JPH1016085A - Manufacture of fuselage skin of airplane - Google Patents
Manufacture of fuselage skin of airplaneInfo
- Publication number
- JPH1016085A JPH1016085A JP8174845A JP17484596A JPH1016085A JP H1016085 A JPH1016085 A JP H1016085A JP 8174845 A JP8174845 A JP 8174845A JP 17484596 A JP17484596 A JP 17484596A JP H1016085 A JPH1016085 A JP H1016085A
- Authority
- JP
- Japan
- Prior art keywords
- fuselage
- skin
- sub
- cylinder
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- 238000000034 method Methods 0.000 claims abstract description 19
- 238000009730 filament winding Methods 0.000 claims abstract description 14
- 238000000429 assembly Methods 0.000 claims description 2
- 238000004804 winding Methods 0.000 abstract description 3
- 238000005192 partition Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 5
- 239000000835 fiber Substances 0.000 description 4
- 238000003754 machining Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Moulding By Coating Moulds (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、複合材製の航空機
胴体の円筒部分の外板の製造方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for manufacturing a skin of a cylindrical portion of an aircraft fuselage made of a composite material.
【０００２】[0002]
【従来の技術】従来の技術を図４に示す。従来のフィラ
メントワインディング法（以下、Ｆ／Ｗ法ともいう）で
は、円筒の長手方向には板厚を変えることができるが、
円筒方向には板厚を変えることが困難であった。2. Description of the Related Art FIG. In the conventional filament winding method (hereinafter also referred to as F / W method), the thickness can be changed in the longitudinal direction of the cylinder.
It was difficult to change the thickness in the cylindrical direction.
【０００３】[0003]
【発明が解決しようとする課題】一般に航空機の外板板
厚は、（Ａ）引張側（引張応力のかかる側）のクラウン
（機体上面）では薄く、（Ｂ）剪断側（剪断応力のかか
る側）のサイド（機体側面）では中くらい、（Ｃ）圧縮
側（圧縮応力のかかる側）のキール（機体下面）では厚
くなっている。Generally, the thickness of the outer skin of an aircraft is small on the crown (the upper surface of the fuselage) on the (A) tension side (the side on which the tensile stress is applied), and (B) on the shear side (the side on which the shear stress is applied). ) Side (the side of the fuselage) is medium, and (C) the keel (the underside of the fuselage) on the compression side (the side where the compressive stress is applied) is thick.
【０００４】従って、同一厚さのフィラメント・ワイン
ディングにすると、重量的に不利になる。そのため、従
来の技術には、次のような問題がある。 （１）フィラメントワインディング法を用いて一体に成
型した円筒を、そのまま航空機の胴体に用いると、円筒
の板厚は、板厚の大きいキール（機体下面）に合わせる
ことになるため、サイド（機体側面）およびクラウン
（機体上面）では、余肉となり、重量が増加する。 （２）また、一体に成型した円筒を、そのまま航空機の
胴体に用いると、窓や扉などの開口部の穴開け加工、内
側へのフレームの取付けが困難であるとともに、輸送す
ることも困難である。 本発明は、これらの問題を解決することができる航空機
の胴体外板の製造方法を提供することを目的とする。[0004] Therefore, it is disadvantageous in terms of weight to use filament winding of the same thickness. Therefore, the conventional technology has the following problems. (1) If a cylinder integrally molded by the filament winding method is used as it is for an aircraft fuselage, the thickness of the cylinder is adjusted to the keel (lower surface of the fuselage) having a large thickness. ) And the crown (the upper surface of the fuselage) become excess and the weight increases. (2) Further, if the integrally molded cylinder is used for the fuselage of an aircraft as it is, it is difficult to make holes in openings such as windows and doors, and to attach a frame to the inside, and it is also difficult to transport. is there. An object of the present invention is to provide a method of manufacturing an aircraft fuselage skin that can solve these problems.
