JP2009500188A - ほぼシェル形の構成要素を製造する方法 - Google Patents
ほぼシェル形の構成要素を製造する方法 Download PDFInfo
- Publication number
- JP2009500188A JP2009500188A JP2008518742A JP2008518742A JP2009500188A JP 2009500188 A JP2009500188 A JP 2009500188A JP 2008518742 A JP2008518742 A JP 2008518742A JP 2008518742 A JP2008518742 A JP 2008518742A JP 2009500188 A JP2009500188 A JP 2009500188A
- Authority
- JP
- Japan
- Prior art keywords
- shell
- doubler
- reinforcing element
- reinforcing
- angle bracket
- 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
Images
Classifications
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
-
- 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
- B29L2031/3082—Fuselages
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
Description
・1つの硬化サイクルでの複雑かつ大型のシェル形構成要素の製造。
・シェル形構成要素の良好な機械的性質。
・硬化されたダブラは、非常に狭い許容誤差内に製造および/または機械加工され得、シェル外板または外板積層物の厚さ許容誤差に対して、より大きな材料厚さを有する領域の厚さ許容誤差を低減する。
図1〜図3について述べる。
図面は、縦通材4として形成された補強要素を備えるシェル形構成要素の製造を示す。強化区域3には、ダブラ1として構成された厚い部分(thickening)が形成されており、負荷の導入を改善する。この場合、プリプレグ材として知られる半完成品が用いられる。プリプレグ材は、硬化性エポキシ樹脂を含浸させた炭素繊維強化シート状構造体である。これに代わって、プリプレグ材に硬化性ポリエステルまたはBMI樹脂系を用いることも可能である。
次に、次の工程で、L形状鋼として既に予め圧縮されていてもよく、実質的に接続アングルブラケット6または連結アングルブラケットとして機能する未硬化の積層物が、縦通材4の基部およびダブラ1の上に敷設される。このL形状鋼は既に硬化している縦通材4のウェブによって支持される。
Claims (5)
- 実質的に炭素繊維強化合成材料から、特に航空機の胴体シェル、翼シェル、垂直安定板シェルおよび水平安定板シェルのいずれかなどの、少なくとも1つの局所強化区域および少なくとも1つの補強要素を有するほぼシェル形の構成要素を製造する方法であって、該方法は、
既に硬化している少なくとも1つのダブラ(1)を大部分が硬化したシェル外板(2)上に配置して、局所強化区域(3)を形成する工程と、
既に硬化している少なくとも1つの補強要素を適用する工程と、
少なくとも、少なくとも1つのダブラ(1)の領域に位置する少なくとも1つの補強要素に対して、少なくとも1つの大部分が硬化した接続アングルブラケット(6)を配置する工程と、
シェル外板(2)、少なくとも1つのダブラ(1)、少なくとも1つの補強要素、および少なくとも1つの接続アングルブラケット(6)によって構成される構造体を真空バッグ内に挿入する工程であって、前記真空バッグは硬化のためにオートクレーブ内に移動されるものである、前記挿入する工程と、
シェル外板(2)および接続アングルブラケット(6)をオートクレーブ内において120℃〜180℃の温度および10バール以内の圧力で硬化させて、完成したシェル形構成要素を生成する工程と
を有することを特徴とする方法。 - 少なくとも1つの補強要素は、少なくとも1つのダブラ(1)の領域において、シェル外板に適用される前に、少なくとも1つのダブラの輪郭に適合させられることを特徴とする、請求項1に記載の方法。
- 補強要素は、強化用形状鋼、特にT形状鋼を用いて形成されることを特徴とする、請求項1または2に記載の方法。
- シェル外板(2)、少なくとも1つの補強要素、少なくとも1つのダブラ(1)、および少なくとも1つの接続アングルブラケット(6)のうちの少なくともいずれかは、実質的に、繊維強化合成材料、特に硬化性エポキシ樹脂を予め含浸させた炭素繊維強化材を有する材料を用いて形成されることを特徴とする、請求項1乃至3のいずれか1項に記載の方法。
- 請求項1乃至4のいずれか1項に従って製造された、特に航空機の胴体シェル、翼シェル、垂直安定板シェルおよび水平安定板シェルのいずれかのような、少なくとも1つの局所強化区域および少なくとも1つの補強要素を有するシェル形構成要素。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005030939A DE102005030939A1 (de) | 2005-06-30 | 2005-06-30 | Verfahren zur Herstellung eines im Wesentlichen schalenförmigen Bauteils |
PCT/EP2006/006384 WO2007003372A1 (en) | 2005-06-30 | 2006-06-30 | Process for producing a substantially shell-shaped component |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2009500188A true JP2009500188A (ja) | 2009-01-08 |
JP2009500188A5 JP2009500188A5 (ja) | 2012-01-05 |
Family
ID=36950577
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008518742A Pending JP2009500188A (ja) | 2005-06-30 | 2006-06-30 | ほぼシェル形の構成要素を製造する方法 |
Country Status (9)
Country | Link |
---|---|
US (1) | US8580170B2 (ja) |
EP (1) | EP1899149B1 (ja) |
JP (1) | JP2009500188A (ja) |
CN (1) | CN101203374B (ja) |
BR (1) | BRPI0613477A2 (ja) |
CA (1) | CA2611248A1 (ja) |
DE (2) | DE102005030939A1 (ja) |
RU (1) | RU2404059C2 (ja) |
WO (1) | WO2007003372A1 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2016534295A (ja) * | 2013-08-09 | 2016-11-04 | ザ・ボーイング・カンパニーThe Boeing Company | 補強複合材パネル |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101391488B (zh) * | 2008-08-22 | 2010-06-09 | 成都飞机工业(集团)有限责任公司 | 非平板复合材料制件的固化成型方法与成型模 |
