WO2001058680A1 - 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 Download PDF

Info

Publication number
WO2001058680A1
WO2001058680A1 PCT/GB2001/000469 GB0100469W WO0158680A1 WO 2001058680 A1 WO2001058680 A1 WO 2001058680A1 GB 0100469 W GB0100469 W GB 0100469W WO 0158680 A1 WO0158680 A1 WO 0158680A1
Authority
WO
WIPO (PCT)
Prior art keywords
laminated
aircraft
skin
reinforcing
laminated member
Prior art date
Application number
PCT/GB2001/000469
Other languages
French (fr)
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
Priority to AT01905863T priority Critical patent/ATE249921T1/en
Priority to AU2001233835A priority patent/AU2001233835A1/en
Priority to US10/182,904 priority patent/US7780808B2/en
Priority to DE60100802T priority patent/DE60100802T2/en
Priority to EP01905863A priority patent/EP1263572B1/en
Publication of WO2001058680A1 publication Critical patent/WO2001058680A1/en

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

Definitions

  • the invention relates to a method of reinforcing a laminated skin for an aircraft.
  • An increase in local thickness of aircraft skin is often desirable, particularly to provide reinforcement around an access hole.
  • Fig 1 is a cross section of a laminated skin for an aircraft reinforced in a known manner.
  • the plies 1 which are formed from carbon fibre composite, glass fibre or aramid fibres, are generally buried spaced apart between successive layers 3 to define a reinforced area 4.
  • An aim of the invention is to provide an improved method of reinforcing a laminated member for an aircraft.
  • a method of reinforcing a laminated member such as a skin for an a ircraft, the method comprising laying-up a plurality of layers to form part of the laminated member, positioning a composite reinforcement member on a layer of the laminate member and laying-up one or more further layers so as to complete the laying up of the laminated member and enclose the composite reinforcing member at a position adjacent one surface of the completed laminated member.
  • the method may include forming the composite reinforcement member from a plurality of layers, preferably at the same time that the laminated member is being produced in a parallel process. In that way, production time can be minimised.
  • the finished composite reinforcement member can then be introduced into the laminated member at a convenient time.
  • a laminated member such as a skin for an aircraft reinforced using a method according to the first aspect or any of the consistory clauses relating thereto.
  • Fig 2 is a cross section through a laminated skin for an aircraft reinforced by a method in accordance with the invention
  • Figure 3 is a cross section through a laminated skin section made in accordance with the invention and having an access hole formed therethrough.
  • An aircraft wing skin 10 is of laminated form and is made from a lay-up of fibres so as to comprise a plurality of layers 12, each layer being laid in one of several different directions, for example at 0 degrees, 45 degrees and - 45 degrees, in known manner.
  • a composite reinforcement member 14 is also made from a lay up of fibres so as to comprise a plurality of layers 16.
  • the layers 16 may be arranged so as to form a reinforcement member 14 which generally tapers towards an inner surface 18 of the wing skin 10.
  • many similar composite reinforcement members 14 are required.
  • the composite reinforcement members 14 can be manufactured by an automated dedicated process.
  • the composite reinforcement member 14 may be produced in parallel with, and preferably at the same time as, the wing skin 10. In that way, the lead-time in manufacturing the wing skin 10 can be significantly reduced.
  • the composite reinforcement member 14 is positioned on a layer 12 of the wing skin 10 just prior to the end of the wing skin lay-up process. Once the reinforcement member 14 has been placed in position, one or more final layers 12 are added to hold the composite reinforcement member 14 firmly in place beneath and adjacent the inner surface 18 of the wing skin 10.
  • manufacturing and design is significantly simplified and associated costs are reduced, together with the risk of delamination when compared to the Figure 1 arrangement.
  • fewer layers 12 are stepped from the centroid of the wing skin 10 than in the Figure 1 arrangement, thereby making the skin more structurally efficient.
  • an access hole 20 may be formed through the composite reinforcement member 14 and layers 12 of the wing skin 10.
  • the composite reinforcement member 14 may be made using a variety of technologies including pre peg, woven, braided, pultruded or any other applicable technology.

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 fibres 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).

