示すように離型フィルムＦを載せ、上面に開口した***２から下部の空気給排空間３を通して真空吸引し、離型フィルムＦを平面積層テーブル１２上に密着させた後、その離型フィルムＦ上で例えば図３に示すように１〜２０ｃｍの各種幅寸法のスリットされた一方向材の細幅プリプレグテープ１３を４軸制御の自動積層機１５の積層ヘッド１４に装着したプリプレグカセット１６から繰り出し、縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体Ｐ２ を形成する。次に前記の大面積のプリプレグ積層体Ｐ１ を平面積層テーブル４の***２から空気を吹き出して離型フィルムＦごと浮上させた後、図６、図７に示すスライド式搬送装置２７の走行装置３０に備えられたチャック３１に離型フィルムＦの両側端を把持させ、走行装置３０をレール２８、２９を走行させて隣接のプリプレグ積層体裁断装置８にスライド式に空中搬送し、その裁断装置８の裁断テーブル９上にプリプレグ積層体Ｐ１ を降して載置し、離型フィルムＦからチャック３１を離した上、裁断テーブル９の上面に開口した***２から下部の空気給排空間３を通して真空吸引し、離型フィルムＦごと大面積のプリプレグ積層体Ｐ１ を裁断テーブル９上に密着させる。然る後、所要寸法，形状となるように自動裁断機１０により図１０に示すように裁断して、スキン部プリプレグ積層体Ｓを形成する。次いで、裁断テーブル９上の離型フィルムＦを真空吸引させたままスキン部プリプレグ積層体Ｓの一側端をクレーン２５のハンガー２６に把持させ離型フィルムＦから引き剥がして図１１に示すようにカーテン状に吊り上げる。そしてクレーン２５を直角方向に走行させて上面がシングルコンター面２３のプリプレグ積層体積層治具２２にスキン部プリプレグ積層体Ｓを空中搬送し、その積層治具２２のシングルコンター面２３上に図１２に示すように吊り降して載置する。次に前記の格子状のプリプレグ積層体Ｐ２ を平面積層テーブル１２の***２から空気を吹き出して離型フィルムＦごと浮上させた後、図６、図７に示すスライド式搬送装置２７′の走行装置３０′に備えられたチャック３１に離型フィルムＦの両側端を把持させ、走行装置３０′をレール２８′、２９を走行させて隣接のプリプレグ積層体裁断装置８にスライド式に空中搬送し、その裁断装置８の裁断テーブル９上にプリプレグ積層体Ｐ２ を降して載置し、離型フィルムＦからチャック３１を離した上、裁断テーブル９の上面に開口した***２から下部の空気給排空間３を通して真空吸引し、離型フィルムＦごと格子状のプリプレグ積層体Ｐ２ を裁断テーブル９上に密着させる。然る後、所要寸法，形状となるように自動裁断機１０により裁断して、図１３に示すように胴体パネルにおけるストリンガー等の取付部の補強となるダブラー部プリプレグ積層体Ｄを形成する。次いで、このダブラー部プリプレグ積層体Ｄを裁断テーブル９の***２から空気を吹き出して離型フィルムＦごと浮上させた後、図８と同様にクレーン２５のハンガー２６に離型フィルムＦの一側端を把持させて図１１と同様にカーテン状に吊り上げる。そしてクレーン２５を直角方向に走行させてダブラー部プリプレグ積層体Ｄをプリプレグ積層体積層治具２２に空中搬送し、その積層治具２２のシングルコンター面２３上に先に載置したスキン部プリプレグ積層体Ｓの上に離型フィルムＦを上にしてダブラー部プリプレグ積層体Ｄを吊り降して載置し、積層し、その後離型フィルムＦを引き剥して除去し、図１４に示すように胴体パネル用のシングルコンター形状の複合材パネルＰ１を作る。
【００２２】
翼パネルや胴体パネルに用いるダブルコンター形状の複合材パネルの製造方法の実施形態においては、製造装置のプリプレグ点在装置１７は使用せず、プリプレグ積層体積層治具２２は上面が図５に示すようにダブルコンター面２４のものが使用される。以下、本製造方法の工程について説明する。幅広プリプレグ積層装置１の平面積層テーブル４上に図２に示すように離型フィルムＦを載せ、上面に開口した***２から真空吸引し、離型フィルムＦを平面積層テーブル４上に密着させた後、その離型フィルムＦ上で図１５に示すように一方向材及びクロス材の幅寸法１ｍの幅広プリプレグ５を４軸制御の自動積層機７の積層ヘッド６により隙間をあけて平面積層し、断続大面積のプリプレグ積層体Ｐ１ ′を形成する。これと並行して細幅プリプレグ積層装置１１で前述の実施形態と同様に図１、図３に示すように格子状のプリプレグ積層体Ｐ２ を形成する。次に前記断続大面積のプリプレグ積層体Ｐ１ ′を平面積層テーブル４の***２から空気を吹き出して離型フィルムＦごと浮上させた後、図６、図７に示すスライド式搬送装置２７の走行装置３０に備えられたチャック３１に離型フィルムＦの両側端を把持させ、走行装置３０をレール２８、２９を走行させて隣接のプリプレグ積層体裁断装置８にスライド式に空中搬送し、その裁断装置８の裁断テーブル９に断続大面積のプリプレグ積層体Ｐ１ ′を降して載置し、離型フィルムＦからチャック３１を離した上、裁断テーブル９の上面に開口した***２から真空吸引し、離型フィルムＦごと断続大面積のプリプレグ積層体Ｐ１ ′を裁断テーブル９上に密着させる。然る後、所要寸法，形状となるように自動裁断機１０により図１６に示すように裁断して、断続スキン部プリプレグ積層体Ｓ′を形成する。次いで断続スキン部プリプレグ積層体Ｓ′を裁断テーブル９の***２から空気を吹き出して離型フィルムＦごと浮上させた後、クレーン２５のハンガー２６に離型フィルムＦの一側端を把持させて図１１と同様にカーテン状に吊り上げる。そしてクレーン２５を直角方向に走行させて上面がダブルコンター面２４のプリプレグ積層体積層治具２２に断続スキン部プリプレグ積層体Ｓ′を空中搬送し、その積層治具２２のダブルコンター面２４上に図１７に示すように吊り降し、離型フィルムＦを上にして載置する。次に離型フィルムＦを図１８に示すように引き剥して断続スキン部プリプレグ積層体Ｓ′をずらしながらダブルコンター面２４になじませた上、その断続スキン部プリプレグ積層体Ｓ′の隙間に図１９に示すように幅広プリプレグ５を手積みにより追加積層して、図２０に示すように隙間無しのスキン部プリプレグ積層体Ｓを形成する。この間に前記格子状のプリプレグ積層体Ｐ２ を前述の実施形態と同様の手順にて隣接のプリプレグ積層体裁断装置８にスライド式に空中搬送し、それの裁断テーブル９上に降して載置した上、所要寸法，形状となるように自動裁断機１０にて裁断して、図１３と同様に翼パネルや胴体パネルにおけるストリンガー等の取付部の補強構造となるダブラー部プリプレグ積層体Ｄを形成する。次いで、このダブラー部プリプレグ積層体Ｄを前述の実施形態と同様の手順にてプリプレグ積層体積層治具２２に空中搬送し、その積層治具２２のダブルコンター面２４上に先に載置して形成したスキン部プリプレグ積層体Ｓ上に離型フィルムＦを上にしてダブラー部プリプレグ積層体Ｄを吊り降して載置し、積層し、その後離型フィルムＦを引き剥して除去し、図２１に示すように翼パネルや胴体パネルに用いるダブルコンター形状の複合材パネルＰ２を作る。
【００２３】
窓などの開口部を作る胴体パネルに用いるシングルコンター形状の複合材パネルの製造方法の実施形態においては、製造装置のプリプレグ点在装置１７は図４に示す自動積層機２１を備えたものを使用し、プリプレグ積層体積層治具２２は上面がシングルコンター面２３のものが使用される。以下本製造方法の工程について説明する。幅広プリプレグ積層装置１及び細幅プリプレグ積層装置１１で、前述のシングルコンター形状の複合材パネルの製造方法と同様に大面積のプリプレグ積層体Ｐ１ 及び格子状のプリプレグ積層体Ｐ２ を並行して形成する。と同時にプリプレグ点在装置１７で点在プリプレグ積層体Ｐ３ を形成する。即ち、プリプレグ点在装置１７の平面積層テーブル１８上に図２２に示すように離型フィルムＦを載せ、上面に開口した***２から下部の空気給排空間３を通して真空吸引し、離型フィルムＦを平面積層テーブル１８上に密着させた後、その離型フィルムＦ上で幅１０〜２０ｍｍの一方向材又はクロス材の細幅プリプレグ１３′を４軸制御の自動制御機２１の積層ヘッド２０により所要位置に点在して平面積層し、点在プリプレグ積層体Ｐ３ を形成する。次に大面積のプリプレグ積層体Ｐ１ と格子状のプリプレグ積層体Ｐ２ を、前述のシングルコンター形状の複合材パネルの製造方法と同様に順次プリプレグ積層体裁断装置８で所要の寸法，形状に裁断して、スキン部プリプレグ積層体Ｓ、ダブラー部プリプレグ積層Ｄを形成した後、これらを順次プリプレグ積層体積層治具２２のシングルコンター面２３上に載置積層する。この後前記点在プリプレグ積層体Ｐ３ を平面積層テーブル１８の***２から空気を吹き出して離型フィルムＦごと浮上させ、人手によりプリプレグ積層体裁断装置８に空中搬送し、その裁断装置８の裁断テーブル９上に点在プリプレグ積層体Ｐ３ を吊り降して載置する。そして裁断テーブル９の***２から真空吸引し、離型フィルムＦごと点在プリプレグ積層体Ｐ３ を裁断テーブル９上に密着させた上、所要寸法，形状となるように自動裁断機１０により裁断して、図２３に示すように胴体パネルにおける窓などの開口部の補強となる局所補強プリプレグ積層体Ｇを形成する。次いでこの局所補強プリプレグ積層体Ｇを裁断テーブル９の***２から空気を吹き出して離型フィルムＦごと浮上させた後、クレーン２５のハンガー２６に離型フィルムＦの一側端を把持させてカーテン状に吊り上げる。そしてクレーン２５をプリプレグ積層体積層治具２２に走行させて局所補強プリプレグ積層体Ｇを空中搬送し、積層治具２２のシングルコンター面２３上に先に載置積層したスキン部プリプレグ積層体Ｓ，ダブラー部プリプレグ積層体Ｄ上に、離型フィルムＦを上にして局所補強プリプレグ積層体Ｇを吊り降して載置し、積層し、その後離型フィルムＦを引き剥して除去し、図２４に示すように窓などの開口部を作る胴体パネル用のシングルコンター形状の複合材パネルＰ３を作る。
【００２４】
