JPS6219440A - Molding of fuselage of airplane - Google Patents
Molding of fuselage of airplaneInfo
- Publication number
- JPS6219440A JPS6219440A JP60160875A JP16087585A JPS6219440A JP S6219440 A JPS6219440 A JP S6219440A JP 60160875 A JP60160875 A JP 60160875A JP 16087585 A JP16087585 A JP 16087585A JP S6219440 A JPS6219440 A JP S6219440A
- Authority
- JP
- Japan
- Prior art keywords
- resin
- adhesive
- reinforcing fibers
- mold
- split
- 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.)
- Pending
Links
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
Abstract
Description
【発明の詳細な説明】
産業上の利用分野
本発明は、飛行機の胴体を繊維強化樹脂により成形する
飛行機の胴体成形方法に関するものである。 −
従来の技術
従来では、例えば第２８図に示すように、ベース上に設
置したウレタン製、金属製、木製などの半割雌型−の凹
大成形面日上に、カーボン繊維やガラス繊維などの強化
繊維を敷くとともに樹脂を供給することと、上方からプ
レスロールｆｉＩを作用させることを繰り返す、いわゆ
るハンドレオ−バーレイにより半割円筒状の積層体−を
成形する。そして所定の厚さまで行なつｔこのち外側を
フィルムで覆い、この状態で吸引を行なうこと多こよっ
て内部の脱泡を行なう。その後１両端を折曲げ成形した
のち硬化させることにより、第２４図に示すように、両
端に連結部−を一体形成してなる半割円筒状の外皮体−
を成形していた。そして第２５図に示すよう１ζ、左右
一対の外皮体■を、その連結部−を介して結合−するこ
とにより胴体（５７１を成形している。DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a method for molding an airplane fuselage using a fiber-reinforced resin. - Conventional technology In the past, for example, as shown in Fig. 28, carbon fiber, glass fiber, etc. A laminate having a half-split cylindrical shape is formed by a so-called hand-over lay, which repeats laying reinforcing fibers, supplying resin, and applying a press roll fiI from above. After this is done to a predetermined thickness, the outside is covered with a film and suction is applied in this state to defoam the inside. After that, both ends are bent and formed and then hardened to form a half-cylindrical outer shell body with connecting parts integrally formed at both ends, as shown in Fig. 24.
was being molded. Then, as shown in FIG. 25, a pair of left and right outer skin bodies (2) are connected via their connecting portions (1ζ) to form a body (571).
発明が解決しようとする問題点
上記のような従来方式によると１強化繊維を敷く際に、
相手が凹入成形面６１Ｊであることから均一な且つ充分
なテンションを強化繊維にかけることができない。この
ことも原因の１つとして、！Ｍ脂含有率が高くなって外
皮体■の肉厚が厚くなると共にコスト高になり、さらに
樹脂含有率はコントロールできない。しかも作業能率は
非常に悪い。Problems to be Solved by the Invention According to the conventional method as described above, when laying reinforcing fibers,
Since the opponent is the concave molding surface 61J, uniform and sufficient tension cannot be applied to the reinforcing fibers. This is also one of the reasons! As the M fat content increases, the thickness of the outer shell (2) becomes thicker and the cost increases, and furthermore, the resin content cannot be controlled. Moreover, the work efficiency is very poor.
問題点を解決するための手段
上記問題点を解決すべく本発明における飛行機の胴体成
形方法は、半割雌型と半割雄型とを準備しておき、半割
雄型を凸出成形面を上位として設置したのち、この凸出
成形面上に、接着剤付着の強化繊維をテンションをかけ
ながら積層し１次いで接着剤を硬化させて得た半割円筒
状の繊維積層体をミシン掛けして強化繊維間を結合した
のち接着剤を除去し１次いで繊維積層体の両端に熱溶融
性や化学的溶解性の保護材料を含浸形成し、そして繊維
積層体を雌型内に設置したのち、この繊維積層体に樹脂
を含浸させ、次いで樹脂硬化により半割円筒状の外皮体
を成形したのち、前記保護材料を除去して外皮体の両端
に強化繊維を露出させ。Means for Solving the Problems In order to solve the above-mentioned problems, the method for molding an airplane fuselage according to the present invention includes preparing a half-split female mold and a half-split male mold, and forming the half-split male mold on a convex molding surface. was installed as the upper layer, and on this convex molded surface, adhesive-adhered reinforcing fibers were laminated under tension, and then the adhesive was cured to obtain a halved cylindrical fiber laminate, which was then sewn by a sewing machine. After bonding the reinforcing fibers together, the adhesive is removed, first, both ends of the fiber laminate are impregnated with a thermally meltable or chemically soluble protective material, and the fiber laminate is placed in a female mold. This fiber laminate is impregnated with a resin, and then the resin is cured to form a half-cylindrical outer skin, and the protective material is removed to expose reinforcing fibers at both ends of the outer skin.