Description

A METHOD OF REINFORCING A LAMINATED MEMBER SUCH AS A SKIN
FOR AN AIRCRAFT
The invention relates to a method of reinforcing a laminated skin for an aircraft.
An increase in local thickness of aircraft skin is often desirable, particularly to provide reinforcement around an access hole.
Fig 1 is a cross section of a laminated skin for an aircraft reinforced in a known manner.
Referring to Fig 1 , it is known to add reinforcement plies 1 to a laminated skin section 2 formed from layers 3 in order to increase the local thickness. The plies 1, which are formed from carbon fibre composite, glass fibre or aramid fibres, are generally buried spaced apart between successive layers 3 to define a reinforced area 4.
Where multiple reinforcement plies 1 are inserted between successive layers 3, the multiple layers are effectively displaced from the centroid of the skin section 2 which is not always desirable. Moreover, the separation of successive layers 3 by the reinforcement plies 1 increases the possibility of peel-induced delamination of the skin section 2.
An aim of the invention is to provide an improved method of reinforcing a laminated member for an aircraft.
According to a first aspect of the invention there is provided a method of reinforcing a laminated member such as a skin for an a ircraft, the method comprising laying-up a plurality of layers to form part of the laminated member, positioning a composite reinforcement member on a layer of the laminate member and laying-up one or more further layers so as to complete the laying up of the laminated member and enclose the composite reinforcing member at a position adjacent one surface of the completed laminated member.
In that way, instead of providing a plurality of reinforcement members, each being placed between different adjacent layers of the laminated member, only the single composite reinforcement member need be placed between the adjacent layers. Consequently, fewer layers of the laminated member are stepped, thereby making the laminated member more structurally efficient and leading to performance benefits.
The method may include forming the composite reinforcement member from a plurality of layers, preferably at the same time that the laminated member is being produced in a parallel process. In that way, production time can be minimised. The finished composite reinforcement member can then be introduced into the laminated member at a convenient time.
According to a second aspect of the invention there is provided a laminated member such as a skin for an aircraft reinforced using a method according to the first aspect or any of the consistory clauses relating thereto.
A method of reinforcing a laminated skin for an aircraft in accordance with the invention will now be described by way of example and with reference to Figures 2 and 3 of the remaining accompanying drawings in which
Fig 2 is a cross section through a laminated skin for an aircraft reinforced by a method in accordance with the invention,
Figure 3 is a cross section through a laminated skin section made in accordance with the invention and having an access hole formed therethrough.
An aircraft wing skin 10 is of laminated form and is made from a lay-up of fibres so as to comprise a plurality of layers 12, each layer being laid in one of several different directions, for example at 0 degrees, 45 degrees and - 45 degrees, in known manner.
Referring to Fig. 2, a composite reinforcement member 14 is also made from a lay up of fibres so as to comprise a plurality of layers 16. The layers 16 may be arranged so as to form a reinforcement member 14 which generally tapers towards an inner surface 18 of the wing skin 10. In some applications, for example when reinforcing access holes in aircraft wing skins, many similar composite reinforcement members 14 are required. In such a case, the composite reinforcement members 14 can be manufactured by an automated dedicated process.
The composite reinforcement member 14 may be produced in parallel with, and preferably at the same time as, the wing skin 10. In that way, the lead-time in manufacturing the wing skin 10 can be significantly reduced.
The composite reinforcement member 14 is positioned on a layer 12 of the wing skin 10 just prior to the end of the wing skin lay-up process. Once the reinforcement member 14 has been placed in position, one or more final layers 12 are added to hold the composite reinforcement member 14 firmly in place beneath and adjacent the inner surface 18 of the wing skin 10. By placing the reinforcement member 14 in the lay-up as described with respect to Figure 2, manufacturing and design is significantly simplified and associated costs are reduced, together with the risk of delamination when compared to the Figure 1 arrangement. Moreover, fewer layers 12 are stepped from the centroid of the wing skin 10 than in the Figure 1 arrangement, thereby making the skin more structurally efficient.
Referring to Fig. 3, once the wing skin lay-up process is completed, an access hole 20 may be formed through the composite reinforcement member 14 and layers 12 of the wing skin 10.
The composite reinforcement member 14 may be made using a variety of technologies including pre peg, woven, braided, pultruded or any other applicable technology.
Whilst specific reference has been made to a laminated skin of an aircraft, the invention could be applied to laminated ribs or spars or another member for an aircraft.