機器取付用の補強部を持つ翼パネルに用いるダブルコンター形状の複合材パネルの製造方法の実施形態においては、製造装置のプリプレグ点在装置１７は細幅プリプレグ手積み位置検出用テンプレート１９を備えたものを使用し、プリプレグ積層体積層治具２２は上面がダブルコンター面のものが使用される。以下本製造方法の工程について説明する。幅広プリプレグ積層装置１及び細幅プリプレグ積層装置１１で、前述のダブルコンター形状の複合材パネルの製造方法と同様に断続大面積のプリプレグ積層体Ｐ１ ′及び格子状のプリプレグ積層体Ｐ２ を並行して形成する。と同時にプリプレグ点在装置１７で点在プリプレグ積層体Ｐ３ ′を形成する。即ち、プリプレグ点在装置１７の平面積層テーブル１８上に図２０と同様に離型フィルムＦを載せ、上面に開口した***２から真空吸引し、離型フィルムＦを平面積層テーブル１８上に密着させた後、その離型フィルムＦ上で幅１０〜２０ｍｍの一方向材又はクロス材の細幅プリプレグ１３′を、図１及び図３に示される手積み位置検出用テンプレート１９により手積み位置を検出してその位置に手積みにより平面積層し、図２５に示す点在プリプレグ積層体Ｐ３ ′を形成する。次に断続大面積のプリプレグ積層体Ｐ１ ′，格子状のプリプレグ積層体Ｐ２ を、前述のダブルコンター形状の複合材パネルの製造方法と同様に順次プリプレグ積層体裁断装置８で所要の寸法，形状に裁断して、断続スキン部プリプレグ積層体Ｓ′，ダブラー部プリプレグ積層体Ｄを形成する。そして断続スキン部プリプレグ積層体Ｓ′を前述の製造方法と同様にプリプレグ積層体積層治具２２に空中搬送し、その積層治具２２のダブルコンター面２４上に図１７と同様に吊り降して載置し、離型フィルムＦを引き剥した後、断続スキン部プリプレグ積層体Ｓ′を図１８と同様にずらしながらダブルコンター面２４になじませた上、その断続スキン部プリプレグ積層体Ｓ′の隙間に図１９と同様に幅広プリプレグ５を手積みにより追加積層して、図２０と同様に隙間無しのスキン部プリプレグ積層体Ｓを形成する。次いで前記ダブラー部プリプレグ積層体Ｄを前述の製造方法と同様にプリプレグ積層体積層治具２２に空中搬送し、その積層治具２２のダブルコンター面２４上に先に載置して形成したスキン部プリプレグ積層体Ｓの上に離型フィルムＦを上にしてダブラー部プリプレグ積層体Ｄを吊り降して載置し、積層し、その後離型フィルムＦを引き剥して除去する。次に前記点在プリプレグ積層体Ｐ３ ′をプリプレグ積層体裁断装置８に空中搬送し、その裁断装置８の裁断テーブル９上に離型フィルムＦを下にして点在プリプレグ積層体Ｐ３ ′を吊り降して載置する。そして裁断テーブル９の***９から真空吸引し、離型フィルムＦごと点在プリプレグ積層体Ｐ３ ′を裁断テーブル９上に密着させた上、所要寸法，形状となるように自動裁断機１０により裁断して、図２６に示すように翼パネルにおける機器取付け用の補強となる局所補強プリプレグ積層体Ｇ′を形成する。次いでこの局所補強プリプレグ積層体Ｇ′を前述の製造方法と同様に空中搬送し、プリプレグ積層体積層治具２２のダブルコンター２４面上に先に載置積層したスキン部プリプレグ積層体Ｓ，ダブラー部プリプレグ積層体Ｄ上に離型フィルムＦを上にして局所補強プリプレグ積層体Ｇ′を吊り降して載置し、積層し、その後離型フィルムＦを引き剥して除去し、図２６に示すように機器取付用の補強部を持つ翼パネル用のダブルコンター形状の複合材パネルＰ４を作る。
【００２５】
【発明の効果】
以上の説明で判るように本発明の航空機用複合材パネルの製造方法は、大面積のスキン部プリプレグ積層、ダブラー部プリプレグ積層、局所補強プリプレグ積層を個別に行うので、各部分の積層を簡素に高速にできる。またそれにより得られた各プリプレグ積層体を所要の形状，寸法に裁断するのを個別に行うので、各プリプレグ積層体は正確に精密裁断できる。さらに裁断成形された各プリプレグ積層体の集合積層により所要の複合材パネルを作るので、効率的に極めて精度の高い複合材パネルを容易に得ることができる。その上、各プリプレグ積層体の裁断エリアへの搬送及び裁断エリアから集合積層エリアへの搬送を空中搬送により行うので、各プリプレグ積層体は変形，損傷することなく安全に且つ迅速に搬送できて、各工程の連繋がスムーズに行われ、高速積層による複合材パネルの製造を実現できる。
【００２６】
また、本発明の航空機用複合材パネルの製造装置によれば、上記の優れた複合材のパネルの製造方法を、容易に且つ確実に効率よく行うことができる。また、本製造装置は、各プリプレグ積層体の積層装置、裁断装置、積層治具、搬送装置を個別に構成して簡素化し、軽量且つ安価な装置としているので、従来のオールインワンタイプの自動積層機のような大がかりなものに比し高速運転でき、また各装置は遊休させることなく連続的に使用できて、複合材パネルの製造を生産レートの高いものにできる。
【図面の簡単な説明】
【図１】本発明の航空機用複合材パネルの製造装置の概略平面図である。
【図２】図１のＡ−Ａ線断面矢視図である。
【図３】図１の斜視図である。
【図４】図１の製造装置におけるプリプレグ点在積層装置の他の例を示す平面図である。
【図５】図１の製造装置におけるプリプレグ積層体積層治具の他の例を示す斜視図である。
【図６】図１の製造装置における幅広プリプレグ積層装置、細幅プリプレグ積層装置とプリプレグ積層体裁断装置とを往来してプリプレグ積層体をスライド式に空中搬送するスライド式搬送装置を示す概略斜視図である。
【図７】図６のＢ部拡大斜視図である。
【図８】図１の製造装置における細幅プリプレグ積層装置に装備されるプリプレグカセットを示す縦断側面図である。
【図９】図８のプリプレグカセット内に収容するプリプレグテープと巻き上げ紙を示す斜視図である。
【図１０】大面積のプリプレグ積層体をプリプレグ積層体裁断装置で裁断して得たスキン部プリプレグ積層体を示す斜視図である。
【図１１】スキン部プリプレグ積層体を吊り上げて空中搬送する状態を示す側面図である。
【図１２】図１の製造装置におけるシングルコンター面のプリプレグ積層体積層治具上にスキン部プリプレグ積層体を載置した状態を示す斜視図である。
【図１３】細幅プリプレグ積層装置で積層して得た格子状のプリプレグ積層体をプリプレグ積層体裁断装置に空中搬送し載置した上、裁断して得たダブラー部プリプレグ積層体を示す斜視図である。
【図１４】図１２のスキン部プリプレグ積層体に図１３のダブラー部プリプレグ積層体を積層してシングルコンター形状の複合材パネルを作った状態を示す斜視図である。
【図１５】図１の製造装置における幅広プリプレグ積層装置で断続大面積のプリプレグ積層体を作った状態を示す斜視図である。
【図１６】図１５の断続大面積のプリプレグ積層体をプリプレグ積層体裁断装置で裁断して得た断続スキン部プリプレグ積層体を示す斜視図である。
【図１７】図１６の断続スキン部プリプレグ積層体をダブルコンター面のプリプレグ積層体積層治具に載置した状態を示す斜視図である。
【図１８】図１７の断続スキン部プリプレグ積層体をダブルコンター面になじませる状態を示す斜視図である。
【図１９】図１８の断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層する状態を示す斜視図である。
【図２０】図１９の幅広プリプレグの追加積層により得られた隙間無しのスキン部プリプレグ積層体を示す斜視図である。
【図２１】図２０の隙間無しのスキン部プリプレグ積層体に、ダブラー部プリプレグ積層体を積層してダブルコンター形状の複合材パネルを作った状態を示す斜視図である。
【図２２】図４のプリプレグ点在積層装置で点在プリプレグ積層体を作った状態を示す斜視図である。
【図２３】図２２の点在プリプレグ積層体をプリプレグ積層体裁断装置で裁断して得た局所補強プリプレグ積層体を示す斜視図である。
【図２４】シングルコンター面のプリプレグ積層体積層治具上に載置積層したスキン部プリプレグ積層体，ダブラー部プリプレグ積層体の上に、図２３の局所補強プリプレグ積層体を積層してシングルコンター形状の複合材パネルを作った状態を示す斜視図である。
【図２５】図１の製造装置におけるプリプレグ点在積層装置で点在プリプレグ積層体を作った状態を示す斜視図である。
【図２６】図２５の点在プリプレグ積層体をプリプレグ積層体裁断装置で裁断して得た局所補強プリプレグ積層体を示す斜視図である。
【図２７】ダブルコンター面のプリプレグ積層体積層治具上に載置したスキン部プリプレグ積層体，ダブラー部プリプレグ積層体の上に、図２６の局所補強プリプレグ積層体を積層してダブルコンター形状の複合材パネルを作った状態を示す斜視図である。
【符号の説明】
１ 幅広プリプレグ積層装置
２ ***
３ 空気給排空間
４ 平面積層テーブル
５ 幅広プリプレグ
６ 積層ヘッド
７ 自動積層機
８ プリプレグ積層体裁断装置
９ 裁断テーブル
１０ 自動裁断機
１１ 細幅プリプレグ積層装置
１２ 平面積層テーブル
１３ 細幅プリプレグテープ
１４ 積層ヘッド
１５ 自動積層機
１６ プリプレグカセット
１７ プリプレグ点在積層装置
１８ 平面積層テーブル
１９ 細幅プリプレグ手積み位置検出用テンプレート
２０ 積層ヘッド
２１ 自動積層機
２２ プリプレグ積層体積層治具
２３ シングルコンター面
２４ ダブルコンター面
２５ クレーン
２６ ハンガー
２７，２７′ スライド式搬送装置
２８，２８′，２９ レール
３０，３０′ 走行装置
３１ チャック
３２ プリプレグカセットのケース
３３ 繰り出しロール
３４ 巻き込みロール
３５ ４５°方向の細幅プリプレグ
３６ ０°方向の細幅プリプレグ
３７ 巻き上げ紙
Ｆ 離型フィルム
Ｐ１ 大面積のプリプレグ積層体
Ｐ１ ′ 断続大面積のプリプレグ積層体
Ｐ２ 格子状のプリプレグ積層体
Ｐ３ 点在プリプレグ積層体
Ｐ３ ′ 点在プリプレグ積層体
Ｓ スキン部プリプレグ積層体
Ｓ′ 断続スキン部プリプレグ積層体
Ｄ ダブラー部プリプレグ積層体
Ｇ，Ｇ′ 局所補強プリプレグ積層体
Ｐ１ 胴体パネル用のシングルコンター形状の複合材パネル
Ｐ２ 翼パネルや胴体パネルに用いるダブルコンター形状の複合材パネル
Ｐ３ 開口部を作る胴体パネル用のシングルコンター形状の複合材パネル
Ｐ４ 機器取付用の補強部を持つ翼パネル用のダブルコンター形状の複合材パネル[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a method and an apparatus for manufacturing a composite panel made of CFRP or the like used as an aircraft fuselage, wing, rocket fuselage, or fairing panel.