【０００５】[0005]
（第１の手段）本発明に係る航空機の胴体外板の製造方
法は、（Ａ）キール（機体下面）用外板に適した板厚の
円筒と、サイド（機体側面）用外板に適した板厚の円筒
と、クラウン（機体上面）用外板に適した板厚の円筒を
それぞれ、フィラメント・ワインディング法を用いて巻
付けて製作した後、オートクレーブで硬化し、（Ｂ）前
記フィラメント・ワインディング法とオートクレーブで
製作した各円筒を、長手方向に切断して、複数に分割
し、（Ｃ）前記分割によってできた各外板に、窓や扉な
どの開口部の加工を施した後、フレームとストリンガー
を取り付けて、サブ・アセンブリを製作し、（Ｄ）前記
キール（機体下面）用サブ・アセンブリと、サイド（機
体側面）用サブ・アセンブリと、クラウン（機体上面）
用のサブ・アセンブリを、適切に再配置した状態で、ス
プライス・ロンジェロンを用いて結合し直すことによ
り、総組立てを行ない、（Ｅ）適切な箇所に必要な板厚
を有する航空機の円筒部分胴体を製作することを特徴と
する。(First Means) The method for manufacturing an aircraft fuselage skin according to the present invention is as follows. (A) A cylinder having a thickness suitable for a keel (bottom surface) skin and a side (side fuselage) skin. And a cylinder having a thickness suitable for the crown (upper surface of the fuselage) are wound by using a filament winding method, and then hardened by an autoclave. Each cylinder produced by the winding method and the autoclave is cut in the longitudinal direction and divided into a plurality of pieces. (C) After processing the openings such as windows and doors on each outer plate formed by the division, Attach the frame and stringer to produce a sub-assembly. (D) The sub-assembly for the keel (bottom surface of the fuselage), the sub-assembly for the side (side surface of the fuselage), and the crown (top surface of the fuselage)
The complete sub-assembly by using splice rongerons, with the sub-assembly for the aircraft properly repositioned, and (E) the cylindrical section fuselage of the aircraft having the required thickness at the appropriate locations It is characterized by producing.
【０００６】すなわち、本発明方法は、 （１）キール（機体下面）、サイド（機体側面）、およ
びクラウン（機体上面）の外板に、それぞれ適した板厚
の円筒を、それぞれ、フィラメント・ワインディング法
を用いて巻付けて製作し、オートクレーブで硬化する。 （２）そのようにして製作した各円筒を、長手方向に複
数（４分割程度）に切断し、分割してできた外板に、窓
や扉などの開口部の加工を施した後、フレームやストリ
ンガーなどを取り付けて、サブ・アセンブリ（ｓｕｂ−
ａｓｓｅｍｂｌｙ）とする。 （３）このようにして出来たキール（機体下面）用と、
サイド（機体側面）用と、クラウン（機体上面）用のサ
ブ・アセンブリを、適切に再配置した状態で、スプライ
ス・ロンジェロンを用いて結合し直すことにより、適切
な箇所に必要な板厚を与えた胴体を製作することを特徴
とする。That is, the method of the present invention comprises the following steps: (1) Cylinders having suitable thicknesses are respectively provided on the outer plates of the keel (the lower surface of the fuselage), the side (the side surface of the fuselage), and the crown (the upper surface of the fuselage), respectively, by filament winding. It is manufactured by winding using a method and is cured in an autoclave. (2) Each cylinder manufactured in this manner is cut into a plurality of pieces (about 4 divisions) in the longitudinal direction, and the outer plate obtained by dividing the outer plate is processed into openings such as windows and doors. And sub-assembly (sub-
assembly). (3) for the keel (bottom of the fuselage) made in this way,
The sub-assemblies for the side (the fuselage side) and the crown (the top surface of the fuselage) are properly repositioned and re-assembled using a splice rongeron to give the necessary thickness to the appropriate places. It is characterized by manufacturing a torso.
【０００７】従って、次のように作用する。 （１）円筒状態でなく、長手方向に分割した状態で作業
するため、窓や扉などの開口部の機械加工が容易に出来
るとともに、組立て作業、および輸送が容易になる。 （２）キール（機体下面）、サイド（機体側面）、クラ
ウン（機体上面）、の各部位の外板に適した板厚を与え
ることができるので、構造重量を軽減することができ
る。Therefore, the following operation is performed. (1) Since work is performed not in a cylindrical state but in a state of being divided in the longitudinal direction, machining of an opening such as a window or a door can be easily performed, and assembling work and transportation can be facilitated. (2) It is possible to provide a plate thickness suitable for the outer plate of each part of the keel (the lower surface of the fuselage), the side (the side surface of the fuselage), and the crown (the upper surface of the fuselage), so that the structural weight can be reduced.
【０００８】[0008]
（第１の実施の形態）本発明の第１の実施の形態を図１
〜図３に示す。図１は、第１の実施の形態に係る円筒の
分割、結合にかかる基本概念図。(First Embodiment) FIG. 1 shows a first embodiment of the present invention.