Claims

1. A method of reinforcing a laminated member for an aircraft, the method comprising laying-up a plurality of layers to form part of the laminated member, positioning a composite reinforcement member on a layer of the laminate member and laying-up one or more further layers so as to complete the laying up of the laminated member and enclose the composite reinforcing member at a position adjacent one surface of the completed laminated member.
2. A method according to Claim 1, in which the method includes forming the composite reinforcement member from a plurality of layers.
3. A method according to Claim 2, in which the method includes forming the composite reinforcement member at the same time as the laminated member is produced in a parallel process.
4. A method according to Claim 1, Claim 2 or Claim 3, in which the method includes forming an access hole through a part of the laminated member which is reinforced by the composite reinforcement member.
5. A method of reinforcing a laminated member for an aircraft substantially as described herein with reference to Figures 2 and 3 of the accompanying drawings.
6. A laminated member for an aircraft reinforced using a method according to any of Claims 1 to 5.
7. A laminated wing skin for an aircraft constructed and arranged substantially as described herein with reference to figure 2 or 3 of the accompanying drawings.
PCT/GB2001/000469 2000-02-11 2001-02-06 A method of reinforcing a laminated member such as a skin for an aircraft WO2001058680A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT01905863T ATE249921T1 (en) 2000-02-11 2001-02-06 METHOD FOR REINFORCING A LAMINATE, E.G. FOR THE OUTSIDE SKIN OF AIRCRAFT
AU2001233835A AU2001233835A1 (en) 2000-02-11 2001-02-06 A method of reinforcing a laminated member such as a skin for an aircraft
US10/182,904 US7780808B2 (en) 2000-02-11 2001-02-06 Method of reinforcing a laminated member such as a skin for an aircraft
DE60100802T DE60100802T2 (en) 2000-02-11 2001-02-06 METHOD FOR REINFORCING A LAMINATE FOR THE EXTERNAL SKIN OF AIRCRAFT
EP01905863A EP1263572B1 (en) 2000-02-11 2001-02-06 A method of reinforcing a laminated member such as a skin for an aircraft

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
GB0003029.6 2000-02-11

Publications (1)

Publication Number Publication Date
WO2001058680A1 true WO2001058680A1 (en) 2001-08-16

Family

ID=9885293

Family Applications (1)

Application Number Title Priority Date Filing Date
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

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)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1544099A1 (en) * 2003-12-18 2005-06-22 Airbus UK Limited Method of joining structural elements in an aircraft
US7357353B2 (en) 2003-12-18 2008-04-15 Airbus Uk Limited Method of joining structural elements in an aircraft
US7629037B2 (en) 2001-07-21 2009-12-08 Airbus Uk Limited Aircraft structural components
FR2933067A1 (en) * 2008-06-26 2010-01-01 Airbus France REINFORCED AIRCRAFT FUSELAGE PANEL AND METHOD FOR MANUFACTURING THE SAME
CN101891015A (en) * 2010-07-20 2010-11-24 中国航空工业集团公司西安飞机设计研究所 Skin plate weight reducing method
FR2977186A1 (en) * 2011-07-01 2013-01-04 Daher Aerospace METHOD FOR LOCALLY REINFORCING A COMPOSITE FIBROUS REINFORCED PANEL AND PANEL OBTAINED BY SUCH A METHOD
ES2401520A2 (en) * 2011-07-28 2013-04-22 Airbus Operations S.L. Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly
US9085350B2 (en) 2010-01-20 2015-07-21 Airbus Operations Limited Aircraft wing cover comprising a sandwich panel and methods to manufacture and design the said wing cover
EP1746284B1 (en) 2001-07-19 2016-04-20 Vestas Wind Systems A/S Wind turbine blade
US9810601B2 (en) 2011-09-01 2017-11-07 Airbus Operations Limited Aircraft structure
CN108146641A (en) * 2016-12-05 2018-06-12 波音公司 The composite fan radome fairing of core with tailored thicknesses
US11447266B2 (en) 2018-03-12 2022-09-20 Subaru Corporation Composite structure, aircraft, and lightning current guiding 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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2347507B1 (en) * 2007-12-27 2011-08-17 Airbus Operations, S.L. OPTIMIZED AIRCRAFT ACCESS MOUTH.
BR112012001714B1 (en) * 2009-10-08 2020-04-07 Mitsubishi Heavy Ind Ltd main aircraft wing and aircraft fuselage
US9108387B2 (en) * 2011-06-30 2015-08-18 The Boeing Company Electrically conductive 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
TR201809971T4 (en) * 2013-07-19 2018-08-27 Philip Morris Products Sa Hydrophobic paper.
EP2842865B1 (en) * 2013-08-28 2019-12-18 Airbus Operations GmbH Window panel for an airframe and method of producing same
GB2604126A (en) * 2021-02-24 2022-08-31 Airbus Operations Ltd Reinforced holes

Citations (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
EP0783960A2 (en) * 1996-01-11 1997-07-16 The Boeing Company Titanium-polymer hybrid laminates
FR2771330A1 (en) * 1997-11-26 1999-05-28 Aerospatiale Aircraft cowl
WO2000034031A1 (en) * 1998-12-04 2000-06-15 Bae Systems Plc Composite laminates