[0002]
[Prior art]
Conventionally, in order to reduce the weight of an aircraft, composite panels made of CFRP or the like have been increasingly used on the outer wall surfaces of various parts such as a fuselage and wings in place of metal panels. In order to manufacture this composite panel, a prepreg automatic laminating machine (commonly referred to as ATL) for directly laminating a prepreg directly on a laminated mold having an upper surface as a contour surface has been developed and used.
This automatic prepreg laminating machine has the function of laminating unidirectional prepregs with a width of 3 or 6 inches by NC control. However, since it can always be laminated only in narrow units, it takes time to laminate large areas and thick plates. And it was inefficient.
[0003]
In addition, recently developed fiber placement devices (commonly known as FPM) are capable of laminating prepregs on a laminar type having a complex contour surface, and that it is possible to simultaneously laminate dozens of narrow prepregs of 3 to 10 mm. Although it is characterized, since the width of the prepreg is too thin for many minutes, the lamination time per unit area takes much longer than that of the automatic prepreg laminator, which is very inefficient.
[0004]
In any of the above methods, the method of laminating the prepreg directly on the laminating mold is restricted by the automatic prepreg laminating, so that no other work can be performed on the mold during the automatic prepreg laminating, and the panel with a high production rate. Not suitable for production.
[0005]
In addition, in order to enable prepreg lamination to a laminated type having a three-dimensional contour surface in any of the above, since the laminated head has a 10-axis control function that has all functions and a function that can cut the prepreg, The stacking head was very heavy and the entire apparatus was large.
[0006]
Furthermore, since the cutting function of the prepreg can only perform linear cutting, it cannot cope with fine shape cutting.
[0007]
Furthermore, in order to perform prepreg lamination on a laminated type having a complicated contour surface, extremely high computing power is required to control the lamination head, and control takes time, so the lamination time also becomes long. Therefore, efficient prepreg lamination was not possible.
[0008]
[Problems to be solved by the invention]
Therefore, the present invention disassembles the functions of the conventional all-in-one type prepreg automatic laminator and operates them as individual functions, respectively, in order to realize high-speed prepreg lamination, wide prepreg planar lamination, narrow prepreg planar Each of the prepreg laminates obtained by laminating and further laminating thin prepregs in individual areas and sequentially cutting the shapes of the prepreg laminates obtained by performing these in another area. The prepreg laminate from each planar lamination area to the cutting area and the prepreg laminate from the cutting area to the stacking jig are lifted and transported in the air. And a method and apparatus for manufacturing an aircraft composite panel by simple prepreg lamination It is.
[0009]
[Means for Solving the Problems]
One of the methods for manufacturing an aircraft composite material panel of the present invention for solving the above-mentioned problem is that after a release film is brought into close contact with a flat laminated table by vacuum suction, a unidirectional material or / And a wide prepreg of a cloth material is laminated in a plane by four-axis control to form a large-area prepreg laminate, and a release film is brought into close contact with another plane lamination table by vacuum suction, and then released. A thin prepreg of unidirectional material and / or cloth material slit to various width dimensions on a film is laminated in plane direction with a required interval in the vertical and horizontal directions by 4-axis control to form a lattice-shaped prepreg laminate. The formation was performed in parallel, and then the large-area prepreg laminate and the lattice-shaped prepreg laminate were floated together with the release film by blowing air from under each planar lamination table. Sequentially slid in the air, placed on one cutting table, fixed by vacuum suction, cut to the required dimensions and shape, and sequentially skinned prepreg laminate, doubler prepreg laminated body Next, the skin part prepreg laminate and the doubler prepreg laminate are sequentially lifted from the cutting table in the form of a curtain, transported in the air, placed on a laminating jig on a single contour surface, laminated, and a composite panel It is characterized by becoming.
[0010]
In this aircraft composite panel manufacturing method, when the skin part prepreg laminated body placed on the single contour surface lamination jig is lifted from the cutting table, the release film is vacuum-sucked to the cutting table. The doubler prepreg laminate to be laminated on the skin prepreg laminate placed on the single contour surface lamination jig is lifted from the cutting table and transported in the air for lamination. It is necessary to take a method in which the release film is lifted up, conveyed in the air, laminated on the skin part prepreg laminate with the release film facing up, and then the release film is removed.
[0011]
Another method for manufacturing an aircraft composite panel according to the present invention is that a release film is brought into close contact with a flat laminated table by vacuum drawing, and then a unidirectional material and / or a cloth material is formed on the release film. Wide prepregs are plane laminated with a gap by 4-axis control to form an intermittent large area prepreg laminate, and a release film is brought into close contact with another plane lamination table by vacuum drawing, and then the mold release is performed. A thin prepreg of unidirectional material and / or cloth material slit to various width dimensions on a film is laminated in plane direction with a required interval in the vertical and horizontal directions by 4-axis control to form a lattice-shaped prepreg laminate. After performing the formation in parallel, and then blowing the air from the bottom of each planar lamination table to float the release film together with the intermittent large area prepreg laminate and the grid-like prepreg laminate Sequentially slid in the air and placed on one cutting table, fixed by vacuum suction, cut to the required dimensions and shape, and then the intermittent skin part prepreg laminate, doubler prepreg laminate Next, the intermittent skin part prepreg laminate was lifted from the cutting table in the form of a curtain and transported in the air and placed on the lamination jig on the double contour surface, so that the intermittent skin portion prepreg laminate was adapted to the double contour surface. Upper, wide prepreg is additionally laminated in the gap of the intermittent skin prepreg laminate, and then the doubler prepreg laminate is lifted from the cutting table as a curtain onto the skin prepreg laminate without gaps and placed in the air And laminated to form a composite panel.
[0012]
In this aircraft composite panel manufacturing method, the intermittent skin part prepreg laminate placed on the lamination jig on the double contour surface, and a wide prepreg added to the gap between the intermittent skin part prepreg laminate, this gap is not present. The doubler prepreg laminate to be laminated on the skin prepreg laminate is lifted from one cutting table and transported in the air and placed on the stacking jig. It is necessary to take a method of placing and laminating each with the mold film facing up and then removing the release film.
[0013]
Another method for manufacturing an aircraft composite panel according to the present invention is that a release film is brought into close contact with a flat laminated table by vacuum suction, and then a unidirectional material and / or a cloth material is formed on the release film. Wide-width prepreg is laminated in plane by 4-axis control to form a large-area prepreg laminate, and a release film is brought into close contact with another plane lamination table by vacuum suction, and then various widths are formed on the release film. Forming a grid-like prepreg laminate by planarly laminating narrow prepregs of a unidirectional material and / or cloth material slitted in dimensions at a required interval in the vertical and horizontal directions by 4-axis control; Furthermore, after the release film is brought into close contact with another plane lamination table by vacuum suction, the unidirectional material and the cross material narrow prepreg are manually stacked on the release film at a plurality of required positions or controlled by four axes. The flat laying is performed in parallel to form the dotted prepreg laminated body, and then the large-area prepreg laminated body, the lattice-shaped prepreg laminated body, and the scattered prepreg laminated body are placed under the respective flat laminated tables. The air is blown out from the air, and the release film is lifted together. Then, it is sequentially transported in the air in a sliding manner, placed on one cutting table, fixed by vacuum suction, and cut to the required dimensions and shape. Then, the skin part prepreg laminate, the doubler prepreg laminate, and the locally reinforced prepreg laminate are sequentially formed, and then these are sequentially lifted from the cutting table in the form of a curtain and transported in the air to be placed on the single contour laminate jig. And laminated to form a composite panel.
[0014]
In this aircraft composite panel manufacturing method, when the skin part prepreg laminated body placed on the single contour surface lamination jig is lifted from the cutting table, the release film is vacuum-sucked to the cutting table. The doubler prepreg laminate laminated on the skin prepreg laminate on the lamination jig and the locally reinforced prepreg laminate laminated on the doubler laminate are lifted from the cutting table and transported in the air. When laminating, the entire release film is lifted and transported in the air, and the release film is placed on the skin part prepreg laminate and doubler prepreg laminate each time the laminate film is removed. is necessary.