そして一対の外皮体の露出強化繊維どうしを絡ませたの
ち、この絡み部に樹脂を供給し硬化させることにより胴
体を成形している。After the exposed reinforcing fibers of the pair of outer skin bodies are entangled with each other, a resin is supplied to the entwined portions and hardened to form the fuselage.
実施例
以下に本発明の一実施例を第１図〜第２２図に基づいて
説明する。EXAMPLE An example of the present invention will be described below with reference to FIGS. 1 to 22.
先ず第１図に示すように、凹入成形面（１）を有する半
割雌型（２）が準備され、さらに第２図に示すように、
凹入成形面（１）に対応する凸出成形面（３）を有する
半割雄型（４）が準備される。First, as shown in FIG. 1, a half female mold (2) having a concave molding surface (1) is prepared, and as shown in FIG.
A half-split male mold (4) having a convex molding surface (3) corresponding to the concave molding surface (1) is prepared.
次いで第８図、第４図に示すように、半割雄型（４）を
回転テーブル（５）上に、その凸出成形面（３）を上位
として載置する。回転テーブル（５）は、縦軸（６）が
回転駆動装置（７）に連動連結して縦軸心（８）の周り
に回転自在である。前記凸出成形面（３）１番こ、接着
剤付着の強化繊維（９）をテンションをかけながら積層
する。この強化繊維（９）はカーボン繊維やガラス繊維
やアラミド繊維などの混合物からなり、それぞれボビン
状の形態から複数の案内ロール０Ｑによりテンションを
かけられた状態で引き出され凸出成形面（３）上に至る
が、その引き出し経路中において、接着剤αυを入れた
槽Ｑ３１ｅ通ることによって、この接着剤αυが付着さ
れる。なお接着剤但としては。Next, as shown in FIGS. 8 and 4, the half-split male mold (4) is placed on the rotary table (5) with its convex molding surface (3) facing upward. The rotary table (5) has a vertical axis (6) operatively connected to a rotary drive device (7) and is rotatable around a vertical axis (8). On the first surface of the convex molded surface (3), reinforcing fibers (9) to which adhesive is attached are laminated while applying tension. This reinforcing fiber (9) is made of a mixture of carbon fiber, glass fiber, aramid fiber, etc., and is pulled out from a bobbin-like form under tension by a plurality of guide rolls 0Q and placed on the convex molding surface (3). However, during the extraction path, the adhesive αυ is adhered by passing through a tank Q31e containing the adhesive αυ. However, as for the adhesive.
パラフィン、油類、水性エマルジョン糊などが使用され
る。さらに引き出し経路中において強化繊維（９）はく
し板時により整とんされ、また所定の積層を行なったの
ちに、切断装置σ尋によって無駄が生じないように切断
される。このような積層は何回も行なわれるのであり、
また適時、回転テーブル（５）を介して半割雄型（４）
の向き変更が行なわれる。Paraffin, oil, water-based emulsion glue, etc. are used. Further, in the drawing path, the reinforcing fibers (9) are arranged by a comb board, and after being laminated in a predetermined manner, they are cut by a cutting device σ so as not to cause any waste. This kind of lamination is done many times,
At the appropriate time, the half-split male mold (4) is
A change in direction is performed.