3 to FIG. FIG. 1 is a basic conceptual diagram relating to division and connection of a cylinder according to the first embodiment.
【０００９】図２は、第１の実施の形態に係る航空機胴
体の側面図。図３は、第１の実施の形態に係るフィラメ
ント・ワインディング法の概念図である。FIG. 2 is a side view of the aircraft fuselage according to the first embodiment. FIG. 3 is a conceptual diagram of the filament winding method according to the first embodiment.
【００１０】図１〜図３に示すように、本発明方法は、 （Ａ）フィラメントワインディング法を用いて、板厚の
異なる数種の円筒を製作し、硬化後に長手方向に複数に
分割する。 （Ｂ）そして、これらの外板を板厚に応じて配置し直
し、 （Ｃ）スプライス・ロンジェロンを用いて結合し、再び
円筒とすることにより、適切な箇所に適切な板厚を与え
ることができる方法である。As shown in FIGS. 1 to 3, the method of the present invention comprises the following steps: (A) By using a filament winding method, several kinds of cylinders having different plate thicknesses are produced, and after curing, they are divided into a plurality of pieces in the longitudinal direction. (B) Then, these outer plates are rearranged in accordance with the plate thickness, and (C) bonding is performed using a splice rongeron to form a cylinder again, so that an appropriate plate thickness can be given to an appropriate place. That's the way you can.
【００１１】図１は、円筒の分割、結合にかかる基本概
念を示す。まず、クラウン（機体上面）用と、サイド
（機体側面）用と、キール（機体下面）用の、３種の円
筒を別々に製作し、それらを長手方向に複数に分割（図
１では、４分割）した後、穴開け加工、フレーム、スト
リンガーなどの取付けのためのサブ組立てを施す。その
後、総組立てにおいて、スプライス・ロンジェロンによ
り結合する。FIG. 1 shows the basic concept of dividing and connecting a cylinder. First, three types of cylinders are separately manufactured for the crown (the upper surface of the fuselage), the side (the side surface of the fuselage), and the keel (the lower surface of the fuselage), and they are divided into a plurality of pieces in the longitudinal direction (4 in FIG. 1). After splitting, sub-assembly for drilling, mounting of frames, stringers, etc. is performed. Then, in the whole assembly, they are joined by a splice rongeron.
【００１２】図２は、航空機の胴体の側面であり、主翼
取付部胴体の前および後に円筒部分胴体が存在する。そ
の部分を、本発明の適用箇所とする。図３は、フィラメ
ント・ワインディング法の概念図である。FIG. 2 is a side view of the fuselage of an aircraft having a cylindrical partial fuselage in front of and behind the wing mounting fuselage. This part is the application point of the present invention. FIG. 3 is a conceptual diagram of the filament winding method.
【００１３】マンドレル（成形型）３は、機体の外形線
図面から板厚分だけ小さいものを準備する。板厚に対応
して、数種のマンドレル（成形型）を用いる。図３の繊
維出口２を傾け、長手方向に移動させる速度を制御する
ことにより、繊維を９０°方向だけでなく、任意の角度
方向に巻くことができる。A mandrel (molding die) 3 is prepared which is smaller by the plate thickness from the outline drawing of the machine body. Several types of mandrels (forming dies) are used according to the thickness of the sheet. By tilting the fiber outlet 2 in FIG. 3 and controlling the speed at which the fiber is moved in the longitudinal direction, the fiber can be wound not only in the 90 ° direction but also in any angle direction.
【００１４】[0014]
【発明の効果】本発明は前述のように構成されているの
で、以下に記載するような効果を奏する。 （１）キール（機体下面）、サイド（機体側面）、クラ
ウン（機体上面）の各部位の外板に適した板厚を与える
ことができるので、航空機の構造重量の軽減を図ること
ができる。 （２）フィラメント・ワインディング法を用いることに
より、プリプレグをレイアップする場合と比較して、コ
スト・タウンを図ることができる。 （３）一体成型した円筒を分割して作業するため、窓や
扉などの開口部の機械加工が容易になる。 （４）サブ・アセンブリ単位に分割した状態で、作業を
することができるので、組立て作業、および輸送の容易
化もできるので、コスト・タウンを図ることができる。Since the present invention is configured as described above, it has the following effects. (1) It is possible to reduce the structural weight of the aircraft because it is possible to provide a suitable thickness for the outer plates of the keel (the lower surface of the fuselage), the side (the side surface of the fuselage), and the crown (the upper surface of the fuselage). (2) By using the filament winding method, it is possible to reduce the cost as compared with the case where the prepreg is laid up. (3) Since the integrally molded cylinder is divided and worked, machining of an opening such as a window or a door becomes easy. (4) Since work can be performed in a state of being divided into sub-assembly units, assembling work and transportation can be facilitated, so that cost reduction can be achieved.