[0015]
Still another method for manufacturing an aircraft composite panel according to the present invention is to attach a release film on a flat laminated table by vacuum suction, and then perform unidirectional material and / or cloth material on the release film. Wide prepregs are laminated in a plane with a gap by 4-axis control to form an intermittent large-area prepreg laminate, and after a release film is brought into close contact with another plane lamination table by vacuuming, the separation is performed. Lattice-like prepreg laminates that are laid on a flat film with unidirectional and / or cross-material narrow prepregs slit to various widths on a mold film with 4-axis control at the required intervals in the vertical and horizontal directions And a plurality of narrow-width prepregs of a unidirectional material and / or a cloth material on the release film after the release film is brought into close contact with another plane lamination table by vacuum suction. In parallel to forming a dotted prepreg laminate in a required position by hand stacking or four-axis control, and then forming a dotted prepreg laminate, then an intermittent large-area prepreg laminate, a grid prepreg laminate, and a dotted prepreg After blowing the air from the bottom of each flat laminate table and floating the release film together with the laminate, the laminate is sequentially transported in the air and placed on one cutting table, fixed by vacuum suction, the required dimensions, Cut into a shape, and form an intermittent skin prepreg laminate, doubler prepreg laminate, and locally reinforced prepreg laminate, then lift the intermittent skin prepreg laminate from the cutting table and carry it in the air to double contour After placing the intermittent skin part prepreg laminate on the double contour surface, place the intermittent skin part prepreg laminate on the surface lamination jig. A wide prepreg is additionally laminated, and then the doubler prepreg laminate and the locally reinforced prepreg laminate are sequentially lifted from the cutting table in the form of a curtain and placed on the skin prepreg laminate without gaps. Thus, a composite material panel is obtained.
[0016]
In this aircraft composite panel manufacturing method, the intermittent skin part prepreg laminate placed on the lamination jig on the double contour surface, and a wide prepreg added to the gap between the intermittent skin part prepreg laminate, this gap is not present. The doubler prepreg laminate laminated on the skin prepreg laminate and the locally reinforced prepreg laminate laminated on the doubler prepreg laminate are each lifted from one cutting table and transported in the air and placed on a lamination jig. When placing and laminating, it is necessary to take a method of lifting the release film together with the release film and carrying it in the air, placing and laminating each with the release film facing up, and then removing the release film.
[0017]
The aircraft composite material panel manufacturing apparatus of the present invention for carrying out each of the above manufacturing methods includes a unidirectional material and / or cloth above a flat laminated table having a number of small holes for vacuum suction and air blowing on the upper surface. Above a wide prepreg laminating apparatus equipped with an automatic laminating machine having a four-axis control laminating head for laminating a wide prepreg of a material, and another flat laminating table which also has a number of small holes for vacuum suction and air blowing on the upper surface A narrow prepreg laminating apparatus equipped with an automatic laminating machine having a four-axis control laminating head for laminating narrow prepregs of unidirectional material and / or cloth material in a grid pattern, and vacuum suction and air blowing on the top surface A narrow-width prepreg hand-loading position detection template is provided above another planar lamination table provided with a large number of small holes, or a thin-width prepreg is laminated in a plane. A prepreg interspersed laminator equipped with an automatic laminator having an axially controlled laminating head, and a vacuum on the upper surface provided at a position surrounded by three sides by the wide prepreg laminator, the narrow prepreg laminator and the prepreg interspersed laminator. A prepreg laminated body cutting device provided with an automatic cutting machine above a cutting table provided with a large number of small holes for suction and air blowing, and a single provided at a position facing the prepreg interspersed lamination device so as to sandwich this prepreg laminated body cutting device A prepreg laminate stacking jig having a contour surface or a double contour surface, the wide prepreg stacking device, the narrow prepreg stacking device, the prepreg interspersed stacking device and the prepreg laminate cutting device, and the prepreg stack can be slid. A slidable conveying device for conveying in the air, the prepreg laminate cutting device and the prepreg And traffic the laminate stacking jig those comprising more hanger with crane for air conveying lifting the prepreg laminate like a curtain.
[0018]
In this aircraft composite panel manufacturing apparatus, the narrow prepreg laminating apparatus includes a plurality of prepreg cassettes that accommodates various width sized prepregs that can be attached to and detached from the laminating head of the automatic laminator. It is preferable.
[0019]
DETAILED DESCRIPTION OF THE INVENTION
An embodiment of a method for manufacturing an aircraft composite panel and an apparatus therefor according to the present invention will be described with reference to the drawings. First, an apparatus for performing a method for manufacturing an aircraft composite panel will be described with reference to FIGS. 1 to 3. Reference numeral 1 denotes a wide prepreg laminating apparatus. The wide prepreg laminating apparatus 1 has small holes for vacuum suction and air blowing on the upper surface. A flat laminated table 4 having a width of 10 m and a length of 15 m with a large number of openings 2 and an air supply / exhaust space 3 in the lower part, and a wide prepreg of a unidirectional material and / or cloth material provided above it and having a width dimension exceeding 1 m And an automatic laminating machine 7 having a 4-axis control laminating head 6 for laminating 5 planes. Reference numeral 8 denotes a prepreg laminate cutting apparatus provided adjacent to the wide prepreg lamination apparatus 1. This prepreg laminate cutting apparatus 8 has a plurality of small holes 2 for vacuum suction and air blowing on the upper surface, and an air supply / discharge space 3 in the lower part. And a cutting table 9 having a width of 10 m and a length of 15 m, and an automatic cutting machine 10 provided above the cutting table 9. 11 is a narrow prepreg laminating apparatus provided adjacent to the prepreg laminated body cutting apparatus 8. This narrow prepreg laminating apparatus 11 has a large number of small holes 2 for vacuum suction and air blowing on the upper surface and air supply / discharge at the lower part. A flat laminated table 12 having a width of 10 m and a length of 15 m provided with a space 3 and a thin prepreg tape 13 of one material and / or a cloth material having a width of 1 to 20 cm provided above the flat laminated table 12 are laminated in a lattice shape. It consists of an automatic laminating machine 15 having a 4-axis control laminating head 14. The narrow-width prepreg laminating apparatus 11 is equipped with a plurality of prepreg cassettes 16 that accommodate narrow-width prepreg tapes 13 of one material or cloth material slit to various width dimensions. Replacement can be installed. Reference numeral 17 denotes a prepreg interspersed laminating apparatus provided adjacent to the prepreg laminated body cutting apparatus 8 in a direction perpendicular to the directions of the wide prepreg laminating apparatus 1 and the narrow prepreg laminating apparatus 11. An example is a flat laminated table 18 having a width of 10 m and a length of 15 m in which a large number of small holes 2 for vacuum suction and air blowing are provided on the upper surface and an air supply / exhaust space 3 is provided on the lower portion, and a narrow prepreg stacking position provided above It comprises a detection template 19. Another example of the prepreg interspersed laminating apparatus 17 is a four-axis structure in which thin prepregs of a unidirectional material or cloth material of 10 to 20 mm are interspersed and planarly laminated above a planar laminating table 18 as shown in FIG. An automatic laminating machine 21 having a control laminating head 20 is provided. In FIG. 1 to FIG. 3, reference numeral 22 denotes a prepreg laminate lamination jig provided at a position facing the prepreg interspersed lamination apparatus 17 with the prepreg laminate cutting apparatus 8 interposed therebetween. The upper surface has a single contour surface 23 as shown in FIG. 3 and a double contour surface 24 as shown in FIG. In FIG. 1 to FIG. 3, reference numeral 25 denotes the prepreg laminate cutting device 8 and the prepreg laminate laminate jig 22, and the prepreg laminate cut by the prepreg laminate cutting device 8 is lifted in a curtain shape to prepreg laminate. It is a crane with a hanger 26 that is conveyed in the air to the body stacking jig 22. Reference numerals 27 and 27 ′ denote slide-type conveyance devices that convey the prepreg laminate from the wide prepreg lamination device 1 and the narrow prepreg lamination device 11 to the prepreg laminate cutting device 8. As shown in FIGS. 6 and 7, the slide-type transfer devices 27 and 27 ′ are arranged on both sides of the cutting table of the cutting device 8 from the rails 28 and 28 ′ on both side ends of the flat stacking tables 4 and 12 of the stacking devices 1 and 11. The traveling devices 30 and 30 ′ traveling on the end rail 29 are provided with openable and closable chucks 31 for gripping both side ends of the release film F disposed on the planar laminated tables 4 and 12.
[0020]
The plurality of prepreg cassettes 16 equipped in the narrow prepreg laminating apparatus 11 in the aircraft composite panel manufacturing apparatus having the above-described configuration are provided with a feed roll 33 and a roll-in roll 34 in a case 32 as shown in FIG. For example, as shown in FIG. 9, a 1 to 20 cm narrow prepreg tape 13 having a narrow width prepreg 35 and a narrow prepreg 36 in the direction of 0 ° is not rolled up on the feeding roll 33. 37, one end of the rolled-up paper 37 is fixed to the winding roll 34, and the prepreg cassette 16 is appropriately replaced and mounted on the laminated head 14 shown in FIGS. 14 is rotated by the 4-axis control, the feeding roll 33 is rotated, and the narrow prepreg tape 13 is fed. It is designed to be stacked.