CN101870172B (zh) * | 2010-06-09 | 2012-10-10 | 哈尔滨工业大学 | 飞机及航空器的碳纤维复合材料壳体的制备模具及其成形方法 |
CN101913250A (zh) * | 2010-08-17 | 2010-12-15 | 沈阳飞机工业(集团)有限公司 | 方向舵壁板成型工艺 |
EP3088152B1 (en) * | 2015-04-30 | 2020-04-15 | Airbus Operations, S.L. | Method for manufacturing composite parts and form |
CN108995264B (zh) * | 2018-05-28 | 2021-02-09 | 广西玉林华飞网络科技有限公司 | 一种epo无人机外壳加固方法及加固结构 |
CN108749028B (zh) * | 2018-05-29 | 2019-10-08 | 沈阳飞机工业(集团)有限公司 | 一种常温固化耐高温辅助工装材料体系及其制造方法 |
US11446884B2 (en) | 2018-10-29 | 2022-09-20 | Airbus Operations Gmbh | Process for producing a component which is two-dimensional in regions from a fibre composite material |
CN110524915A (zh) * | 2019-09-05 | 2019-12-03 | 航天特种材料及工艺技术研究所 | 一种套接成型工装和套接成型方法 |
GB2615755A (en) * | 2022-02-15 | 2023-08-23 | Airbus Operations Ltd | Fuel tank stringer with flow passage |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4813202A (en) * | 1987-05-22 | 1989-03-21 | Grumman Aerospace Corporation | Structural members connected by interdigitating portions |
JP2001310798A (ja) * | 2000-04-27 | 2001-11-06 | Honda Motor Co Ltd | 繊維強化複合材からなる胴体構造体の製造方法、及びそれにより製造される胴体構造体 |
US20050112397A1 (en) * | 2003-07-24 | 2005-05-26 | Rolfe Jonathan L. | Assembled non-random foams |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1997718A (en) * | 1934-08-03 | 1935-04-16 | Claff Clarence Lloyd | Folding box and method of making the same |
GB884920A (en) * | 1957-08-01 | 1961-12-20 | Robert Frank Geiger | Apparatus and method for metal adhesive bonding |
US4331723A (en) * | 1980-11-05 | 1982-05-25 | The Boeing Company | Advanced composite |
CN1042692A (zh) * | 1988-11-14 | 1990-06-06 | 通用电气公司 | 反转的飞机螺旋桨叶 |
JPH0310798A (ja) | 1989-06-05 | 1991-01-18 | Nec Corp | 切断かしめ機構 |
JPH058316A (ja) | 1991-07-05 | 1993-01-19 | Mitsubishi Heavy Ind Ltd | 複合材製構造体の製造方法 |
US5242523A (en) * | 1992-05-14 | 1993-09-07 | The Boeing Company | Caul and method for bonding and curing intricate composite structures |
FR2699499B1 (fr) | 1992-12-23 | 1995-03-10 | Eurocopter France | Pale en composite thermoplastique, notamment pour rotor arrière caréné d'hélicoptère, et son procédé de fabrication avec étape d'injection. |
US6562436B2 (en) * | 2000-02-25 | 2003-05-13 | The Boeing Company | Laminated composite radius filler |
US6374570B1 (en) * | 2000-08-25 | 2002-04-23 | Lockheed Martin Corporation | Apparatus and method for joining dissimilar materials to form a structural support member |
RU2230406C2 (ru) | 2001-08-27 | 2004-06-10 | Симонов Владимир Федорович | Размеростабильное интегральное изделие из композиционных материалов, способ его изготовления и форма для осуществления способа |
US6964723B2 (en) * | 2002-10-04 | 2005-11-15 | The Boeing Company | Method for applying pressure to composite laminate areas masked by secondary features |
US7052573B2 (en) * | 2003-11-21 | 2006-05-30 | The Boeing Company | Method to eliminate undulations in a composite panel |
-
2005
- 2005-06-30 DE DE102005030939A patent/DE102005030939A1/de not_active Ceased
-
2006
- 2006-06-30 BR BRPI0613477-7A patent/BRPI0613477A2/pt not_active IP Right Cessation
- 2006-06-30 DE DE602006005052T patent/DE602006005052D1/de active Active
- 2006-06-30 RU RU2007148546/05A patent/RU2404059C2/ru not_active IP Right Cessation
- 2006-06-30 CA CA002611248A patent/CA2611248A1/en not_active Abandoned