【図１】本発明の第１の実施の形態に係る円筒の分割、
結合にかかる基本概念図。FIG. 1 is a diagram illustrating division of a cylinder according to a first embodiment of the present invention;
The basic concept figure concerning connection.
【図２】本発明の第１の実施の形態に係る航空機胴体の
側面図。FIG. 2 is a side view of the aircraft fuselage according to the first embodiment of the present invention.
【図３】本発明の第１の実施の形態に係るフィラメント
・ワインディング法の概念図。FIG. 3 is a conceptual diagram of a filament winding method according to the first embodiment of the present invention.
１…フィラメント・ワインディング・マシン・ヘッド ２…繊維出口 ３…マンドレル（成形型） ４…スプライス・ロンジェロン １１…キール（機体下面）用外板に適した板厚の円筒 １２…サイド（機体側面）用外板に適した板厚の円筒 １３…クラウン（機体上面）用外板に適した板厚の円筒 ２１…キール（機体下面）用サブ・アセンブリ ２２…サイド（機体側面）用サブ・アセンブリ ２３…クラウン（機体上面）用のサブ・アセンブリ １００…航空機の円筒部分胴体 DESCRIPTION OF SYMBOLS 1 ... Filament winding machine head 2 ... Fiber outlet 3 ... Mandrel (molding die) 4 ... Splice longeron 11 ... Cylinder of thickness suitable for outer plate for keel (bottom surface of body) 12 ... Side (side surface of body) A cylinder having a thickness suitable for an outer panel 13 ... A cylinder having a thickness suitable for an outer panel for a crown (upper surface of the fuselage) 21 ... A sub-assembly for a keel (lower surface of the fuselage) 22 ... A sub-assembly for a side (side surface of the fuselage) 23 ... Sub-assembly for crown (top of fuselage) 100: cylindrical fuselage of aircraft
───────────────────────────────────────────────────── フロントページの続き (51)Int.Cl.6 識別記号 庁内整理番号 ＦＩ 技術表示箇所 // Ｂ２９Ｋ 101:10 105:08 ──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. 6 Identification code Agency reference number FI Technical display location // B29K 101: 10 105: 08
Claims (1)
板厚の円筒（１１）と、サイド（機体側面）用外板に適
した板厚の円筒（１２）と、クラウン（機体上面）用外
板に適した板厚の円筒（１３）をそれぞれ、フィラメン
ト・ワインディング法を用いて巻付けて製作した後、オ
ートクレーブで硬化し、（Ｂ）前記フィラメント・ワイ
ンディング法とオートクレーブで製作した各円筒（１
１、１２、１３）を、長手方向に切断して、複数に分割
し、（Ｃ）前記分割によってできた各外板に、窓や扉な
どの開口部の加工を施した後、フレームとストリンガー
を取り付けて、サブ・アセンブリを製作し、（Ｄ）前記
キール（機体下面）用サブ・アセンブリ（２１）と、サ
イド（機体側面）用サブ・アセンブリ（２２）と、クラ
ウン（機体上面）用のサブ・アセンブリ（２３）を、適
切に再配置した状態で、スプライス・ロンジェロン
（４）を用いて結合し直すことにより、総組立てを行な
い、（Ｅ）適切な箇所に必要な板厚を有する航空機の円
筒部分胴体（１００）を製作することを特徴とする航空
機の胴体外板の製造方法。(A) A cylinder (11) having a thickness suitable for a keel (bottom surface) skin, a cylinder (12) having a thickness suitable for a side (body side) skin, and a crown ( Each of the cylinders (13) having a thickness suitable for an outer panel for the upper surface of the machine body is wound by using a filament winding method and manufactured, then hardened by an autoclave, and (B) manufactured by the filament winding method and the autoclave. Each cylinder (1
1, 12 and 13) are cut in the longitudinal direction and divided into a plurality of pieces. (C) Each of the outer plates formed by the above-mentioned division is subjected to processing of openings such as windows and doors, and then the frame and the stringer are cut. And (D) a sub-assembly (21) for the keel (bottom surface of the fuselage), a sub-assembly (22) for side (side surface of the fuselage), and a crown (upper surface of the fuselage). With the sub-assemblies (23) properly relocated and re-assembled using the splice rongeron (4), the total assembly is performed and (E) an aircraft having the required thickness at the appropriate locations A method of manufacturing an aircraft fuselage skin, comprising manufacturing the cylindrical partial fuselage (100).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8174845A JPH1016085A (en) | 1996-07-04 | 1996-07-04 | Manufacture of fuselage skin of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8174845A JPH1016085A (en) | 1996-07-04 | 1996-07-04 | Manufacture of fuselage skin of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH1016085A true JPH1016085A (en) | 1998-01-20 |
