WO2001034381A1 - Renfort pour element stratifie d'un aeronef - Google Patents

Renfort pour element stratifie d'un aeronef Download PDF

Info

Publication number
WO2001034381A1
WO2001034381A1 PCT/GB2000/004186 GB0004186W WO0134381A1 WO 2001034381 A1 WO2001034381 A1 WO 2001034381A1 GB 0004186 W GB0004186 W GB 0004186W WO 0134381 A1 WO0134381 A1 WO 0134381A1
Authority
WO
WIPO (PCT)
Prior art keywords
reinforcement member
laminated
reinforcement
aircraft
penetrates
Prior art date
Application number
PCT/GB2000/004186
Other languages
English (en)
Inventor
Andrew Paul Godbehere
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 JP2001536358A priority Critical patent/JP2003513821A/ja
Priority to AU11555/01A priority patent/AU1155501A/en
Publication of WO2001034381A1 publication Critical patent/WO2001034381A1/fr

Links

Classifications

    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B29C65/564—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined hidden in the joint, e.g. dowels or Z-pins
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • 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
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/08—Interconnection of layers by mechanical means
    • B32B7/09—Interconnection of layers by mechanical means by stitching, needling or sewing
    • 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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/08—Reinforcements
    • 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
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Definitions

  • the invention relates to reinforcement of a laminated member for an aircraft and relates primarily to a method of securing a reinforcement member to a laminated skin for an aircraft.
  • Fig 1 of the accompanying drawings it is known to add reinforcement plies 1 to a laminated skin section 2 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 in a stack, the stack being bound by successive layers 3 forming the skin section 2 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 securing a reinforcement member to a laminated member for an aircraft comprising the steps of, positioning the reinforcement member on or beneath a surface ofthe laminated member and providing means which penetrates the reinforcement member and laminated member to inhibit separation of one from the other.
  • the method may include providing the laminated member in the form of a laminated skin for the aircraft.
  • the method may further include leaving the means which penetrates the reinforcement member permanently in position.
  • the method may include causing the means which penetrates the reinforcement member to pass completely through the reinforcement member.
  • the method includes providing the means which penetrates the reinforcement member in the form of pins or stitches.
  • the step of providing pins or stitches may comprise inserting the pins or stitches into the reinforcement member and the laminated member at an angle substantially perpendicular to the plane of the laminated member.
  • the pins penetrate those laminations of the laminated member which, in use, will be subjected to peel loads.
  • the step of positioning a reinforcement member on the laminated member takes place after the laminating stage of making the laminated member. That is advantageous over the prior method where the plies needed to increase the local thickness need to be put in place during the laminating process.
  • the method includes providing a reinforcement member in the form of a structural member arranged to withstand loading or a preformed laminate.
  • the method may include introducing a material such as an adhesive or compliant layer between an edge region ofthe reinforcement member and the laminated member.
  • a material such as an adhesive or compliant layer between an edge region ofthe reinforcement member and the laminated member.
  • Fig 2 is a cross section of part of a laminated skin for an aircraft reinforced by a method in accordance with the invention
  • Fig 3 is a cross section of part of a laminated skm for an aircraft reinforced usmg a further method in accordance with the invention.
  • Fig 4 shows one example of the case of a structural member to reinforce a laminated skm for an aircraft
  • a parent mate ⁇ al such as an aircraft wmg skm 10 is of laminated form
  • the wmg skm 10 comp ⁇ ses a lay-up of fibres 12, each layer of fibres 12 being laid m one of several different directions, for example at 0 degrees, 45 degrees and - 45 degrees
  • a preformed reinforcement member 14 is positioned on an inner surface 16 of the wmg skm 10
  • Pms 18 are inserted through the reinforcement member 14 into the wmg skm 10
  • the pms 18 enter at an angle substantially perpendicular to the wmg skm 10 and penetrate some of the layers of fibres 12.
  • the pms 18 may enter at different and va ⁇ ous angles so that the reinforcement members 14 are particularly difficult to detach from the wing skm 10
  • the pms 18 penetrate the wmg skm 10 to a layer of fibres 12 at a depth where the layer of fibres 12 is not exposed to peel loads.
  • the reinforcement member 14 can be preformed to the desired thickness it is not necessary to reinforce the skin, for example by introducing multiple plies 1 between successive layers 3 as shown in Fig 1 , thereby simplifying the design of the wing skin 10.
  • a compliant layer 20 such as an adhesive may be introduced between the wing skin 10 and a peripheral margin ofthe reinforcement member 14.
  • the compliant layer 20 helps to reduce local stress at the edge of the reinforcement member 14.
  • the compliant layer 20 is of triangular cross section but may be of another suitable cross section. When it is desirable that part ofthe compliant layer 20 be a ⁇ anged under the reinforcement member 14 as shown in Fig 3, the compliant layer is positioned on the wing skin 10 prior to positioning of the reinforcement member 14. The pins 18 then pass through the reinforcement member 14 and the compliant layer 20 into the wing skin 10.
  • the compliant layer 20 may be arranged directly against the peripheral edge of the reinforcement member 14 after positioning of the reinforcement member on the wing skin 10.
  • a main structural member 22 of T-shaped cross section intended to bear load has its flange 24 joined to the wing skin 10 and is held in place by means of pins 18.
  • the preformed reinforcement member 14 may be positioned beneath the inner surface 16 of the wing skin 10 just prior to the end of the laminating stage and one or more closure layers 12 may be added in the laminating stage to hold the reinforcement member 14 firmly in place.
  • the reinforcement member 14 could be buried in the wing skin 10 at any depth by temporarily halting the laminating stage. As a single reinforcement member 14 is inserted in such a case rather than a multiplicity of plies, the risk of delamination is reduced when compared to the Fig 1 construction. It will be appreciated that whilst pins 18 have been described as the means which penetrates the reinforcement member and the laminated skin of the aircraft, stitches could also be used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
  • Connection Of Plates (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)