すなわち第４図の状態から４５度回転させたのが第５図
の状態であり、これは例えば第４図の状態から９０度回
転させるなど、積層のたびに向きが任意に変更される。That is, the state shown in FIG. 5 is obtained by rotating 45 degrees from the state shown in FIG. 4, and the orientation is arbitrarily changed each time the layers are stacked, for example, by rotating 90 degrees from the state shown in FIG.
所定数の積層を行なったのち、第６図に示すように外側
にフィルム（至）をかぶせると共に、フィルム（ト）の
周縁をシール部材（ト）でシールし、そして適所に設け
た吸引管（財）を介してフィルム（至）内、を真空化さ
せる。これにより強化繊維（９）群は圧縮され、さらに
テンションが助長されると共に肉厚が薄くなる。After a predetermined number of layers have been laminated, as shown in Figure 6, the outside is covered with a film (T), the periphery of the film (G) is sealed with a sealing member (T), and a suction tube (T) provided at an appropriate location is covered. The inside of the film is evacuated through the film. As a result, the reinforcing fibers (9) group are compressed, the tension is further promoted, and the wall thickness is reduced.
このように圧縮成形した状態で、第７図に示すように加
熱装置！（７）により接着剤（６）を硬化させ、強化繊
維（９）群をプリセットして半割円筒状の繊維積層体ａ
９とする。その後にフィルム（へ）が除去され。In this compression molded state, as shown in Fig. 7, a heating device is installed! (7) to harden the adhesive (6) and preset the reinforcing fiber (9) group to form a halved cylindrical fiber laminate a.
9. The film is then removed.
そして第７図仮想線に示すよう逍繊維積層体ａ嗜は脱型
される。The fiber laminate a is then demolded as shown by the imaginary line in FIG.
これにより得た繊維積層体α呻は１例えば＠８図に示す
ように積み重ねるなどしてプールされる。The fiber laminates α thus obtained are stacked and pooled, for example, as shown in Figure @8.
そして繊維積層体σ場は第９図に示すようにミシン装置
−により肉厚方向で縫いとげられる。これにより第１０
図に示すように、例えば糸の一例であ □るアラ
ミド繊維ゆにより強化繊維（９）間の結合、ならびに肉
厚方向の補強が行なわれる。The fiber laminate σ field is then sewn off in the thickness direction using a sewing machine as shown in FIG. This results in the 10th
As shown in the figure, the reinforcing fibers (9) are bonded together and reinforced in the thickness direction by aramid fiber, which is an example of thread.
縫合された繊維積層体−は、第１１図に示すように積上
げられた状態で真空加熱炉翰内に設置され、ここで接着
剤ａηや油類が除去（飛ばされる）される。真空加熱炉
（４）から出された繊維積層体α優は。The stitched fiber laminates are placed in a vacuum heating furnace in a stacked state as shown in FIG. 11, where the adhesive aη and oil are removed (blown away). The fiber laminate α Yu is discharged from the vacuum heating furnace (4).
第１２図に示すように結合促進剤（−シラン系処理剤）
Ｑ内に吊り装置０を介してつけられる。この結合促進剤
（至）は、強化繊維（９）ならびに樹脂（後述する）に
結合し易いもので、結果的に強化繊維（９）に対して樹
脂の結合を促進する。As shown in Figure 12, the bonding promoter (-silane treatment agent)
It is attached inside Q via hanging device 0. This bonding promoter (to) is easily bonded to the reinforcing fibers (9) and the resin (described later), and as a result promotes the bonding of the resin to the reinforcing fibers (9).
処理された繊維積層体αりは１両端を修正されたのち、
例えば第１８図に示すように積上げによりプールされる
。After the treated fiber laminate α was corrected at both ends,
For example, as shown in FIG. 18, they are pooled by stacking.
次いで繊維積層体四は、第１４図に示すように両端がパ
ラフィン（イ）に浸けられ、以って第１５図に示すよう
に両端にパラフィン（イ）の層を含浸形成する。Next, both ends of the fiber laminate 4 are dipped in paraffin (A) as shown in FIG. 14, thereby impregnating and forming layers of paraffin (A) at both ends as shown in FIG.
