JP5144584B2 - 航空機の支柱用のロッドボディを製造するための方法 - Google Patents
航空機の支柱用のロッドボディを製造するための方法 Download PDFInfo
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- JP5144584B2 JP5144584B2 JP2009112093A JP2009112093A JP5144584B2 JP 5144584 B2 JP5144584 B2 JP 5144584B2 JP 2009112093 A JP2009112093 A JP 2009112093A JP 2009112093 A JP2009112093 A JP 2009112093A JP 5144584 B2 JP5144584 B2 JP 5144584B2
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Description
a)45°の位置合わせで、または90°の位置合わせで同じ数の縦糸および横糸を用いた炭素繊維布から製作される少なくとも1つの第1の補強層と、縦糸を0°の位置合わせで横糸より多い数の縦糸を用いた炭素繊維布から製作される少なくとも1つの第2の補強層とを含み、それらが圧力下で人工樹脂によって結合されるプリプレグ層間スクリムを室温またはより高温で第1の事前に圧縮するステップ。
b)中空円筒を製造するために、好ましくは事前に加熱されたマンドレルのまわりに、補強層を含むプリプレグ層間スクリムを少なくとも2回巻き付けるステップ。
c)プリプレグ層間スクリムが上に置かれたマンドレルのまわりに、事前に張力をかけられた熱可塑性織布テープを中間の圧縮のために巻き付けるステップ。
g)表面を改善するために、剥離層および/または穿孔リリース膜層を、最後の、すなわち最外部の補強層上に余分な人工樹脂を除去する目的で巻き付ける。
h)この後に、事前に張力をかけられた熱可塑性織布テープを最後の包装材としてその上に巻き付ける。その後に、
i)温度を上昇させて人工樹脂を硬化させ、一方同時に最終の圧縮を実施する。
2 中間デッキ
3 ロッドボディ
4 ロッド端部
5 マンドレル
6 プリプレグ層間スクリム
7 剥離層
8 リリース膜層
9 織布テープ
10 補強層
11 織布テープ
Claims (4)
- 航空機胴体(1)中に配置される中間デッキ(2)を支持するための、繊維強化材料を含む中空円筒形のロッドボディ(3)を含む支柱であって、前記ロッドボディ(3)の2つの端部が、前記航空機胴体(1)に、または前記中間デッキ(2)に着脱可能に取り付けるための取り付け部として設計される支柱において、前記支柱のロッドボディ(3)を製造するための方法であって、
a)45°の位置合わせで、または90°の位置合わせで同じ数の縦糸および横糸を用いた炭素繊維布から製作される少なくとも1つの第1の補強層(10a)と、縦糸を0°の位置合わせで横糸より多い数の縦糸を用いた炭素繊維布から製作される少なくとも1つの第2の補強層(10b、10c)とを含むプリプレグ層間スクリム(6)を事前に圧縮するステップであって、前記第1および第2の補強層は、室温またはより高い温度において圧力下で人工樹脂によって結合されて繊維強化材料を形成する、事前に圧縮するステップと、
b)中空円筒を製造するために、前記補強層(10a〜10c)を含む前記プリプレグ層間スクリム(6)を少なくとも2回マンドレル(5)のまわりに巻き付けるステップと、
c)前記繊維強化材料を脱気し、そして余分な人工樹脂を除去するために、前記プリプレグ層間スクリム(6)が上に置かれた前記マンドレル(5)のまわりに、事前に張力をかけられた熱可塑性織布テープ(11)を中間の圧縮のために巻き付けるステップとを少なくとも1回実施することを含む、方法。 - 熱による中間の圧縮の後、
d)前記織布テープ(11)は、巻き戻されことによって除去されることを特徴とする、請求項1に記載の方法。 - 補強層(10a〜10c)の層設計を得るために、前記ステップa)からd)を何回か繰り返すことを特徴とする、請求項2に記載の方法。
- 最後のプリプレグ層間スクリム(6’’’)上に、
(f)ガラス繊維布を含む外部補強層(10d)が、前記ロッドボディ(3)の視覚による損傷標識として貼り付けられることを特徴とする、請求項3に記載の方法。
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DE102008022377.8A DE102008022377B4 (de) | 2008-05-06 | 2008-05-06 | Stützstrebe zur Abstützung eines in einem Flugzeugrumpf angeordneten Zwischendecks sowie Verfahren zur Herstellung eines Stangenkörpers für eine solche Stützstrebe |
DE102008022377.8 | 2008-05-06 |
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US (1) | US8328138B2 (ja) |
EP (1) | EP2116356A3 (ja) |
JP (1) | JP5144584B2 (ja) |
DE (1) | DE102008022377B4 (ja) |
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DE102008007838B4 (de) * | 2008-02-07 | 2013-07-18 | Airbus Operations Gmbh | Fußbodensystem für eine Rumpfzelle eines Flugzeugs |
FR2954210B1 (fr) * | 2009-12-18 | 2012-06-15 | Messier Dowty Sa | Procede de fabrication d'une piece en materiau composite obtenue par depot de couches de fibres renforcantes plaquees sur un mandrin |
JP5625397B2 (ja) * | 2010-03-09 | 2014-11-19 | セイコーエプソン株式会社 | 印刷装置 |
RU2434784C1 (ru) * | 2010-05-19 | 2011-11-27 | Открытое Акционерное Общество Центральная Компания Финансово-Промышленной Группы "Российский Авиационный Консорциум" | Фюзеляж летательного аппарата |
JP2013539843A (ja) * | 2010-09-14 | 2013-10-28 | パワー・ツリー・コープ | 複合フライホイール |
DE102010062682A1 (de) * | 2010-12-09 | 2012-06-14 | Robert Bosch Gmbh | Verfahren zum Herstellen eines Faserverbund-Aufnahmekörpers |
US9352538B1 (en) * | 2010-12-29 | 2016-05-31 | Park Electrochemical Corporation | Composite material structure and method of manufacturing same |
GB201120227D0 (en) | 2011-11-23 | 2012-01-04 | Crompton Technology Group Ltd | Composite material component |
US20140054414A1 (en) * | 2012-03-28 | 2014-02-27 | Magellan Aerospace, Winnipeg A Division of Magellan Aerospace Limited | Cable Cutting Device for Aircraft |
US20140265050A1 (en) | 2013-03-14 | 2014-09-18 | Bell Helicopter Textron Inc. | Multi-layer and Multi-fiber Orientation Compression Rolling Process |
FR3033139B1 (fr) * | 2015-02-27 | 2017-03-31 | Faurecia Automotive Composites | Procede de fabrication de profile creux en materiaux composites |
JP6438832B2 (ja) * | 2015-04-22 | 2018-12-19 | Jxtgエネルギー株式会社 | パイプ成形体 |
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FR3059591B1 (fr) * | 2016-12-06 | 2020-06-19 | Airbus Operations | Procede de fabrication d'un profile en matiere composite, comprenant une couche de resine pigmentee |
CN115972614A (zh) * | 2022-11-01 | 2023-04-18 | 上海骐杰碳素材料有限公司 | 一种宽幅板材预应力压制工艺 |
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US20090277995A1 (en) | 2009-11-12 |
EP2116356A3 (en) | 2016-04-27 |
US8328138B2 (en) | 2012-12-11 |
EP2116356A2 (en) | 2009-11-11 |
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JP2009269603A (ja) | 2009-11-19 |
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