JP2011240925A - 漸進的な剛性を有する複合構造部材 - Google Patents
漸進的な剛性を有する複合構造部材 Download PDFInfo
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- JP2011240925A JP2011240925A JP2011110718A JP2011110718A JP2011240925A JP 2011240925 A JP2011240925 A JP 2011240925A JP 2011110718 A JP2011110718 A JP 2011110718A JP 2011110718 A JP2011110718 A JP 2011110718A JP 2011240925 A JP2011240925 A JP 2011240925A
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- 239000002131 composite material Substances 0.000 title claims abstract description 23
- 230000000750 progressive effect Effects 0.000 title description 2
- 208000002740 Muscle Rigidity Diseases 0.000 title 1
- 239000000835 fiber Substances 0.000 claims abstract description 53
- 230000002787 reinforcement Effects 0.000 claims abstract description 16
- 238000009826 distribution Methods 0.000 claims abstract description 4
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 4
- 230000007423 decrease Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 230000004907 flux Effects 0.000 abstract description 2
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 229920001187 thermosetting polymer Polymers 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229920005992 thermoplastic resin Polymers 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- 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
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/205—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration
- B29C70/207—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration arranged in parallel planes of fibres crossing at substantial angles
-
- 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
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
- Y10T428/24124—Fibers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Aviation & Aerospace Engineering (AREA)
- Textile Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
【解決手段】 本発明は、繊維強化による複合構造部材および航空機用の主翼ボックスの製造におけるその応用に関する。より詳しくは、前記部材の長手方向(2)に関連して0度、90度、および+/−θを含む方向に配向される複数のレイヤーから成る繊維強化による複合構造部材(230)に関するものであり、これらの配向の1つにおけるレイヤーの相対的比率は、横軸(3)に沿った機械的応力の規定の配分に従って部材の剛性を空間的に調整するように、前記部材の横方向(3)に沿って可変である。
このように、部材の剛性は、前記部材の全容積にわたってフォース・フラックスを分散するように、応力システムに局部的に適合している。
【選択図】図10
Description
‐補強上面パネルおよび補強下面パネルと、
‐上記の実施形態のいずれか1つにより、ボックスの上面パネルと下面パネルの間を横断して延びる複合部材でできている翼桁であって、翼桁の長手方向が上面パネルおよび下面パネルの補強材とほぼ平行である翼桁と、を備え、
‐前記翼桁は上面パネルおよび下面パネルに完全に接続している、
2 長手方向(軸)
3 横方向(軸)
10 輪郭
11 ストリップまたはバンド
11´ 一方向性バンド
12 ストリップまたは(一方向性)バンド
13 ストリップまたは(一方向性)バンド
14 ストリップまたは(一方向性)バンド
110 マルチ軸バンド
120 バンド
140 マルチ軸バンド
150 マルチ軸バンド
200 主翼ボックス
210 (補強)上面パネル
211 長手方向の補強材
220 (補強)下面パネル
221 長手方向の補強材
230 翼桁(複合構造部材)
231 外側(端)領域
232 (中間)領域
233 (中間)領域
234 中央ゾーン(領域)
235 (中間)領域
236 (中間)領域
237 外側(端)領域
900 航空機
930 着陸装置用ハウジング
2100 圧縮応力
2200 引張応力
2300 剪断応力
Claims (7)
- 部材の長手方向(2)に関連して0度、90度、および+/−θを含む方向に配向される複数のレイヤーから成る繊維強化による複合構造部材(1、230)であって、これらの配向の1つにおけるレイヤーの相対的比率が、横軸に沿った機械的応力の規定の配分に従って該部材の剛性を空間的に調整するように、前記部材の横方向(3)に沿って可変であり、ここにおいて、+/−θ方向に配向される繊維の少なくとも1つのレイヤーが、該部材の一方からその全表面にわたりもう一方まで延びる連続繊維から形成され、そして前記部材の厚さが一定である複合部材。
- θ=45度である請求項1に記載の複合部材。
- 航空機の主翼ボックス(200)であって、すなわち、
‐補強上面パネル(210)および補強下面パネル(220)と、
‐前記ボックスの前記上面パネル(210)と前記下面パネル(220)の間を横断して延びる、請求項1に記載の複合部材でできている翼桁(230)であって、前記翼桁の長手方向(2)が前記上面パネル(210)および前記下面パネル(220)の補強材(211、221)とほぼ平行である翼桁(230)と、を備え、
‐前記翼桁(230)は前記上面パネル(210)および前記下面パネル(220)に完全に接続している主翼ボックス(200)。 - 前記翼桁(230)が、前記上面パネル(210)および前記下面パネル(220)との接続部から始まる前記翼桁の全幅の4分の1未満の幅を有する、端部として公知の領域(231、237)に0度で配向した繊維を40%〜50%の比率で含む請求項3に記載の主翼ボックス(200)。
- 前記翼桁(230)が、前記2つの端領域(231、237)の間に、前記端領域(231、237)から前記翼桁の前記長手方向中心軸(3)に向かって、0度の繊維の比率が1つの領域から次の領域へと減少する中間領域(232、233、236、235)を含む請求項4に記載の主翼ボックス(200)。
- 前記翼桁(230)が、前記翼桁の長手方向中心軸(3)のいずれの側にも延びて、配向0度、90度、および+/−θにおいて同じ比率の繊維から成る、中心領域として公知の領域(234)を含む請求項5に記載の主翼ボックス。
- 請求項6に記載の主翼ボックス(200)を備える航空機(900)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1053922A FR2960179A1 (fr) | 2010-05-20 | 2010-05-20 | Piece structurale composite a rigidite evolutive |
FR1053922 | 2010-05-20 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2011240925A true JP2011240925A (ja) | 2011-12-01 |
JP2011240925A5 JP2011240925A5 (ja) | 2014-06-26 |
Family
ID=43334738
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2011110718A Pending JP2011240925A (ja) | 2010-05-20 | 2011-05-17 | 漸進的な剛性を有する複合構造部材 |