このパラフィン（２）は熱溶融性の保護材料の一例であ
って、他には例えばセルロール樹脂、ポリスチロール樹
脂など樹脂系のような化学的溶解性の保護材料を含浸成
形してもよい。This paraffin (2) is an example of a heat-melting protective material, and it may also be impregnated with a chemically soluble protective material such as a cellulose resin or a polystyrene resin.
次いで繊維Ｗ履体（６）は、第１６図に示すように半割
雌型（２）内に設置され、そしてフィルム（ホ）を介し
て半割雄型（４）が上方から当てかわれる。フィルム（
至）と凹入成形面（１）との間において繊維積層体α９
は。Next, the fiber W shoe body (6) is placed in the half female mold (2) as shown in FIG. 16, and the half male mold (4) is applied from above through the film (E). . film(
) and the recessed molding surface (1), the fiber laminate α9
teeth.
吸引ポンプ弼や吸引Ｗ＠を介して吸気脱気され、またタ
ンク四内の樹脂に）が、供給ポンプ０◇と圧入管（至）
とを介して供給され含浸される。なお樹脂（７）の含浸
としては、第１７図に示すように押圧ローラ曽を使用し
たレイアップ方式も可能である。これらの成形を行ない
、そして樹脂（７）を常温で少し硬化させることにより
、第１８図に示すように両端にパラフィン（イ）を取付
けた半割円筒状の外皮体（ロ）を成形し得、脱型し得る
。Air is taken in and deaerated via the suction pump ＼ and suction W＠, and into the resin in the tank ＠), and the supply pump ◇ and the press-fit pipe (to)
It is supplied and impregnated through. Note that for impregnation with the resin (7), a lay-up method using a pressure roller as shown in FIG. 17 is also possible. By performing these moldings and slightly curing the resin (7) at room temperature, it is possible to mold a half-cylindrical outer shell (b) with paraffin (a) attached to both ends, as shown in Figure 18. , can be demolded.
次いで外皮体（至）を、第１９図に示すように加熱炉（
至）内に入れ、その熱によりパラフィン（イ）を溶融除
去すると共に樹脂（７）を硬化させる。その後、第２０
図に示すようにパラフィン（イ）の除去により両端に現
われた露出強化繊維（９ａ）を溶剤（７）により洗浄し
。Next, the outer skin (to) is heated in a heating furnace (as shown in FIG. 19).
), and the heat melts and removes the paraffin (a) and hardens the resin (7). Then the 20th
As shown in the figure, the exposed reinforcing fibers (9a) that appeared at both ends by removing the paraffin (A) were washed with a solvent (7).
以って第２１図に示すように、きれいな露出強化繊維（
９ａ）とする。Therefore, as shown in Fig. 21, clean exposed reinforcing fibers (
9a).
そして＠２２図に示すように、一対の外皮体（至）の露
出強化繊維（９ａ）どうしを絡ませたのち、この絡み部
■に樹脂（至）を供給し硬化させることにより胴体（至
）を成形し得る。Then, as shown in Figure @22, after the exposed reinforcing fibers (9a) of the pair of outer skin bodies (to) are entwined with each other, resin (to) is supplied to this entwined part (■) and hardened, thereby forming the body (to). Can be molded.
発明の効果
上記構成の本発明によると、凸出成形面とに敷いた接着
剤付着の強化繊維に均一で且つ充分なテンションをかけ
ることができ、さらにかかる状態の繊維積層体をミシン
がけにより肉厚方向を強化して一体化できろ。したがっ
て、その後に樹脂含浸などにより得た外皮体は、樹脂含
有率を低くコントロールできて肉厚を薄くでき、コスト
低下と軽量化を可能にできる。しかも作業能率を向上で
き、多量生産も可能となる。Effects of the Invention According to the present invention having the above configuration, uniform and sufficient tension can be applied to the adhesive-adhered reinforcing fibers laid on the convex molding surface, and the fiber laminate in such a state can be tightened by sewing. Strengthen it in the thickness direction and integrate it. Therefore, the resin content of the outer shell obtained by impregnating with resin or the like can be controlled to be low, and the wall thickness can be made thin, thereby making it possible to reduce cost and weight. Moreover, work efficiency can be improved and mass production possible.