Abstract

L'invention concerne un procédé qui permet de fixer un élément de renfort (14) à un élément stratifié d'un aéronef, tel qu'un parement stratifié (10). Le procédé consiste à placer l'élément de renfort (14) sur ou sous une surface (16) de l'élément stratifié (18) et à utiliser un moyen qui pénètre l'élément de renfort (14) et l'élément stratifié (18) pour les empêcher de se désolidariser.
PCT/GB2000/004186 1999-11-11 2000-11-02 Renfort pour element stratifie d'un aeronef WO2001034381A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2001536358A JP2003513821A (ja) 1999-11-11 2000-11-02 航空機用の積層した部材の強化
AU11555/01A AU1155501A (en) 1999-11-11 2000-11-02 Reinforcement of a laminated member for an aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9926579.5 1999-11-11
GBGB9926579.5A GB9926579D0 (en) 1999-11-11 1999-11-11 Reinforcement of a laminated member for an aircraft

Publications (1)

Publication Number Publication Date
WO2001034381A1 true WO2001034381A1 (fr) 2001-05-17

Family

ID=10864257

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2000/004186 WO2001034381A1 (fr) 1999-11-11 2000-11-02 Renfort pour element stratifie d'un aeronef

Country Status (4)

Country Link
JP (1) JP2003513821A (fr)
AU (1) AU1155501A (fr)
GB (1) GB9926579D0 (fr)
WO (1) WO2001034381A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014038837A1 (fr) * 2012-09-04 2014-03-13 한국항공우주연구원 Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée
US8968500B2 (en) 2009-03-19 2015-03-03 Airbus Operations Gmbh Method and device for adhesively joining large-surface components in vehicle construction
US9011618B2 (en) 2009-03-19 2015-04-21 Airbus Operations Gmbh Method for applying adhesive according to tolerance in vehicle construction
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
US9475568B2 (en) 2012-02-29 2016-10-25 Mitsubishi Heavy Industries, Ltd. Composite structure, aircraft wing and aircraft fuselage including composite structure, and method of manufacturing composite structure
EP3173334A1 (fr) * 2015-11-25 2017-05-31 The Boeing Company Rails de siège dotés de cadres composites
US11772775B2 (en) 2018-11-19 2023-10-03 The Boeing Company Shear ties for aircraft wing