Family
ID=15985664
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8174845A Withdrawn JPH1016085A (en) | 1996-07-04 | 1996-07-04 | Manufacture of fuselage skin of airplane |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH1016085A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007532384A (en) * | 2004-04-06 | 2007-11-15 | ザ・ボーイング・カンパニー | Composite barrel section of aircraft fuselage and other structures, and method and system for manufacturing such barrel section |
| JP2010529922A (en) * | 2007-06-13 | 2010-09-02 | エアバス・オペレーションズ・ゲーエムベーハー | Method and apparatus for manufacturing aircraft fuselage compartment with composite fiber material |
| JP2011504425A (en) * | 2007-10-31 | 2011-02-10 | アレニア・アエロナウティカ・ソシエタ・ペル・アチオニ | Method of using a vacuum bag around a fuselage body made of a composite material to be polymerized |
| WO2011077700A1 (en) * | 2009-12-25 | 2011-06-30 | 川崎重工業株式会社 | Disassembly method and disassembly apparatus for mandrel used in production of composite material structure |
| WO2011077699A1 (en) * | 2009-12-25 | 2011-06-30 | 川崎重工業株式会社 | Assembly method and assembly apparatus for mandrel used in production of composite material structure |
| WO2011077698A1 (en) * | 2009-12-25 | 2011-06-30 | 川崎重工業株式会社 | Die for manufacturing a composite material structure |
| JP2012101787A (en) * | 2010-11-11 | 2012-05-31 | Boeing Co:The | Fuselage employing multifunctional crown and method of making the same |
| ES2725897A1 (en) * | 2018-03-28 | 2019-09-30 | Torres Martinez M | MANUFACTURING PROCEDURE OF REINFORCED STRUCTURES AND STRUCTURE OBTAINED (Machine-translation by Google Translate, not legally binding) |
-
1996
- 1996-07-04 JP JP8174845A patent/JPH1016085A/en not_active Withdrawn
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007532384A (en) * | 2004-04-06 | 2007-11-15 | ザ・ボーイング・カンパニー | Composite barrel section of aircraft fuselage and other structures, and method and system for manufacturing such barrel section |
| JP2008184155A (en) * | 2004-04-06 | 2008-08-14 | Boeing Co:The | Composite barrel section of aircraft fuselage and other structures, and method and system for manufacturing such barrel section |
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| US9021678B2 (en) | 2009-12-25 | 2015-05-05 | Kawasaki Jukogyo Kabushiki Kaisha | Disassembling method of mandrel used for manufacturing composite material structure and disassembling apparatus of mandrel |
| US9079654B2 (en) | 2009-12-25 | 2015-07-14 | Kawasaki Jukogyo Kabushiki Kaisha | Assembling method of mandrel used for manufacturing composite material structure and assembling apparatus of mandrel |
| US9434483B2 (en) | 2009-12-25 | 2016-09-06 | Kawasaki Jukogyo Kabushiki Kaisha | Assembling method of mandrel used for manufacturing composite material structure and assembling apparatus of mandrel |
| US9522487B2 (en) | 2009-12-25 | 2016-12-20 | Kawasaki Jukogyo Kabushiki Kaisha | Disassembling method of mandrel used for manufacturing composite material structure and disassembling apparatus of mandrel |
| JP2012101787A (en) * | 2010-11-11 | 2012-05-31 | Boeing Co:The | Fuselage employing multifunctional crown and method of making the same |
| ES2725897A1 (en) * | 2018-03-28 | 2019-09-30 | Torres Martinez M | MANUFACTURING PROCEDURE OF REINFORCED STRUCTURES AND STRUCTURE OBTAINED (Machine-translation by Google Translate, not legally binding) |
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