第１図〜第２２図は本発明の一実施例を示し、第１図、
第２図は型の正面図、第８図は強化繊維積層時の正面図
、第４図、第５図は同平面図、第６図、第７図はテンシ
ョン掛は時の正面図、第８図はプール時の正面図、＠９
図はミシン掛は時の正面図、第１０図はミシン掛は後の
要部拡大図、第１１図、第１２図は接着剤除去作業を示
す正面図、第１８図はプール時の正面図、＠１４図は保
護材料成形時の正面図、第１５図は成形後の正面図、第
１６図、第１７図は樹脂含浸作業の夫々別個を示す正面
図、第１８図は含浸後の正面図、第１９図、第２０図は
保護材料除去時の正面図、第２１図は除去後の要部拡大
図、第２２図は結合時の正面図、第２８図〜第２５図は
従来の方式１程図である。
（１）−・・凹入成形面、（２）・・・半割雌型、（３
）・・・凸出成形面、（４）−・半割雄型、（５）・・
・回転テーブル、 （９）−・・強化繊維、（９ａ）・
・・露出強化繊維、συ・・・接着剤、口・・・くし板
、α◆・・・切断装置、に）・・・フィルム、（１つ・
・・吸引管。
−・・・加熱装置、α傷・・・繊維積層体、■・・・ミ
シン装置。1 to 22 show an embodiment of the present invention, and FIG.
Figure 2 is a front view of the mold, Figure 8 is a front view when reinforcing fibers are laminated, Figures 4 and 5 are the same plan views, Figures 6 and 7 are front views when tension is applied, Figure 8 is the front view when swimming, @9
The figure is a front view when the sewing machine is installed, Figure 10 is an enlarged view of the main part after the sewing machine is installed, Figures 11 and 12 are front views showing adhesive removal work, and Figure 18 is a front view when the pool is in use. , @ Figure 14 is a front view during molding of the protective material, Figure 15 is a front view after molding, Figures 16 and 17 are front views showing separate resin impregnation operations, and Figure 18 is a front view after impregnation. Figures 19 and 20 are front views when the protective material is removed, Figure 21 is an enlarged view of the main parts after removal, Figure 22 is a front view when combined, and Figures 28 to 25 are the conventional This is a diagram of method 1. (1) --- Concave molding surface, (2) -- Half-split female mold, (3
)...Convex molding surface, (4)--half male mold, (5)...
・Rotary table, (9)--Reinforced fiber, (9a)-
...exposed reinforcing fiber, συ...adhesive, opening...comb board, α◆...cutting device, ni)...film, (1...
...Suction tube. −...Heating device, α-wound...Fiber laminate, ■...Sewing machine device.
Claims (1)
凸出成形面を上位として設置したのち、この凸出成形面
上に、接着剤付着の強化繊維をテンションをかけながら
積層し、次いで接着剤を硬化させて得た半割円筒状の繊
維積層体をミシン掛けして強化繊維間を結合したのち接
着剤を除去し、次いで繊維積層体の両端に熱溶融性や化
学的溶解性の保護材料を含浸形成し、そして繊維積層体
を雌型内に設置したのち、この繊維積層体に樹脂を含浸
させ、次いで樹脂硬化により半割円筒状の外皮体を成形
したのち、前記保護材料を除去して外皮体の両端に強化
繊維を露出させ、そして一対の外皮体の露出強化繊維ど
うしを絡ませたのち、この絡み部に樹脂を供給し硬化さ
せることにより胴体を成形する飛行機の胴体成形方法。1. Prepare a half-split female mold and a half-split male mold, and then install the half-split male mold with the convex molding surface on top, and then tension the reinforcing fibers attached with adhesive onto this convex molding surface. The fiber laminate is laminated while applying heat, and then the adhesive is cured. The resulting half-split cylindrical fiber laminate is sewn to bond the reinforcing fibers, the adhesive is removed, and then both ends of the fiber laminate are heat-fused. After forming the fiber laminate by impregnating it with a chemically soluble protective material and placing it in a female mold, the fiber laminate is impregnated with resin, and then the resin is cured to form a half-cylindrical outer shell. After that, the protective material is removed to expose the reinforcing fibers at both ends of the outer skin, and the exposed reinforcing fibers of the pair of outer skins are entangled with each other, and a resin is supplied to the entwined portion and hardened to form the fuselage. How to mold an airplane fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60160875A JPS6219440A (en) | 1985-07-19 | 1985-07-19 | Molding of fuselage of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60160875A JPS6219440A (en) | 1985-07-19 | 1985-07-19 | Molding of fuselage of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6219440A true JPS6219440A (en) | 1987-01-28 |
