ATE249921T1 - Verfahren zur verstärkung eines laminats z.b für die aussenhaut von flugzeugen - Google Patents

Verfahren zur verstärkung eines laminats z.b für die aussenhaut von flugzeugen

Info

Publication number
ATE249921T1
ATE249921T1 AT01905863T AT01905863T ATE249921T1 AT E249921 T1 ATE249921 T1 AT E249921T1 AT 01905863 T AT01905863 T AT 01905863T AT 01905863 T AT01905863 T AT 01905863T AT E249921 T1 ATE249921 T1 AT E249921T1
Authority
AT
Austria
Prior art keywords
reinforcing
aircraft
laminate
skin
laminated
Prior art date
Application number
AT01905863T
Other languages
English (en)
Inventor
Andrew Paul Godbehere
Stephen Williams
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
Application granted granted Critical
Publication of ATE249921T1 publication Critical patent/ATE249921T1/de

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • 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
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • 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.]
    • Y10T428/24752—Laterally noncoextensive components

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
AT01905863T 2000-02-11 2001-02-06 Verfahren zur verstärkung eines laminats z.b für die aussenhaut von flugzeugen ATE249921T1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0003029.6A GB0003029D0 (en) 2000-02-11 2000-02-11 A method of reinforcing a laminated member such as a skin for an aircraft
PCT/GB2001/000469 WO2001058680A1 (en) 2000-02-11 2001-02-06 A method of reinforcing a laminated member such as a skin for an aircraft

Publications (1)

Publication Number Publication Date
ATE249921T1 true ATE249921T1 (de) 2003-10-15

Family

ID=9885293

Family Applications (1)

Application Number Title Priority Date Filing Date
AT01905863T ATE249921T1 (de) 2000-02-11 2001-02-06 Verfahren zur verstärkung eines laminats z.b für die aussenhaut von flugzeugen

Country Status (8)

Country Link
US (1) US7780808B2 (de)
EP (1) EP1263572B1 (de)
AT (1) ATE249921T1 (de)
AU (1) AU2001233835A1 (de)
DE (1) DE60100802T2 (de)
ES (1) ES2202274T3 (de)
GB (1) GB0003029D0 (de)
WO (1) WO2001058680A1 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2002354986B2 (en) 2001-07-19 2006-11-30 Vestas Wind Systems A/S Wind turbine blade
GB0117804D0 (en) 2001-07-21 2001-09-12 Bae Systems Plc Aircraft structural components
EP1544099B1 (de) * 2003-12-18 2009-01-07 Airbus UK Limited Verfahren zum Verbinden von Flugzeugstrukturbauteilen
GB0329373D0 (en) 2003-12-18 2004-01-21 Airbus Uk Ltd Method of joining structural elements in an aircraft
ES2347507B1 (es) * 2007-12-27 2011-08-17 Airbus Operations, S.L. Boca de acceso de aeronave optimizada.
FR2933067B1 (fr) * 2008-06-26 2010-10-08 Airbus France Panneau de fuselage d'aeronef renforce et procede de fabrication.
WO2011043346A1 (ja) * 2009-10-08 2011-04-14 三菱重工業株式会社 複合材構造体、これを備えた航空機主翼および航空機胴体
GB201000878D0 (en) 2010-01-20 2010-03-10 Airbus Operations Ltd Sandwich panel
CN101891015B (zh) * 2010-07-20 2013-04-10 中国航空工业集团公司西安飞机设计研究所 一种蒙皮板减重方法
US9108387B2 (en) * 2011-06-30 2015-08-18 The Boeing Company Electrically conductive structure
FR2977186B1 (fr) * 2011-07-01 2014-08-22 Daher Aerospace Procede de renforcement local d'un panneau composite a renfort fibreux et panneau obtenu par un tel procede
ES2401520B1 (es) 2011-07-28 2014-06-10 Airbus Operations S.L. procedimiento de fabricación de una pieza de material compuesto de un compartimento cerrado con una disposición de acceso integrada
GB201115080D0 (en) 2011-09-01 2011-10-19 Airbus Operations Ltd An aircraft structure
DE102011083162A1 (de) * 2011-09-21 2013-03-21 Bayerische Motoren Werke Aktiengesellschaft Mehrlagiges Faserverbundbauteil und Verfahren zum Herstellen desselben
US10542773B2 (en) * 2013-07-19 2020-01-28 Philip Morris Products S.A. Hydrophobic paper
EP2842865B1 (de) * 2013-08-28 2019-12-18 Airbus Operations GmbH Fensterscheibe für ein flugwerk und verfahren zur herstellung davon
US10479517B2 (en) * 2016-12-05 2019-11-19 The Boeing Company Composite fan cowl with a core having tailored thickness
JP6770987B2 (ja) 2018-03-12 2020-10-21 株式会社Ｓｕｂａｒｕ 複合材構造体、航空機及び雷電流の誘導方法
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
GB2604126A (en) * 2021-02-24 2022-08-31 Airbus Operations Ltd Reinforced holes

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2154286A (en) 1984-02-13 1985-09-04 Gen Electric Hollow laminated airfoil
US5866272A (en) * 1996-01-11 1999-02-02 The Boeing Company Titanium-polymer hybrid laminates
FR2771330B1 (fr) 1997-11-26 2004-02-27 Aerospatiale Procede de fabrication d'un panneau composite monolithique articule avec des moyens raidisseurs integres, panneau articule obtenu et capot articule dans un aeronef
GB9826681D0 (en) 1998-12-04 1999-01-27 British Aerospace Composite laminates

Also Published As

Publication number Publication date
US7780808B2 (en) 2010-08-24
AU2001233835A1 (en) 2001-08-20
DE60100802D1 (de) 2003-10-23
EP1263572A1 (de) 2002-12-11
ES2202274T3 (es) 2004-04-01
WO2001058680A1 (en) 2001-08-16
GB0003029D0 (en) 2000-03-29
DE60100802T2 (de) 2004-04-08
US20030021958A1 (en) 2003-01-30
EP1263572B1 (de) 2003-09-17

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