JP5463414B2 - 構造要素及び構造要素を製造するための方法 - Google Patents
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/887—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced locally reinforced, e.g. by fillers
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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
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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
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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
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Description
104 補強経路
106 補強帯
200 リング構造
202 下側シェル
203 航空機の長手方向
204 湾曲の方向
206 胴体バレル部
211 帯部分
212 帯部分
213 帯部分
300 管紐
302 挿入コア
311 要素の半分
312 要素の半分
401 フェイシング
402 フェイシング
403 ストラット
406 アンカ
408 コア構成要素
500 追加ストラット
502 追加ストラット
600 ウィンドウ
500 垂直ストラット
502 対角ストラット
700 サポート
702 更なるフェイシング
704 ドア
Claims (14)
- 要素領域にわたって拡がるコア構成要素(408)と、
コア構成要素(408)の対向する境界面に、要素領域にわたって拡がって構成される第1(401)及び第2(402)の表面板と、
コア構成要素(408)内のインサート(300,302)によって形成される補強帯(106)であって、インサートが、表面板(401,402)間の補強経路(104)に沿って拡がり、前記補強経路が要素領域に対して略平行に拡がり、かつ、インサートが、インサートコア(300)と、インサートコア(302)を囲む管状繊維紐(300)とを備える、補強帯と、
要素領域にわたって分配される複数のストラット(403,500,502)であって、第1(401)及び第2(402)の表面板を、コア構成要素(408)を介して互いに接続するストラットと、を備え、
少なくとも1つのストラット(500,502)が、少なくとも1つの表面板(401,402)及び管状繊維紐(300)を貫通する航空機又は宇宙機のための構造要素(102)。 - コア構成要素(408)及び/又はインサートコア(302)は、発泡材料を備えることを特徴とする請求項1に記載の構造要素(102)。
- 各ストラット(403)は、樹脂が含浸される繊維束を備えることを特徴とする請求項1又は請求項2に記載の構造要素(102)。
- 少なくとも1つのストラット(500,502)は、インサート(300,302)を貫通することを特徴とする請求項1から3のいずれか1項に記載の構造要素(102)。
- 少なくとも1つのストラット(500,502)は、要素領域に対して対角線状に拡がることを特徴とする請求項4に記載の構造要素(102)。
- 表面板(401,402)、管状繊維紐(300)及びストラット(403,500,502)は共に樹脂が含浸されていることを特徴とする請求項1から5のいずれか1項に記載の構造要素(102)。
- 要素領域は、少なくとも1つの湾曲方向(204)における湾曲部を備え、補強帯(106)は、湾曲方向(204)において螺旋状で対角線状に拡がることを特徴とする請求項1から6のいずれか1項に記載の構造要素(102)。
- 角度(α)で互いに交差して拡がる第1(106)及び第2(106’)の補強帯によって特徴づけられる請求項1から7のいずれか1項に記載の構造要素(102)。
- 補強帯(106)は、実質的に補強経路(104)の方向において、第1(211)及び第3(213)の部分内で延び、第1(211)と第3(213)の部分との間に設けられる第2の部分(212)内に、2つの環状に接続される分岐部内への分割体(200)を備えることを特徴とする請求項1から8のいずれか1項に記載の構造要素(102)。
- 請求項1から9のいずれか1項に記載の構造要素を備える航空機又は宇宙機のための胴体シェル(206)。
- 請求項10に記載の胴体シェル(206)又は請求項1から9のいずれか1項に記載の構造要素(102)を備える航空機又は宇宙機。
- 以下のステップ、
要素領域にわたって拡がり、発泡材料を備えるコア構成要素(408)の準備と、
コア構成要素(408)の2つの対向する境界面上への第1(401)及び第2(402)の表面板の配置であって、表面板が要素領域にわたって拡がる、表面板の配置と、
コア構成要素(408)内で、インサート(300,302)によって形成される補強帯(106)の挿入であって、インサートが、表面板(401,402)間の補強経路(104)に沿って拡がり、前記補強経路が要素領域に対して略平行に拡がり、インサートが、インサートコア(300)及びインサートコア(302)を囲む管状繊維紐(300)を備える、補強帯(106)の挿入と、
要素領域にわたって分配される複数のストラット(406,500,502)の形成であって、少なくとも1つのストラット(500,502)が少なくとも1つの表面板(401,402)及び管状繊維紐(300)を貫通するように、ストラットが、第1(401)及び第2(402)の表面板を、コア構成要素(408)を介して互いに接続する、複数のストラットの形成と、
を備える航空機又は宇宙機のための構造要素(102)を製造するための方法。 - 表面板(401,402)、管状繊維紐(302)及びストラット(403,500,502)の樹脂含浸結束によって特徴づけられる請求項12に記載の方法。
- 発泡材料の少なくとも部分的な除去のステップによって特徴づけられる請求項12又は13に記載の方法。
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009026458.2 | 2009-05-25 | ||
DE200910026458 DE102009026458A1 (de) | 2009-05-25 | 2009-05-25 | Strukturbauteil und Herstellungsverfahren für ein Strukturbauteil |
US18104509P | 2009-05-26 | 2009-05-26 | |
US61/181,045 | 2009-05-26 | ||
PCT/EP2010/056860 WO2010136362A1 (de) | 2009-05-25 | 2010-05-19 | Strukturbauteil und herstellungsverfahren für ein strukturbauteil |
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JP2012528028A JP2012528028A (ja) | 2012-11-12 |