[0021]
Next, various embodiments of a method for manufacturing an aircraft composite panel by the manufacturing apparatus configured as described above will be described. In the embodiment of the manufacturing method of the single contour-shaped composite material panel used for the body panel that does not form an opening such as a window, the prepreg interspersed device 17 of the manufacturing device is not used, and the prepreg laminate stacking jig 22 is the upper surface. As shown in FIG. 3, a single contour surface 23 is used. Hereafter, the process of this manufacturing method is demonstrated. As shown in FIG. 2, the release film F is placed on the flat lamination table 4 of the wide prepreg laminating apparatus 1, and vacuum suction is performed from the small hole 2 opened on the upper surface through the lower air supply / discharge space 3, so that the release film F is flattened. After being brought into close contact with the lamination table 4, as shown in FIG. 3, a wide prepreg 5 having a width dimension of 1 m of a unidirectional material and a cloth material is laminated on the release film F by a laminating head 6 of an automatic laminating machine 7 controlled by four axes. A large area prepreg laminate P 1 Form. In parallel with this, the release film F is placed on the plane lamination table 12 of the narrow-width prepreg laminating apparatus 11 as shown in FIG. 2, and vacuum suction is performed from the small hole 2 opened on the upper surface through the lower air supply / discharge space 3, After the release film F is brought into intimate contact with the flat laminated table 12, a narrow prepreg tape 13 of slit unidirectional material having various width dimensions of 1 to 20 cm as shown in FIG. Is fed out from a prepreg cassette 16 mounted on a laminating head 14 of a four-axis control automatic laminating machine 15 and laminated in a plane with a predetermined interval in the vertical and horizontal directions to form a lattice-shaped prepreg laminate P 2 Form. Next, the large-area prepreg laminate P 1 After the air is blown out from the small holes 2 of the flat laminated table 4 and floated together with the release film F, the release film F is applied to the chuck 31 provided in the traveling device 30 of the slide type conveyance device 27 shown in FIGS. The both side ends of the cutting device 8 are gripped, and the traveling device 30 travels on the rails 28 and 29 and is slid in the air to the adjacent prepreg laminated body cutting device 8, and the prepreg laminated body P is placed on the cutting table 9 of the cutting device 8. 1 The chuck 31 is released from the release film F, and vacuum suction is performed from the small hole 2 opened on the upper surface of the cutting table 9 through the lower air supply / discharge space 3 so that the entire area of the release film F is large. Prepreg laminate P 1 Is brought into close contact with the cutting table 9. Thereafter, the skin part prepreg laminate S is formed by cutting with an automatic cutter 10 as shown in FIG. Next, while the release film F on the cutting table 9 is vacuum-sucked, one end of the skin portion prepreg laminate S is held by the hanger 26 of the crane 25 and peeled off from the release film F, as shown in FIG. Hanging up in a curtain shape. Then, the crane 25 is moved in a right angle direction, and the skin portion prepreg laminate S is transported in the air to the prepreg laminate laminate jig 22 whose upper surface is the single contour surface 23, and on the single contour surface 23 of the laminate jig 22, FIG. Suspend and place as shown. Next, the lattice-shaped prepreg laminate P 2 After the air is blown out from the small holes 2 of the flat laminated table 12 and floated together with the release film F, the release is applied to the chuck 31 provided in the traveling device 30 ′ of the slide type conveying device 27 ′ shown in FIGS. The both sides of the film F are gripped, the traveling device 30 ′ travels on the rails 28 ′ and 29, and is slid in the air to the adjacent prepreg laminated body cutting device 8, and the prepreg is placed on the cutting table 9 of the cutting device 8. Laminate P 2 The chuck 31 is released from the release film F, and vacuum suction is performed from the small hole 2 opened on the upper surface of the cutting table 9 through the lower air supply / discharge space 3 so that the release film F and the release film F are in a lattice shape. Prepreg laminate P 2 Is brought into close contact with the cutting table 9. Thereafter, a doubler prepreg laminate D is formed which is cut by an automatic cutter 10 so as to have a required size and shape, and serves as a reinforcement of a mounting portion such as a stringer in the body panel as shown in FIG. Next, this doubler prepreg laminate D was blown out of the small hole 2 of the cutting table 9 to float the release film F together with the release film F, and then one end of the release film F on the hanger 26 of the crane 25 as in FIG. Is lifted in a curtain shape as in FIG. Then, the crane 25 is moved in a right angle direction so that the doubler prepreg laminate D is conveyed in the air to the prepreg laminate laminate jig 22, and the skin part prepreg laminate placed on the single contour surface 23 of the laminate jig 22 first. The doubler prepreg laminate D is suspended and placed on the body S with the release film F facing up, and then the release film F is peeled off to remove the fuselage as shown in FIG. A single-contour composite panel P1 for the panel is made.
[0022]
In the embodiment of the manufacturing method of the double contour-shaped composite panel used for the wing panel and the fuselage panel, the prepreg interspersed device 17 of the manufacturing apparatus is not used, and the prepreg laminated body stacking jig 22 has an upper surface shown in FIG. Thus, the double contour surface 24 is used. Hereafter, the process of this manufacturing method is demonstrated. As shown in FIG. 2, the release film F is placed on the flat lamination table 4 of the wide prepreg lamination apparatus 1, and vacuum suction is performed from the small hole 2 opened on the upper surface, thereby bringing the release film F into close contact with the flat lamination table 4. After that, on the release film F, as shown in FIG. 15, a wide prepreg 5 having a width dimension of 1 m of a unidirectional material and a cloth material is laminated in a plane with a gap by a laminating head 6 of an automatic laminating machine 7 controlled by four axes. , Intermittent large area prepreg laminate P 1 ′ Is formed. In parallel with this, the narrow-width prepreg laminating apparatus 11 has a grid-like prepreg laminate P as shown in FIGS. 2 Form. Next, the intermittent large area prepreg laminate P 1 'Is blown out from the small holes 2 of the flat laminated table 4 and floated together with the release film F, and then released onto the chuck 31 provided in the traveling device 30 of the slide type conveying device 27 shown in FIGS. The both side ends of F are gripped, and the traveling device 30 is caused to travel on the rails 28 and 29 and is slid in the air to the adjacent prepreg laminated body cutting device 8, and the prepreg having an intermittent large area is transferred to the cutting table 9 of the cutting device 8. Laminate P 1 ′ Is lowered, the chuck 31 is released from the release film F, and vacuum suction is performed from the small hole 2 opened on the upper surface of the cutting table 9, so that the release film F and the release film F are intermittently large-area prepreg laminate P 1 'Is brought into close contact with the cutting table 9. Thereafter, the automatic cutting machine 10 cuts to the required size and shape as shown in FIG. 16 to form the intermittent skin portion prepreg laminate S ′. Next, after the intermittent skin portion prepreg laminate S ′ is blown up from the small hole 2 of the cutting table 9 and floated together with the release film F, the hanger 26 of the crane 25 holds the one side end of the release film F. As in 11, it is lifted in a curtain shape. Then, the crane 25 is moved in a right angle direction, and the intermittent skin portion prepreg laminate S ′ is transported in the air to the prepreg laminate laminate jig 22 whose upper surface is the double contour surface 24, and on the double contour surface 24 of the laminate jig 22. As shown in FIG. 17, it is suspended and placed with the release film F facing up. Next, the release film F is peeled off as shown in FIG. 18 so that the intermittent skin portion prepreg laminate S ′ is moved to the double contour surface 24 while shifting, and the gap is formed between the intermittent skin portion prepreg laminate S ′. As shown in FIG. 19, the wide prepreg 5 is additionally laminated by hand to form a skin part prepreg laminate S without gaps as shown in FIG. 20. During this period, the lattice-shaped prepreg laminate P 2 Is slid in the air to the adjacent prepreg laminate cutting apparatus 8 in the same procedure as in the above-described embodiment, placed on the cutting table 9 and placed thereon, so that the required dimensions and shape are obtained. A doubler prepreg laminate D that is a reinforcing structure for an attachment portion such as a stringer in a wing panel or a fuselage panel is formed by cutting with an automatic cutting machine 10. Next, the doubler prepreg laminate D is transported in the air to the prepreg laminate laminate jig 22 in the same procedure as in the above-described embodiment, and placed on the double contour surface 24 of the laminate jig 22 first. The doubler part prepreg laminate D is suspended and placed on the formed skin part prepreg laminate S with the release film F facing upward, and then the release film F is peeled off and removed. As shown in FIG. 5, a double contour composite material panel P2 used for a wing panel and a fuselage panel is produced.
[0023]
In the embodiment of the manufacturing method of the single contour-shaped composite panel used for the fuselage panel for making an opening such as a window, the prepreg interspersed device 17 of the manufacturing device uses the one provided with the automatic laminator 21 shown in FIG. The prepreg laminate jig 22 has a single contour surface 23 on the upper surface. Hereinafter, the process of this manufacturing method is demonstrated. In the wide prepreg laminating apparatus 1 and the narrow prepreg laminating apparatus 11, the prepreg laminated body P having a large area is obtained in the same manner as the method for manufacturing the single-contour-shaped composite panel described above. 1 And lattice-shaped prepreg laminate P 2 Are formed in parallel. At the same time, the prepreg interspersed device 17 interspersed with the prepreg laminate P 3 Form. That is, the release film F is placed on the plane lamination table 18 of the prepreg interspersed device 17 as shown in FIG. 22, and vacuum suction is performed from the small hole 2 opened on the upper surface through the lower air supply / discharge space 3 to release the release film F. Is adhered to the flat laminating table 18, and then a unidirectional material or a cross material narrow prepreg 13 ′ having a width of 10 to 20 mm is formed on the release film F by the laminating head 20 of the automatic controller 21 with four-axis control. Interspersed at the required position and planarly laminated, the scattered prepreg laminate P 3 Form. Next, a large-area prepreg laminate P 1 And lattice prepreg laminate P 2 Were sequentially cut into the required size and shape by the prepreg laminate cutting apparatus 8 in the same manner as in the method for manufacturing the single contour composite panel described above, to form the skin part prepreg laminate S and the doubler prepreg laminate D. Thereafter, these are sequentially placed and laminated on the single contour surface 23 of the prepreg laminate laminate jig 22. Thereafter, the interspersed prepreg laminate P 3 The air is blown out from the small holes 2 of the flat laminate table 18 to float together with the release film F, and is manually transported in the air to the prepreg laminate cutting apparatus 8, and the prepreg laminate P scattered on the cutting table 9 of the cutting apparatus 8. 3 Is suspended and placed. And vacuum suction is performed from the small hole 2 of the cutting table 9, and the release film F and the dotted prepreg laminate P 3 Is adhered to the cutting table 9, and is cut by an automatic cutting machine 10 so as to have a required size and shape, and as shown in FIG. 23, a locally reinforced prepreg laminate is used to reinforce openings such as windows in a fuselage panel. Form body G. Next, this locally reinforced prepreg laminate G was blown out from the small hole 2 of the cutting table 9 and floated together with the release film F, and then a hanger 26 of the crane 25 was held on one side end of the release film F to form a curtain shape. Suspend to. Then, the crane 25 is moved to the prepreg laminate lamination jig 22 to transport the locally reinforced prepreg laminate G in the air, and the skin portion prepreg laminate S, which is first placed and laminated on the single contour surface 23 of the lamination jig 22, On the doubler prepreg laminate D, the locally reinforced prepreg laminate G is suspended and placed with the release film F facing up, and then the release film F is peeled off and removed, as shown in FIG. As shown, a single-contour composite panel P3 for a fuselage panel that creates an opening such as a window is made.