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100932302B1 (ko) * 2007-09-17 2009-12-16 한국항공우주연구원 핀을 박아 성능을 보강한 복합재 적층 구조물, 상기 복합재적층 구조물 제조 방법, 장치 및 상기 장치 제작 방법
JP5808111B2 (ja) 2011-02-04 2015-11-10 三菱重工業株式会社 航空機用複合材構造体、これを備えた航空機主翼および航空機胴体
CA2815966C (fr) * 2011-02-04 2017-09-19 Mitsubishi Heavy Industries, Ltd. Structure en materiau composite, et aile et fuselage d'avion comprenant celle-ci
JP5808112B2 (ja) 2011-02-04 2015-11-10 三菱重工業株式会社 複合材構造体およびこれを備えた航空機主翼

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4046933A (en) * 1975-09-16 1977-09-06 Ppg Industries, Inc. Laminated window structure and its method of fabrication
US4331495A (en) * 1978-01-19 1982-05-25 Rockwell International Corporation Method of fabricating a reinforced composite structure
GB2238283A (en) * 1989-11-08 1991-05-29 Royal Ordnance Plc Protecting aircraft structures from the effects of explosions
EP0580417A1 (fr) * 1992-07-24 1994-01-26 British Aerospace Public Limited Company Bouclier de protection contre la foudre
US5429326A (en) * 1992-07-09 1995-07-04 Structural Laminates Company Spliced laminate for aircraft fuselage
US5980665A (en) * 1996-05-31 1999-11-09 The Boeing Company Z-pin reinforced bonds for connecting composite structures

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4046933A (en) * 1975-09-16 1977-09-06 Ppg Industries, Inc. Laminated window structure and its method of fabrication
US4331495A (en) * 1978-01-19 1982-05-25 Rockwell International Corporation Method of fabricating a reinforced composite structure
GB2238283A (en) * 1989-11-08 1991-05-29 Royal Ordnance Plc Protecting aircraft structures from the effects of explosions
US5429326A (en) * 1992-07-09 1995-07-04 Structural Laminates Company Spliced laminate for aircraft fuselage
EP0580417A1 (fr) * 1992-07-24 1994-01-26 British Aerospace Public Limited Company Bouclier de protection contre la foudre
US5980665A (en) * 1996-05-31 1999-11-09 The Boeing Company Z-pin reinforced bonds for connecting composite structures

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8968500B2 (en) 2009-03-19 2015-03-03 Airbus Operations Gmbh Method and device for adhesively joining large-surface components in vehicle construction
US9011618B2 (en) 2009-03-19 2015-04-21 Airbus Operations Gmbh Method for applying adhesive according to tolerance in vehicle construction
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
US9475568B2 (en) 2012-02-29 2016-10-25 Mitsubishi Heavy Industries, Ltd. Composite structure, aircraft wing and aircraft fuselage including composite structure, and method of manufacturing composite structure
WO2014038837A1 (fr) * 2012-09-04 2014-03-13 한국항공우주연구원 Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée
EP3173334A1 (fr) * 2015-11-25 2017-05-31 The Boeing Company Rails de siège dotés de cadres composites
US10556691B2 (en) 2015-11-25 2020-02-11 The Boeing Company Seat tracks with composite frames
RU2719619C2 (ru) * 2015-11-25 2020-04-21 Зе Боинг Компани Направляющие сидений с композитными каркасами
US10994847B2 (en) 2015-11-25 2021-05-04 The Boeing Company Seat tracks with composite frames
US11772775B2 (en) 2018-11-19 2023-10-03 The Boeing Company Shear ties for aircraft wing

Also Published As

Publication number Publication date
AU1155501A (en) 2001-06-06
GB9926579D0 (en) 2000-01-12
JP2003513821A (ja) 2003-04-15

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