Patent Citations (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
EP0783960A2 (en) * 1996-01-11 1997-07-16 The Boeing Company Titanium-polymer hybrid laminates
FR2771330A1 (en) * 1997-11-26 1999-05-28 Aerospatiale Aircraft cowl
WO2000034031A1 (en) * 1998-12-04 2000-06-15 Bae Systems Plc Composite laminates

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3219981B1 (en) 2001-07-19 2021-09-01 Vestas Wind Systems A/S Wind turbine blade
EP1520983B1 (en) 2001-07-19 2017-04-12 Vestas Wind Systems A/S Wind turbine blade
EP1746284B1 (en) 2001-07-19 2016-04-20 Vestas Wind Systems A/S Wind turbine blade
US7629037B2 (en) 2001-07-21 2009-12-08 Airbus Uk Limited Aircraft structural components
US7357353B2 (en) 2003-12-18 2008-04-15 Airbus Uk Limited Method of joining structural elements in an aircraft
EP1544099A1 (en) * 2003-12-18 2005-06-22 Airbus UK Limited Method of joining structural elements in an aircraft
FR2933067A1 (en) * 2008-06-26 2010-01-01 Airbus France REINFORCED AIRCRAFT FUSELAGE PANEL AND METHOD FOR MANUFACTURING THE SAME
US9034453B2 (en) 2008-06-26 2015-05-19 Airbus Operations S.A.S. Reinforced aircraft fuselage panel and method of manufacture
WO2010004159A3 (en) * 2008-06-26 2010-03-04 Airbus Operations Reinforced aircraft fuselage panel and method of manufacture.
WO2010004159A2 (en) * 2008-06-26 2010-01-14 Airbus Operations Reinforced aircraft fuselage panel and method of manufacture.
US9085350B2 (en) 2010-01-20 2015-07-21 Airbus Operations Limited Aircraft wing cover comprising a sandwich panel and methods to manufacture and design the said wing cover
CN101891015A (en) * 2010-07-20 2010-11-24 中国航空工业集团公司西安飞机设计研究所 Skin plate weight reducing method
FR2977186A1 (en) * 2011-07-01 2013-01-04 Daher Aerospace METHOD FOR LOCALLY REINFORCING A COMPOSITE FIBROUS REINFORCED PANEL AND PANEL OBTAINED BY SUCH A METHOD
WO2013004671A1 (en) 2011-07-01 2013-01-10 Daher Aerospace Method for locally strengthening a composite panel with fibrous reinforcement and panel obtained using such a method
US9889603B2 (en) 2011-07-01 2018-02-13 Daher Aerospace Method for local reinforcement of a composite fiber reinforced panel and panel obtained using said method
US9073271B2 (en) 2011-07-28 2015-07-07 Airbus Operations, S.L. Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly
ES2401520R1 (en) * 2011-07-28 2013-08-05 Airbus Operations Sl MANUFACTURING PROCEDURE OF A COMPOSITE MATERIAL PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS PROVISION
ES2401520A2 (en) * 2011-07-28 2013-04-22 Airbus Operations S.L. Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly
US9810601B2 (en) 2011-09-01 2017-11-07 Airbus Operations Limited Aircraft structure
CN108146641A (en) * 2016-12-05 2018-06-12 波音公司 The composite fan radome fairing of core with tailored thicknesses
EP3360784A1 (en) * 2016-12-05 2018-08-15 The Boeing Company Composite fan cowl with a core having tailored thickness
US10479517B2 (en) 2016-12-05 2019-11-19 The Boeing Company Composite fan cowl with a core having tailored thickness
CN108146641B (en) * 2016-12-05 2023-08-04 波音公司 Composite fan cowling with tailored thickness core
US11447266B2 (en) 2018-03-12 2022-09-20 Subaru Corporation Composite structure, aircraft, and lightning current guiding method
EP3539881B1 (en) * 2018-03-12 2023-02-08 Subaru Corporation Composite structure, aircraft, and lightning current guiding 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

Also Published As

Publication number Publication date
US7780808B2 (en) 2010-08-24
DE60100802D1 (en) 2003-10-23
AU2001233835A1 (en) 2001-08-20
EP1263572B1 (en) 2003-09-17
ATE249921T1 (en) 2003-10-15
GB0003029D0 (en) 2000-03-29
DE60100802T2 (en) 2004-04-08
ES2202274T3 (en) 2004-04-01
US20030021958A1 (en) 2003-01-30
EP1263572A1 (en) 2002-12-11

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