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DE60211185D1 - Verbundwerkstoffstruktur - Google Patents

Verbundwerkstoffstruktur

Info

Publication number
DE60211185D1
DE60211185D1 DE60211185T DE60211185T DE60211185D1 DE 60211185 D1 DE60211185 D1 DE 60211185D1 DE 60211185 T DE60211185 T DE 60211185T DE 60211185 T DE60211185 T DE 60211185T DE 60211185 D1 DE60211185 D1 DE 60211185D1
Authority
DE
Germany
Prior art keywords
laminated
portions
rib
regions
corner portion
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.)
Expired - Lifetime
Application number
DE60211185T
Other languages
English (en)
Other versions
DE60211185T2 (de
Inventor
Kays Clement Kairouz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations Ltd
Original Assignee
BAE Systems PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by BAE Systems PLC filed Critical BAE Systems PLC
Publication of DE60211185D1 publication Critical patent/DE60211185D1/de
Application granted granted Critical
Publication of DE60211185T2 publication Critical patent/DE60211185T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
  • Glass Compositions (AREA)
DE60211185T 2001-09-13 2002-09-06 Verbundwerkstoffstruktur Expired - Lifetime DE60211185T2 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB0122050 2001-09-13
GBGB0122050.8A GB0122050D0 (en) 2001-09-13 2001-09-13 Composite material structure
PCT/GB2002/004046 WO2003022677A1 (en) 2001-09-13 2002-09-06 Composite material structure

Publications (2)

Publication Number Publication Date
DE60211185D1 true DE60211185D1 (de) 2006-06-08
DE60211185T2 DE60211185T2 (de) 2006-09-07

Family

ID=9921965

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60211185T Expired - Lifetime DE60211185T2 (de) 2001-09-13 2002-09-06 Verbundwerkstoffstruktur

Country Status (9)

Country Link
US (1) US7380753B2 (de)
EP (1) EP1425215B1 (de)
AT (1) ATE325034T1 (de)
CA (1) CA2459167C (de)
DE (1) DE60211185T2 (de)
ES (1) ES2258645T3 (de)
GB (1) GB0122050D0 (de)
NO (1) NO322021B1 (de)
WO (1) WO2003022677A1 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0219451D0 (en) * 2002-08-21 2002-09-25 Bae Systems Plc A bracket
EP1495859B1 (de) * 2003-07-08 2008-09-03 Airbus Deutschland GmbH Leichtbaustruktur
EP1666354B1 (de) * 2004-12-01 2010-09-29 Airbus Operations GmbH Strukturbauteil, Verfahren zum Herstellen eines Strukturbauteils und Verwendung eines Strukturbauteils für eine Flugzeugschale
GB0525691D0 (en) * 2005-12-16 2006-01-25 Airbus Uk Ltd A fastener assembly
US7721995B2 (en) * 2006-12-13 2010-05-25 The Boeing Company Rib support for wing panels
GB0813584D0 (en) * 2008-07-25 2008-09-03 Airbus Uk Ltd Method of stiffening a rib
ES2372828B1 (es) * 2008-12-17 2012-12-13 Airbus Operations, S.L. Costilla-herraje.
GB0906952D0 (en) 2009-04-23 2009-06-03 Airbus Uk Ltd Aircraft assembly and spar
US8936216B2 (en) * 2009-05-28 2015-01-20 Societe Lorraine De Construction Aeronautique Composite structuring panel for the trailing edge of an aircraft element
US8408493B2 (en) * 2010-05-19 2013-04-02 The Boeing Company Composite stringer end trim
GB201110973D0 (en) * 2011-06-28 2011-08-10 Airbus Operations Ltd Bracket
US8758879B2 (en) * 2012-06-24 2014-06-24 The Boeing Company Composite hat stiffener, composite hat-stiffened pressure webs, and methods of making the same
US9327470B1 (en) * 2012-12-05 2016-05-03 The Boeing Company Variable-radius laminated radius filler and system and method for manufacturing same
EP3100852B1 (de) * 2015-06-03 2017-11-15 Tusas-Türk Havacilik Ve Uzay Sanayii A.S. Gebogene laminierte struktur
CN105151271B (zh) * 2015-09-21 2017-12-22 中国运载火箭技术研究院 一种外形贯穿飞行器机身的复合材料梁结构
US10046525B2 (en) 2016-09-30 2018-08-14 The Boeing Company Advanced variable radius laminated composite radius filler
CN109625245A (zh) * 2018-11-02 2019-04-16 中国航空工业集团公司西安飞机设计研究所 一种通用飞机复合材料方向舵及制作方法
CN109334944B (zh) * 2018-11-12 2021-02-26 中国直升机设计研究所 一种飞机支撑骨架
US11180238B2 (en) * 2018-11-19 2021-11-23 The Boeing Company Shear ties for aircraft wing
CN114261506B (zh) * 2021-12-31 2024-06-07 中国航空工业集团公司西安飞机设计研究所 一种具有整体油箱的复合材料机翼

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4219980A (en) * 1977-08-26 1980-09-02 Rockwell International Corporation Reinforced composite structure and method of fabrication thereof
US4657615A (en) * 1984-08-20 1987-04-14 The Boeing Company Composite leading edge/spar member for an aircraft control surface
US5358583A (en) * 1988-10-19 1994-10-25 E. I. Du Pont De Nemours And Company Apparatus and method for shaping fiber reinforced resin matrix materials and product thereof
US5514448A (en) 1992-07-22 1996-05-07 Mitsui Toatsu Chemicals, Inc. Laminated molding
GB9828368D0 (en) 1998-12-22 1999-02-17 British Aerospace Forming reinforcing components
EP1031406A1 (de) 1999-02-22 2000-08-30 British Aerospace Herstellung von Verstärkungsteilen
US6513757B1 (en) * 1999-07-19 2003-02-04 Fuji Jukogyo Kabushiki Kaisha Wing of composite material and method of fabricating the same
JP4425424B2 (ja) 2000-05-01 2010-03-03 本田技研工業株式会社 繊維強化複合材からなるジョグル付き半硬化物品の製造方法、及びそれを用いた予備成形構造体の製造方法

Also Published As

Publication number Publication date
NO20041174L (no) 2004-03-19
WO2003022677A1 (en) 2003-03-20
ATE325034T1 (de) 2006-06-15
CA2459167A1 (en) 2003-03-20
CA2459167C (en) 2008-11-18
US7380753B2 (en) 2008-06-03
GB0122050D0 (en) 2001-10-31
DE60211185T2 (de) 2006-09-07
EP1425215B1 (de) 2006-05-03
ES2258645T3 (es) 2006-09-01
EP1425215A1 (de) 2004-06-09
US20040244334A1 (en) 2004-12-09
NO322021B1 (no) 2006-08-07

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Legal Events

Date Code Title Description
8327 Change in the person/name/address of the patent owner

Owner name: AIRBUS UK LTD., BRISTOL, GB

8364 No opposition during term of opposition
R082 Change of representative

Ref document number: 1425215

Country of ref document: EP

Representative=s name: PATENTANWAELTE WALLACH, KOCH & PARTNER, 80339 MUEN