JP5463414B2 true JP5463414B2 (ja) | 2014-04-09 |
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US (1) | US8356451B2 (ja) |
EP (1) | EP2435237B1 (ja) |
JP (1) | JP5463414B2 (ja) |
CN (1) | CN102481732B (ja) |
BR (1) | BRPI1012025A2 (ja) |
CA (1) | CA2763113C (ja) |
DE (1) | DE102009026458A1 (ja) |
RU (1) | RU2519111C2 (ja) |
WO (1) | WO2010136362A1 (ja) |
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DE102011113806B4 (de) | 2011-09-20 | 2014-09-25 | Airbus Operations Gmbh | Rumpfsegment sowie Verfahren zur Herstellung eines Rumpfsegments |
DE102012016781A1 (de) | 2012-08-23 | 2014-02-27 | Daimler Ag | Faserverbundkunststoff-Strukturbauteil mit einer geschlossenen Schale und Verfahren zu dessen Herstellung |
EP2730497B1 (en) * | 2012-11-13 | 2017-04-19 | Airbus Operations GmbH | Aircraft window arrangement |
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DE102013018158A1 (de) * | 2013-12-05 | 2015-06-11 | Airbus Defence and Space GmbH | Verfahren zur Herstellung von verstärkten Materialien und Material erhältlich aus diesem Verfahren |
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FR2836690B1 (fr) * | 2002-03-04 | 2004-08-27 | Eads Launch Vehicles | Procede pour la realisation d'une piece monolithique composite thermostructurale a double paroi et piece obtenue |
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US8512853B2 (en) * | 2007-07-31 | 2013-08-20 | The Boeing Company | Composite structure having reinforced core |
US20090078820A1 (en) * | 2007-09-26 | 2009-03-26 | The Boeing Company | Wing-to-body fairing |
US8127450B2 (en) * | 2008-01-31 | 2012-03-06 | Airbus Operations Gmbh | Method for producing a sandwich construction, in particular a sandwich construction for the aeronautical and aerospace fields |
DE102009026458A1 (de) * | 2009-05-25 | 2010-12-09 | Airbus Operations Gmbh | Strukturbauteil und Herstellungsverfahren für ein Strukturbauteil |
-
2009
- 2009-05-25 DE DE200910026458 patent/DE102009026458A1/de not_active Withdrawn
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2010
- 2010-05-19 CA CA2763113A patent/CA2763113C/en not_active Expired - Fee Related
- 2010-05-19 JP JP2012511273A patent/JP5463414B2/ja active Active
- 2010-05-19 WO PCT/EP2010/056860 patent/WO2010136362A1/de active Application Filing
- 2010-05-19 RU RU2011147139/05A patent/RU2519111C2/ru active
- 2010-05-19 EP EP10720604.7A patent/EP2435237B1/de active Active
- 2010-05-19 CN CN201080022906.3A patent/CN102481732B/zh active Active
- 2010-05-19 BR BRPI1012025A patent/BRPI1012025A2/pt not_active IP Right Cessation
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2011
- 2011-11-22 US US13/302,670 patent/US8356451B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
RU2519111C2 (ru) | 2014-06-10 |
US8356451B2 (en) | 2013-01-22 |
EP2435237B1 (de) | 2015-08-19 |
US20120135180A1 (en) | 2012-05-31 |
BRPI1012025A2 (pt) | 2017-06-27 |
CA2763113C (en) | 2017-04-04 |
RU2011147139A (ru) | 2013-05-27 |
JP2012528028A (ja) | 2012-11-12 |
EP2435237A1 (de) | 2012-04-04 |
CA2763113A1 (en) | 2010-12-02 |
CN102481732B (zh) | 2014-11-12 |
CN102481732A (zh) | 2012-05-30 |
WO2010136362A1 (de) | 2010-12-02 |
DE102009026458A1 (de) | 2010-12-09 |
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