[0024]
In the embodiment of the manufacturing method of the double contour-shaped composite material panel used for the wing panel having the reinforcing portion for mounting the equipment, the prepreg interspersed device 17 of the manufacturing apparatus includes the narrow-width prepreg hand-loading position detecting template 19. The prepreg laminate laminate jig 22 has an upper surface with a double contour surface. Hereinafter, the process of this manufacturing method is demonstrated. In the wide prepreg laminating apparatus 1 and the narrow prepreg laminating apparatus 11, the prepreg laminated body P having an intermittent large area is obtained in the same manner as the above-described method of manufacturing the double-contour-shaped composite panel. 1 'And lattice-shaped prepreg laminate P 2 Are formed in parallel. At the same time, the prepreg interspersed device 17 interspersed with the prepreg laminate P 3 ′ Is formed. That is, the release film F is placed on the flat laminated table 18 of the prepreg interspersed device 17 in the same manner as in FIG. 20, and vacuum suction is performed through the small holes 2 opened on the upper surface, thereby bringing the release film F into close contact with the flat laminated table 18. After that, on the release film F, the hand-loading position is detected by the hand-loading position detecting template 19 shown in FIG. 1 and FIG. Then, it is laminated in a plane by hand stacking at that position, and the scattered prepreg laminate P shown in FIG. 3 ′ Is formed. Next, intermittent large-area prepreg laminate P 1 ', Lattice-shaped prepreg laminate P 2 In the same manner as in the method of manufacturing the double-contour composite panel described above, the prepreg laminate cutting apparatus 8 sequentially cuts to the required size and shape, and the intermittent skin portion prepreg laminate S ′ and doubler prepreg laminate D. Form. Then, the intermittent prepreg laminate S ′ is conveyed to the prepreg laminate jig 22 in the air in the same manner as in the above-described manufacturing method, and suspended on the double contour surface 24 of the laminate jig 22 as in FIG. After placing and peeling off the release film F, the intermittent skin portion prepreg laminate S ′ was fitted to the double contour surface 24 while shifting in the same manner as in FIG. 18, and then the intermittent skin portion prepreg laminate S ′. As in FIG. 19, the wide prepreg 5 is additionally stacked in the gap by hand to form the skin part prepreg laminate S without gap as in FIG. Next, the doubler part prepreg laminate D is transported in the air to the prepreg laminate lamination jig 22 in the same manner as in the above-described manufacturing method, and the skin part formed by placing on the double contour surface 24 of the lamination jig 22 first. The doubler prepreg laminate D is suspended and placed on the prepreg laminate S with the release film F facing up, and then the release film F is peeled off and removed. Next, the dotted prepreg laminate P 3 'Is conveyed in the air to the prepreg laminate cutting apparatus 8, and the dotted prepreg laminate P is placed on the cutting table 9 of the cutting apparatus 8 with the release film F facing down. 3 ′ Is suspended and placed. Then, vacuum suction is performed from the small holes 9 of the cutting table 9, and the release film F and the dotted prepreg laminate P 3 ′ Is brought into intimate contact with the cutting table 9 and cut by the automatic cutting machine 10 so as to have a required size and shape, and a locally reinforced prepreg laminate as a reinforcement for mounting the equipment on the wing panel as shown in FIG. G 'is formed. Next, the locally reinforced prepreg laminate G ′ is conveyed in the air in the same manner as in the above-described manufacturing method, and the skin portion prepreg laminate S, the doubler portion, which is first placed and laminated on the double contour 24 surface of the prepreg laminate lamination jig 22. 26. The locally reinforced prepreg laminate G ′ is suspended and placed on the prepreg laminate D with the release film F facing upward, stacked, and then the release film F is peeled off and removed, as shown in FIG. A double-contoured composite panel P4 for a wing panel having a reinforcing portion for mounting the device is made.
[0025]
【The invention's effect】
As can be seen from the above description, the aircraft composite panel manufacturing method of the present invention performs large-area skin prepreg lamination, doubler prepreg lamination, and locally reinforced prepreg lamination individually, so that the lamination of each part is simplified. Can be fast. Moreover, since each prepreg laminated body obtained thereby is individually cut into a required shape and size, each prepreg laminated body can be precisely and precisely cut. Furthermore, since a required composite material panel is made by collective lamination of the prepreg laminates that have been cut and formed, an extremely highly accurate composite material panel can be obtained efficiently and easily. In addition, since each prepreg laminate is transported to and from the cutting area by air transportation, each prepreg laminate can be transported safely and quickly without deformation or damage. Each process is smoothly linked, and it is possible to produce a composite panel by high-speed lamination.
[0026]
Further, according to the aircraft composite panel manufacturing apparatus of the present invention, the above-described excellent composite panel manufacturing method can be easily and reliably performed efficiently. In addition, the present manufacturing apparatus is a lightweight, inexpensive apparatus that is configured by simplifying the laminating apparatus, the cutting apparatus, the laminating jig, and the conveying apparatus for each prepreg laminate, so that the conventional all-in-one type automatic laminating machine Compared with such a large-scale device, it can be operated at high speed, and each device can be used continuously without being idle, so that the production of the composite panel can be made at a high production rate.
[Brief description of the drawings]
FIG. 1 is a schematic plan view of an aircraft composite panel manufacturing apparatus according to the present invention.
FIG. 2 is a cross-sectional view taken along line AA in FIG.
FIG. 3 is a perspective view of FIG. 1;
4 is a plan view showing another example of the prepreg interspersed laminating apparatus in the manufacturing apparatus of FIG. 1. FIG.
5 is a perspective view showing another example of the prepreg laminate laminate jig in the manufacturing apparatus of FIG. 1. FIG.
FIG. 6 is a schematic perspective view showing a slide type conveying apparatus that moves between the wide prepreg laminating apparatus, the narrow prepreg laminating apparatus, and the prepreg laminated body cutting apparatus in the manufacturing apparatus of FIG. 1 to convey the prepreg laminated body in the air in a sliding manner. It is.
7 is an enlarged perspective view of a portion B in FIG. 6. FIG.
8 is a longitudinal side view showing a prepreg cassette equipped in a narrow prepreg laminating apparatus in the manufacturing apparatus of FIG. 1; FIG.
9 is a perspective view showing a prepreg tape and a rolled-up paper housed in the prepreg cassette of FIG. 8. FIG.
FIG. 10 is a perspective view showing a skin part prepreg laminate obtained by cutting a large-area prepreg laminate with a prepreg laminate cutting apparatus.
FIG. 11 is a side view showing a state in which a skin part prepreg laminate is lifted and transported in the air.
12 is a perspective view showing a state in which a skin part prepreg laminate is placed on a prepreg laminate lamination jig having a single contour surface in the manufacturing apparatus of FIG. 1; FIG.
FIG. 13 is a perspective view showing a doubler prepreg laminate obtained by cutting a lattice-shaped prepreg laminate obtained by laminating with a narrow-width prepreg laminate and carrying it in the air to a prepreg laminate cutting apparatus and then cutting it. It is.
14 is a perspective view showing a state in which a single-contour-shaped composite material panel is formed by laminating the doubler prepreg laminate of FIG. 13 on the skin prepreg laminate of FIG. 12;
15 is a perspective view showing a state in which a prepreg laminated body having an intermittent large area is formed by the wide prepreg laminating apparatus in the manufacturing apparatus of FIG. 1. FIG.
16 is a perspective view showing an intermittent skin part prepreg laminate obtained by cutting the prepreg laminate having the intermittent large area of FIG. 15 with a prepreg laminate cutting apparatus. FIG.
17 is a perspective view showing a state in which the intermittent skin part prepreg laminate of FIG. 16 is placed on a prepreg laminate laminate jig having a double contour surface.
18 is a perspective view showing a state in which the intermittent skin part prepreg laminated body of FIG. 17 is adapted to the double contour surface.
19 is a perspective view showing a state in which a wide prepreg is additionally laminated in the gap of the intermittent skin part prepreg laminated body of FIG. 18. FIG.
20 is a perspective view showing a skin part prepreg laminated body without gaps obtained by additional lamination of the wide prepreg of FIG. 19. FIG.
21 is a perspective view showing a state in which a double contour-shaped composite material panel is formed by laminating a doubler prepreg laminate on the skin portion prepreg laminate having no gap in FIG. 20;
22 is a perspective view showing a state where a dotted prepreg laminated body is made by the prepreg dotted lamination apparatus of FIG. 4; FIG.
23 is a perspective view showing a locally reinforced prepreg laminate obtained by cutting the interspersed prepreg laminate of FIG. 22 with a prepreg laminate cutting apparatus. FIG.
FIG. 24 shows a single contour shape by laminating the locally reinforced prepreg laminate of FIG. 23 on the skin part prepreg laminate and the doubler prepreg laminate placed and laminated on the prepreg laminate lamination jig on the single contour surface. It is a perspective view which shows the state which made the composite material panel of this.
25 is a perspective view showing a state where a dotted prepreg laminated body is made by the prepreg dotted lamination apparatus in the manufacturing apparatus of FIG. 1. FIG.
26 is a perspective view showing a locally reinforced prepreg laminate obtained by cutting the interspersed prepreg laminate of FIG. 25 with a prepreg laminate cutting apparatus. FIG.