Family
ID=15724257
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60160875A Pending JPS6219440A (en) | 1985-07-19 | 1985-07-19 | Molding of fuselage of airplane |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6219440A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5170967A (en) * | 1990-02-28 | 1992-12-15 | Fuji Jukogyo Kabushiki Kaisa | Aircraft fuselage structure |
| US5223067A (en) * | 1990-02-28 | 1993-06-29 | Fuji Jukogyo Kabushiki Kaisha | Method of fabricating aircraft fuselage structure |
| JP2002060721A (en) * | 2000-08-23 | 2002-02-26 | Honda Motor Co Ltd | Method for bonding non-magnetic member |
| 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 |
| JP2010537889A (en) * | 2007-09-07 | 2010-12-09 | エアバス・オペレーションズ | Structural frame formed from composite material and aircraft fuselage comprising the structural frame |
| JP2016083907A (en) * | 2014-10-29 | 2016-05-19 | トヨタ自動車株式会社 | Method for producing fiber-reinforced resin-molded member, and method for connecting the member |
| WO2020183545A1 (en) * | 2019-03-08 | 2020-09-17 | 株式会社Ｉｈｉエアロスペース | Frp molding system and method |
-
1985
- 1985-07-19 JP JP60160875A patent/JPS6219440A/en active Pending
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5170967A (en) * | 1990-02-28 | 1992-12-15 | Fuji Jukogyo Kabushiki Kaisa | Aircraft fuselage structure |
| US5223067A (en) * | 1990-02-28 | 1993-06-29 | Fuji Jukogyo Kabushiki Kaisha | Method of fabricating aircraft fuselage structure |
| JP2002060721A (en) * | 2000-08-23 | 2002-02-26 | Honda Motor Co Ltd | Method for bonding non-magnetic member |
| JP4577960B2 (en) * | 2000-08-23 | 2010-11-10 | 本田技研工業株式会社 | Non-magnetic member joining method |
| JP2008222221A (en) * | 2004-04-06 | 2008-09-25 | Boeing Co:The | Composite barrel section for aircraft fuselage and other structure, and method and system for manufacturing the barrel section |
| JP2008184156A (en) * | 2004-04-06 | 2008-08-14 | Boeing Co:The | Composite barrel section for aircraft fuselage and other structure, and method and system for manufacturing such barrel section |
| JP2008184155A (en) * | 2004-04-06 | 2008-08-14 | Boeing Co:The | Composite barrel section for aircraft fuselage and other structure, and method and system manufacturing such barrel section |
| 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 |
| JP2010537889A (en) * | 2007-09-07 | 2010-12-09 | エアバス・オペレーションズ | Structural frame formed from composite material and aircraft fuselage comprising the structural frame |
| JP2016083907A (en) * | 2014-10-29 | 2016-05-19 | トヨタ自動車株式会社 | Method for producing fiber-reinforced resin-molded member, and method for connecting the member |
| WO2020183545A1 (en) * | 2019-03-08 | 2020-09-17 | 株式会社Ｉｈｉエアロスペース | Frp molding system and method |
| JP6766268B1 (en) * | 2019-03-08 | 2020-10-07 | 株式会社Ｉｈｉエアロスペース | FRP molding system and method |
| RU2764456C1 (en) * | 2019-03-08 | 2022-01-17 | АйЭйчАй АЭРОСПЕЙС КО., ЛТД. | Frp forming system and method |
| US11826976B2 (en) | 2019-03-08 | 2023-11-28 | Ihi Aerospace Co., Ltd. | FRP molding system and method |
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