Country Status (4)
Country | Link |
---|---|
US (1) | US8708279B2 (ja) |
EP (1) | EP2388130B1 (ja) |
JP (1) | JP2011240925A (ja) |
FR (1) | FR2960179A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2017200753A (ja) * | 2016-02-08 | 2017-11-09 | ザ・ボーイング・カンパニーThe Boeing Company | 多層複合部品のためのプライ最適化実行可能性分析 |
JP2019038517A (ja) * | 2017-08-23 | 2019-03-14 | ザ・ボーイング・カンパニーThe Boeing Company | 共硬化した桁および縦通材の中央ウイングボックス |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BR112012001714B1 (pt) * | 2009-10-08 | 2020-04-07 | Mitsubishi Heavy Ind Ltd | asa principal de aeronave e fuselagem de aeronave |
ES2404946B1 (es) * | 2011-10-21 | 2014-09-02 | Airbus Operations S.L. | Fuselaje de aeronave resistente al impacto y tolerante al daño mejorado |
US9527575B2 (en) * | 2012-11-26 | 2016-12-27 | The Boeing Company | Multi-box wing spar and skin |
AU2014200142B2 (en) * | 2013-01-26 | 2017-02-23 | The Boeing Company | Box structures for carrying loads and methods of making the same |
Citations (6)
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US4606961A (en) * | 1984-10-09 | 1986-08-19 | The Boeing Company | Discretely stiffened composite panel |
JP2002531299A (ja) * | 1998-12-04 | 2002-09-24 | ビ−エイイ− システムズ パブリック リミテッド カンパニ− | 複合積層物 |
JP2002302097A (ja) * | 2001-04-05 | 2002-10-15 | Fuji Heavy Ind Ltd | 複合材翼およびその製造方法 |
JP2003082117A (ja) * | 2001-07-04 | 2003-03-19 | Toray Ind Inc | 炭素繊維強化基材、それからなるプリフォームおよび複合材料 |
US20050163975A1 (en) * | 2004-01-28 | 2005-07-28 | The Boeing Company | Composite stacking sequence optimization for multi-zoned composites |
JP2011518700A (ja) * | 2008-04-28 | 2011-06-30 | エアバス オペレーションズ リミテッド | 複合パネルの設計方法 |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6513757B1 (en) * | 1999-07-19 | 2003-02-04 | Fuji Jukogyo Kabushiki Kaisha | Wing of composite material and method of fabricating the same |
US20030186038A1 (en) * | 1999-11-18 | 2003-10-02 | Ashton Larry J. | Multi orientation composite material impregnated with non-liquid resin |
US7115323B2 (en) * | 2003-08-28 | 2006-10-03 | The Boeing Company | Titanium foil ply replacement in layup of composite skin |
US20060222837A1 (en) * | 2005-03-31 | 2006-10-05 | The Boeing Company | Multi-axial laminate composite structures and methods of forming the same |
EP1840775A1 (en) | 2006-03-31 | 2007-10-03 | Airbus Espana, S.L. | Computer-aided method of obtaining a ply model of composite component |
US7575194B2 (en) * | 2006-11-30 | 2009-08-18 | The Boeing Company | Apparatuses and methods for joining composite members and other structural members in aircraft wing boxes and other structures |
-
2010
- 2010-05-20 FR FR1053922A patent/FR2960179A1/fr not_active Withdrawn
-
2011
- 2011-05-16 EP EP11166265.6A patent/EP2388130B1/fr not_active Not-in-force
- 2011-05-17 JP JP2011110718A patent/JP2011240925A/ja active Pending
- 2011-05-17 US US13/109,448 patent/US8708279B2/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4606961A (en) * | 1984-10-09 | 1986-08-19 | The Boeing Company | Discretely stiffened composite panel |
JP2002531299A (ja) * | 1998-12-04 | 2002-09-24 | ビ−エイイ− システムズ パブリック リミテッド カンパニ− | 複合積層物 |
JP2002302097A (ja) * | 2001-04-05 | 2002-10-15 | Fuji Heavy Ind Ltd | 複合材翼およびその製造方法 |
JP2003082117A (ja) * | 2001-07-04 | 2003-03-19 | Toray Ind Inc | 炭素繊維強化基材、それからなるプリフォームおよび複合材料 |
US20050163975A1 (en) * | 2004-01-28 | 2005-07-28 | The Boeing Company | Composite stacking sequence optimization for multi-zoned composites |
JP2011518700A (ja) * | 2008-04-28 | 2011-06-30 | エアバス オペレーションズ リミテッド | 複合パネルの設計方法 |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2017200753A (ja) * | 2016-02-08 | 2017-11-09 | ザ・ボーイング・カンパニーThe Boeing Company | 多層複合部品のためのプライ最適化実行可能性分析 |
JP2019038517A (ja) * | 2017-08-23 | 2019-03-14 | ザ・ボーイング・カンパニーThe Boeing Company | 共硬化した桁および縦通材の中央ウイングボックス |
JP7242197B2 (ja) | 2017-08-23 | 2023-03-20 | ザ・ボーイング・カンパニー | 共硬化した桁および縦通材の中央ウイングボックス |
Also Published As
Publication number | Publication date |
---|---|
US20110299993A1 (en) | 2011-12-08 |
US8708279B2 (en) | 2014-04-29 |
EP2388130B1 (fr) | 2015-07-01 |
EP2388130A1 (fr) | 2011-11-23 |
FR2960179A1 (fr) | 2011-11-25 |
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