FIG. 27 is a cross-sectional view of the double-contour-shaped reinforced prepreg laminate of FIG. 26 laminated on the skin part prepreg laminate and the doubler prepreg laminate placed on the prepreg laminate lamination jig on the double contour surface. It is a perspective view which shows the state which made the composite material panel.
[Explanation of symbols]
1 Wide prepreg laminating equipment
2 small holes
3 Air supply / discharge space
4 Planar laminated table
5 Wide prepreg
6 Laminated head
7 Automatic laminating machine
8 Pre-preg laminate cutting device
9 Cutting table
10 Automatic cutting machine
11 Narrow prepreg laminating equipment
12 Planar laminated table
13 Narrow prepreg tape
14 Laminated head
15 Automatic laminating machine
16 prepreg cassette
17 Prepreg interspersed laminating equipment
18 Planar laminated table
19 Narrow prepreg hand load position detection template
20 Laminated head
21 Automatic laminating machine
22 Prepreg Laminate Lamination Jig
23 Single contour surface
24 Double contour surface
25 crane
26 Hanger
27,27 'slide type conveying device
28, 28 ', 29 rails
30, 30 'traveling device
31 Chuck
32 Prepreg cassette case
33 Feeding roll
34 Entrainment roll
35 45 ° narrow prepreg
360 narrow prepreg in the direction of 0 °
37 Rolled paper
F release film
P 1 Large area prepreg laminate
P 1 ′ Intermittent large area prepreg laminate
P 2 Lattice-like prepreg laminate
P 3 Dotted prepreg laminate
P 3 ′ Dotted prepreg laminate
S skin prepreg laminate
S 'Intermittent skin prepreg laminate
D Doubler prepreg laminate
G, G 'Locally reinforced prepreg laminate
P1 Single contour composite panel for fuselage panel
P2 Double-contour composite panel used for wing panels and fuselage panels
P3 Single-contour composite panel for fuselage panels that create openings
P4 Double-contour composite panel for wing panels with reinforcement for mounting equipment

Claims (10)

平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により平面積層し、大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することを並行して行い、次に大面積のプリプレグ積層体と格子状のプリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次スライド式に空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次スキン部プリプレグ積層体，ダブラー部プリプレグ積層体を形成し、次いでこれらスキン部プリプレグ積層体，ダブラー部プリプレグ積層体を順次裁断テーブルからカーテン状に吊り上げ空中搬送してシングルコンター面の積層治具上に載置し、積層して、複合材パネルとなすことを特徴とする航空機用複合材パネルの製造方法。After the release film is brought into close contact with the plane lamination table by vacuum suction, a wide-area prepreg of a unidirectional material and / or a cloth material is plane-laminated by 4-axis control on the release film to obtain a large area prepreg laminate. After forming and attaching a release film on another plane lamination table by vacuum suction, a narrow width prepreg of a unidirectional material and / or cloth material slit to various width dimensions on the release film Four-axis control is performed to form a lattice-shaped prepreg laminate in parallel by forming a plane stack with a required interval in the vertical and horizontal directions, and then to form a large-area prepreg laminate and a lattice-shaped prepreg laminate. After blowing the air from the bottom of each flat laminated table and floating the release film together with the release film, it is sequentially transported in the air in a sliding manner and placed on one cutting table for vacuum suction. In addition, the skin part prepreg laminate and the doubler prepreg laminate are sequentially formed, and then the skin part prepreg laminate and the doubler prepreg laminate are sequentially cut into the table. A method of manufacturing a composite panel for an aircraft, wherein the composite panel is lifted in a curtain shape, transported in the air, placed on a stacking jig on a single contour surface, and stacked to form a composite panel. 請求項１記載の航空機用複合材パネルの製造方法において、シングルコンター面の積層治具上に載置するスキン部プリプレグ積層体は、裁断テーブルから吊り上げる際、離型フィルムを裁断テーブルに真空吸引したまま離型フィルムから引き剥がす方法をとり、シングルコンター面の積層治具上に載置したスキン部プリプレグ積層体の上に積層するダブラー部プリプレグ積層体は、裁断テーブルから吊り上げ空中搬送して積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にしてスキン部プリプレグ積層体に積層し、その後離型フィルムを除去する方法をとることを特徴とする航空機用複合材パネルの製造方法。2. The method of manufacturing an aircraft composite panel according to claim 1, wherein when the skin part prepreg laminate placed on the single contour surface lamination jig is lifted from the cutting table, the release film is vacuum-sucked to the cutting table. The doubler part prepreg laminate to be laminated on the skin part prepreg laminate placed on the single contour surface lamination jig is lifted from the cutting table and stacked in the air by laminating from the release film as it is. At the time, the entire release film is lifted and conveyed in the air, and the release film is placed on the skin prepreg laminate, and then the release film is removed. Method. 平面積層テーブル上に離型フィルムを真空引きにより密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により隙間をあけて平面積層し、断続大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空引きにより密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することを並行して行い、次に断続大面積のプリプレグ積層体と格子状プリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次スライド式に空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次断続スキン部プリプレグ積層体，ダブラー部プリプレグ積層体を形成し、次いで断続スキン部プリプレグ積層体を裁断テーブルからカーテン状に吊り上げ空中搬送してダブルコンター面の積層治具上に載置し、断続スキン部プリプレグ積層体をダブルコンター面になじませた上、断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層し、次にこの隙間無しのスキン部プリプレグ積層体上にダブラー部プリプレグ積層体を裁断テーブルからカーテン状に吊り上げ空中搬送して載置し、積層して、複合材パネルとなすことを特徴とする航空機用複合材パネルの製造方法。After the release film is brought into close contact with the plane lamination table by vacuum drawing, a wide prepreg of a unidirectional material and / or cloth material is laminated on the release film with a gap by 4-axis control, and the intermittent large area Unidirectional material and / or cloth material slitted in various width dimensions on the release film after forming the release film on the other flat lamination table by vacuum drawing Narrow width prepregs are plane-laminated at predetermined intervals in the vertical and horizontal directions by 4-axis control to form a lattice-shaped prepreg laminate in parallel, and then an intermittent large-area prepreg laminate And the lattice-shaped prepreg laminate are blown out of air from the bottom of each flat laminate table and floated together with the release film, and then sequentially transported in the air in a sliding manner on one cutting table. And then cut into the required dimensions and shape to form an intermittent skin prepreg laminate and a doubler prepreg laminate, and then the intermittent skin prepreg laminate from the cutting table. Suspended in the form of a curtain, transported in the air and placed on a stacking jig on the double contour surface. Next, the doubler prepreg laminate is stacked on the skin prepreg laminate without gaps, lifted in a curtain form from the cutting table, transported in the air, and stacked to form a composite panel. A method for manufacturing an aircraft composite panel. 請求項３記載の航空機用複合材パネルの製造方法において、ダブルコンター面の積層治具上に載置する断続スキン部プリプレグ積層体、及びこの断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層後この隙間無しのスキン部プリプレグ積層体上に積層するダブラー部プリプレグ積層体は、夫々１つの裁断テーブルから吊り上げ空中搬送して積層治具上に載置積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にして各々載置，積層し、その後離型フィルムを除去する方法をとることを特徴とする航空機用複合材パネルの製造方法。4. The method of manufacturing an aircraft composite panel according to claim 3, wherein an intermittent skin part prepreg laminate placed on a double contour surface laminating jig, and a wide prepreg additionally laminated in a gap between the intermittent skin part prepreg laminates. The doubler prepreg laminate to be laminated on the skin portion prepreg laminate without gaps is then lifted from one cutting table, transported in the air, and placed on the stacking jig to be lifted together with the release film. A method for manufacturing an aircraft composite panel, comprising transporting, placing and laminating each with a release film facing upward, and then removing the release film. 平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御により平面積層し、大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することと、さらに別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の細幅プリプレグを複数の所要位置に手積み又は４軸制御により平面積層し、点在プリプレグ積層体を形成することを並行して行い、次に大面積のプリプレグ積層体と格子状のプリプレグ積層体と点在プリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次スライド式に空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次スキン部プリプレグ積層体，ダブラー部プリプレグ積層体，局所補強プリプレグ積層体を形成し、次いでこれらを順次裁断テーブルからカーテン状に吊り上げ空中搬送してシングルコンター面の積層治具上に載置し、積層して、複合材パネルとなすことを特徴とする航空機用複合材パネルの製造方法。After the release film is brought into close contact with the plane lamination table by vacuum suction, a wide prepreg of a unidirectional material and / or a cloth material is plane-laminated by 4-axis control on the release film to obtain a large area prepreg laminate. After forming and attaching a release film on another plane lamination table by vacuum suction, a narrow width prepreg of unidirectional material and / or cloth material slit to various width dimensions on the release film Four-axis control is used to laminate the surfaces in the vertical and lateral directions with a required interval to form a lattice-shaped prepreg laminate, and the release film is brought into close contact with another plane lamination table by vacuum suction. After that, on the release film, a thin prepreg of unidirectional material and / or cross material is stacked in a plurality of required positions by hand stacking or four-axis control to form a dotted prepreg laminate. In parallel, the large-area prepreg laminate, the lattice-shaped prepreg laminate, and the dotted prepreg laminate were blown up from the bottom of each planar lamination table to float together with the release film. After that, it is sequentially transported in the air in a sliding manner, placed on one cutting table, fixed by vacuum suction, cut to the required dimensions and shape, and sequentially laminated to the skin part prepreg laminate and the doubler prepreg lamination. Body, locally reinforced prepreg laminated body, and then these are sequentially lifted in a curtain form from a cutting table, transported in the air, placed on a single contour surface laminating jig, and laminated to form a composite panel. A method for manufacturing a composite panel for aircraft. 