AU2001233835A1 - A method of reinforcing a laminated member such as a skin for an aircraft - Google Patents

A method of reinforcing a laminated member such as a skin for an aircraft

Info

Publication number
AU2001233835A1
AU2001233835A1 AU2001233835A AU3383501A AU2001233835A1 AU 2001233835 A1 AU2001233835 A1 AU 2001233835A1 AU 2001233835 A AU2001233835 A AU 2001233835A AU 3383501 A AU3383501 A AU 3383501A AU 2001233835 A1 AU2001233835 A1 AU 2001233835A1
Authority
AU
Australia
Prior art keywords
skin
reinforcing
aircraft
laminated
laminated member
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.)
Abandoned
Application number
AU2001233835A
Inventor
Andrew Paul Godbehere
Stephen Williams
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.)
BAE Systems PLC
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 AU2001233835A1 publication Critical patent/AU2001233835A1/en
Abandoned legal-status Critical Current

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)

Abstract

A method of reinforcing a laminated wing skin (10) for an aircraft. The method comprises laying-up a plurality of fibers to form the laminated wing skin (10). A composite reinforcement member (14) is positioned on a surface (16) of the laminated skin (10) and one or more further layers are laid up so as to enclose the composite reinforcing member (14) at a position adjacent one surface of the laminated skin (10).
AU2001233835A 2000-02-11 2001-02-06 A method of reinforcing a laminated member such as a skin for an aircraft Abandoned AU2001233835A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB0003029 2000-02-11
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
AU2001233835A1 true AU2001233835A1 (en) 2001-08-20

Family

ID=9885293

Family Applications (1)

Application Number Title Priority Date Filing Date
AU2001233835A Abandoned AU2001233835A1 (en) 2000-02-11 2001-02-06 A method of reinforcing a laminated member such as a skin for an aircraft

Country Status (8)

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

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1746284B2 (en) 2001-07-19 2021-09-29 Vestas Wind Systems A/S Wind turbine blade
GB0117804D0 (en) 2001-07-21 2001-09-12 Bae Systems Plc Aircraft structural components
EP1544099B1 (en) * 2003-12-18 2009-01-07 Airbus UK Limited Method of joining structural elements in an aircraft
GB0329373D0 (en) 2003-12-18 2004-01-21 Airbus Uk Ltd Method of joining structural elements in an aircraft
ES2347507B1 (en) * 2007-12-27 2011-08-17 Airbus Operations, S.L. OPTIMIZED AIRCRAFT ACCESS MOUTH.
FR2933067B1 (en) 2008-06-26 2010-10-08 Airbus France REINFORCED AIRCRAFT FUSELAGE PANEL AND METHOD FOR MANUFACTURING THE SAME
US9108718B2 (en) * 2009-10-08 2015-08-18 Mitsubishi Heavy Industries, Ltd. Composite-material structure and aircraft main wing and aircraft fuselage provided with the same
GB201000878D0 (en) 2010-01-20 2010-03-10 Airbus Operations Ltd Sandwich panel
CN101891015B (en) * 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 Skin plate weight reducing method
US9108387B2 (en) * 2011-06-30 2015-08-18 The Boeing Company Electrically conductive structure
FR2977186B1 (en) * 2011-07-01 2014-08-22 Daher Aerospace METHOD FOR LOCALLY REINFORCING A COMPOSITE FIBROUS REINFORCED PANEL AND PANEL OBTAINED BY SUCH A METHOD
ES2401520B1 (en) * 2011-07-28 2014-06-10 Airbus Operations S.L.  MANUFACTURING PROCEDURE OF A COMPOSITE MATERIAL PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS PROVISION
GB201115080D0 (en) 2011-09-01 2011-10-19 Airbus Operations Ltd An aircraft structure
DE102011083162A1 (en) * 2011-09-21 2013-03-21 Bayerische Motoren Werke Aktiengesellschaft Method for manufacturing multilayered fiber composite component of vehicle, involves attaching portions of fiber composite layers at which space is formed by inserting insert portion, with each other
EP3021695B1 (en) * 2013-07-19 2018-06-27 Philip Morris Products S.a.s. Hydrophobic paper
EP2842865B1 (en) * 2013-08-28 2019-12-18 Airbus Operations GmbH Window panel for an airframe and method of producing same
US10479517B2 (en) * 2016-12-05 2019-11-19 The Boeing Company Composite fan cowl with a core having tailored thickness
JP6770987B2 (en) * 2018-03-12 2020-10-21 株式会社Ｓｕｂａｒｕ Composite structure, aircraft and lightning current induction method
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 (en) 1997-11-26 2004-02-27 Aerospatiale METHOD OF MANUFACTURING A MONOLITHIC COMPOSITE PANEL ARTICULATED WITH INTEGRATED STRAIGHTENER MEANS, ARTICULATED PANEL OBTAINED AND ARTICULATED HOOD IN AN AIRCRAFT
GB9826681D0 (en) * 1998-12-04 1999-01-27 British Aerospace Composite laminates

Also Published As

Publication number Publication date
WO2001058680A1 (en) 2001-08-16
US7780808B2 (en) 2010-08-24
GB0003029D0 (en) 2000-03-29
DE60100802D1 (en) 2003-10-23
ATE249921T1 (en) 2003-10-15
EP1263572A1 (en) 2002-12-11
ES2202274T3 (en) 2004-04-01
US20030021958A1 (en) 2003-01-30
EP1263572B1 (en) 2003-09-17
DE60100802T2 (en) 2004-04-08

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