- 2006-06-30 JP JP2008518742A patent/JP2009500188A/ja active Pending
- 2006-06-30 US US11/922,940 patent/US8580170B2/en active Active
- 2006-06-30 CN CN2006800217411A patent/CN101203374B/zh not_active Expired - Fee Related
- 2006-06-30 WO PCT/EP2006/006384 patent/WO2007003372A1/en active Application Filing
- 2006-06-30 EP EP06762316A patent/EP1899149B1/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4813202A (en) * | 1987-05-22 | 1989-03-21 | Grumman Aerospace Corporation | Structural members connected by interdigitating portions |
JP2001310798A (ja) * | 2000-04-27 | 2001-11-06 | Honda Motor Co Ltd | 繊維強化複合材からなる胴体構造体の製造方法、及びそれにより製造される胴体構造体 |
US20050112397A1 (en) * | 2003-07-24 | 2005-05-26 | Rolfe Jonathan L. | Assembled non-random foams |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2016534295A (ja) * | 2013-08-09 | 2016-11-04 | ザ・ボーイング・カンパニーThe Boeing Company | 補強複合材パネル |
Also Published As
Publication number | Publication date |
---|---|
CN101203374B (zh) | 2011-02-02 |
US20090115088A1 (en) | 2009-05-07 |
RU2007148546A (ru) | 2009-08-10 |
BRPI0613477A2 (pt) | 2011-01-11 |
WO2007003372A1 (en) | 2007-01-11 |
DE602006005052D1 (de) | 2009-03-19 |
CN101203374A (zh) | 2008-06-18 |
RU2404059C2 (ru) | 2010-11-20 |
EP1899149B1 (en) | 2009-01-28 |
DE102005030939A1 (de) | 2007-01-04 |
EP1899149A1 (en) | 2008-03-19 |
US8580170B2 (en) | 2013-11-12 |
CA2611248A1 (en) | 2007-01-11 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP2009500188A (ja) | ほぼシェル形の構成要素を製造する方法 | |
US10737760B2 (en) | Multi-box wing spar and skin | |
EP2129510B1 (en) | Method for producing a structural component | |
US8197625B2 (en) | Process of manufacturing composite structures with embedded precured tools | |
EP1800842B1 (en) | A method of manufacturing an elongate structural element configured for stiffening a shell structure, and a method for manufacturing a rigid shell structure integrated with at least one elongate stiffening element | |
US8263205B2 (en) | Method of molding complex composite parts using pre-plied multi-directional continuous fiber laminate | |
US9669581B2 (en) | Method for manufacturing an aeronautical torsion box, torsion box and tool for manufacturing an aeronautical torsion box | |
US20130309443A1 (en) | Reinforced Stiffeners and Method for Making the Same | |
US10766621B2 (en) | Method for manufacturing an overhead storage compartment for an aircraft cabin | |
US20140248143A1 (en) | Monolithic fan cowl of an aircraft engine and a manufacturing method thereof | |
US8623160B2 (en) | Method of repairing an aircraft structure component | |
US20200384721A1 (en) | Composite Panel Sandwich Structures with Integrated Joints |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20090619 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20110708 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20110712 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20111007 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20111017 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20111109 |
|
A524 | Written submission of copy of amendment under section 19 (pct) |
Free format text: JAPANESE INTERMEDIATE CODE: A524 Effective date: 20111109 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20120203 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20120703 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20121128 |