請求項５記載の航空機用複合材パネルの製造方法において、シングルコンター面の積層治具上に載置するスキン部プリプレグ積層体は、裁断テーブルから吊り上げる際、離型フィルムを裁断テーブルに真空吸引したまま離型フィルムから引き剥がす方法をとり、積層治具上のスキン部プリプレグ積層体上に積層するダブラー部プリプレグ積層体及びそのダブラー部積層体上に積層する局所補強プリプレグ積層体は、裁断テーブルから吊り上げ空中搬送して積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にして各々スキン部プリプレグ積層体，ダブラー部プリプレグ積層体に積層の都度、離型フィルムを除去する方法をとることを特徴とする航空機用複合材パネルの製造方法。6. The method of manufacturing an aircraft composite panel according to claim 5, wherein when the skin part prepreg laminate placed on the single contour surface lamination jig is lifted from the cutting table, the release film is vacuum-sucked to the cutting table. The doubler prepreg laminate to be laminated on the skin part prepreg laminate on the lamination jig and the locally reinforced prepreg laminate to be laminated on the doubler laminate are taken from the cutting table. When lifting and transporting and laminating, the release film is lifted together and transported in the air, and the release film is lifted up to remove the release film each time it is laminated on the skin prepreg laminate and doubler prepreg laminate. A method for manufacturing a composite panel for aircraft, characterized in that: 平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の幅広プリプレグを４軸制御に隙間をあけて平面積層し、断続大面積のプリプレグ積層体を形成することと、別の平面積層テーブル上に離型フィルムを真空引きにより密着させた後、その離型フィルム上で各種幅寸法にスリットされた一方向材又は／及びクロス材の細幅プリプレグを４軸制御により縦方向，横方向に所要の間隔をあけて平面積層し、格子状のプリプレグ積層体を形成することと、さらに別の平面積層テーブル上に離型フィルムを真空吸引により密着させた後、その離型フィルム上で一方向材又は／及びクロス材の細幅プリプレグを複数の所要位置に手積み又は４軸制御により平面積層し、点在プリプレグ積層体を形成することとを並行して行い、次に断続大面積のプリプレグ積層体と格子状のプリプレグ積層体と点在プリプレグ積層体とを各々の平面積層テーブルの下から空気を吹き出して離型フィルムごと浮上させた後、順次空中搬送して１つの裁断テーブル上に載置し、真空吸引により固定した上、所要寸法，形状となるように裁断して、順次断続スキン部プリプレグ積層体，ダブラー部プリプレグ積層体，局所補強プリプレグ積層体を形成し、次いで断続スキン部プリプレグ積層体を裁断テーブルからカーテン状に吊り上げ空中搬送してダブルコンター面の積層治具上に載置し、断続スキン部プリプレグ積層体をダブルコンター面になじませた上、断続スキン部プリプレグ積層体の隙間に幅広プリプレグを追加積層し、次にこの隙間無しのスキン部プリプレグ積層体にダブラー部プリプレグ積層体，局所補強プリプレグ積層体を順次裁断テーブルからカーテン状に吊り上げ空中搬送して載置し、積層して、複合材パネルとなすことを特徴とする航空機用複合材パネルの製造方法。After the release film is brought into close contact with the plane lamination table by vacuum suction, the wide prepreg of the unidirectional material and / or the cloth material is laminated on the release film with a gap in a 4-axis control, and the intermittent large area Unidirectional material and / or cloth material slitted in various width dimensions on the release film after forming the release film on the other flat lamination table by vacuum drawing The thin prepregs are flatly laminated at the required intervals in the vertical and horizontal directions by 4-axis control to form a lattice-like prepreg laminate, and the release film is vacuumed on another flat laminate table. After adhering by suction, thin prepregs of unidirectional material and / or cloth material are stacked on a plurality of required positions on the release film by hand stacking or four-axis control, and dotted prepregs The layered body is formed in parallel, and then the intermittent large-area prepreg laminate, lattice-shaped prepreg laminate, and interspersed prepreg laminate are blown away from the bottom of each planar lamination table. After floating together with the mold film, it is sequentially transported in the air and placed on one cutting table, fixed by vacuum suction, cut to the required dimensions and shape, and sequentially interrupted skin part prepreg laminate, A doubler prepreg laminate and a locally reinforced prepreg laminate are formed, and then the intermittent skin prepreg laminate is lifted from the cutting table in the form of a curtain and transported in the air to be placed on the double contour surface lamination jig, and the intermittent skin portion. After the prepreg laminate is blended with the double contour surface, a wide prepreg is additionally laminated in the gap of the intermittent skin prepreg laminate, and then there is no gap For aircraft, characterized in that a doubler prepreg laminate and a locally reinforced prepreg laminate are sequentially lifted from a cutting table in the form of a curtain and placed in the air, stacked and laminated to a skin prepreg laminate. A method for manufacturing a composite panel. 請求項７記載の航空機用複合材パネルの製造方法において、ダブルコンター面の積層治具上に載置する断続スキン部プリプレグ積層体、この断続スキン部プリプレグ積層体の隙間に幅広のプリプレグを追加積層後この隙間無しのスキン部プリプレグ積層体上に積層するダブラー部プリプレグ積層体及びこのダブラー部プリプレグ積層体上に積層する局所補強プリプレグ積層体は、夫々１つの裁断テーブルから吊り上げ空中搬送して積層治具上に載置積層する際、離型フィルムごと吊り上げて空中搬送し、離型フィルムを上にして各々載置，積層し、その後離型フィルムを除去する方法をとることを特徴とする航空機用複合材パネルの製造方法。8. The method of manufacturing an aircraft composite panel according to claim 7, wherein an intermittent skin part prepreg laminate placed on a lamination jig having a double contour surface, and a wide prepreg is additionally laminated in a gap between the intermittent skin part prepreg laminates. The doubler prepreg laminate laminated on the skin prepreg laminate without gaps and the locally reinforced prepreg laminate laminated on the doubler prepreg laminate are each lifted from one cutting table and transported in the air to laminate. For aircraft, characterized in that when placing and laminating on a tool, the release film is lifted together and transported in the air, and each release film is placed and laminated, and then the release film is removed. A method for manufacturing a composite panel. 上面に真空吸引，空気吹き出しの***を多数設けた平面積層テーブルの上方に、一方向材又は／及びクロス材の幅広プリプレグを平面積層する４軸制御の積層ヘッドを有する自動積層機を備えた幅広プリプレグ積層装置と、同じく上面に真空吸引，空気吹き出しの***を多数設けた別の平面積層テーブルの上方に、一方向材又は／及びクロス材の細幅プリプレグを格子状に平面積層する４軸制御の積層ヘッドを有する自動積層機を備えた細幅プリプレグ積層装置と、同じく上面に真空吸引，空気吹き出しの***を多数設けたさらに別の平面積層テーブルの上方に細幅プリプレグ手積み位置検出用テンプレートを備えるか、または細幅プリプレグを平面積層する４軸制御の積層ヘッドを有する自動積層機を備えたプリプレグ点在積層装置と、前記幅広プリプレグ積層装置と細幅プリプレグ積層装置とプリプレグ点在積層装置とで三方より囲まれる位置に設けられ上面に真空吸引，空気吹き出しの***を多数設けた裁断テーブルの上方に自動裁断機を備えたプリプレグ積層体裁断装置と、このプリプレグ積層体裁断装置を挾むようにプリプレグ点在積層装置と対向する位置に設けられシングルコンター面又はダブルコンター面を有するプリプレグ積層体積層治具と、前記幅広プリプレグ積層装置，細幅プリプレグ積層装置，プリプレグ点在積層装置とプリプレグ積層体裁断装置とを往来してプリプレグ積層体をスライド式に空中搬送するスライド式搬送装置と、前記プリプレグ積層体裁断装置とプリプレグ積層体積層治具とを往来してプリプレグ積層体をカーテン状に吊り上げて空中搬送するハンガー付きクレーンとより成る航空機用複合材パネルの製造装置。Wide with an automatic laminating machine with a 4-axis control laminating head that planarly laminates a wide prepreg of unidirectional material and / or cloth material above a flat laminating table with many small holes for vacuum suction and air blowing on the upper surface Four-axis control for laminating narrow prepregs of unidirectional material and / or cloth material in a grid pattern above a prepreg laminating device and another planar laminating table that is also provided with many small holes for vacuum suction and air blowing on the top surface A narrow prepreg laminating apparatus equipped with an automatic laminating machine having a laminating head and a narrow prepreg stacking position detecting template above another flat laminating table provided with many small holes for vacuum suction and air blowing on the upper surface. Or a prepreg interspersed laminating apparatus equipped with an automatic laminating machine having a four-axis control laminating head for planarly laminating narrow prepregs, An automatic cutting machine is provided above the cutting table, which is provided at a position surrounded by three sides of the wide prepreg laminating device, narrow prepreg laminating device, and prepreg interspersed laminating device, and provided with many small holes for vacuum suction and air blowing on the upper surface. A prepreg laminate cutting apparatus, a prepreg laminate lamination jig having a single contour surface or a double contour surface provided at a position facing the prepreg interspersed lamination apparatus so as to sandwich the prepreg laminate cutting apparatus, and the wide prepreg lamination apparatus A narrow-width prepreg laminating apparatus, a prepreg interspersed laminating apparatus, and a prepreg laminated body cutting apparatus, and a slide-type conveying apparatus that slidably conveys the prepreg laminated body in the air, and the prepreg laminated body cutting apparatus and the prepreg laminated body laminated Carry the jigs and lift the prepreg laminate in a curtain to carry it in the air More comprising manufacturing apparatus for aircraft composite panel hanger with crane for. 請求項９記載の航空機用複合材パネルの製造装置において、細幅プリプレグ積層装置には、その自動積層機の積層ヘッドに着脱させる各種幅寸法の細幅プリプレグを繰り出し可能に収容した複数のプリプレグカセットを備えたことを特徴とする航空機用複合材パネルの製造装置。10. The aircraft composite panel manufacturing apparatus according to claim 9, wherein the narrow prepreg laminating apparatus includes a plurality of prepreg cassettes in which narrow prepregs of various width dimensions to be attached to and detached from the laminating head of the automatic laminator are accommodated. An aircraft composite panel manufacturing apparatus comprising:
JP2002173242A 2002-06-13 2002-06-13 Method and apparatus for manufacturing aircraft composite panel Expired - Lifetime JP3632176B2 (en)

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