FR2241410B1 - - Google Patents

Info

Publication number
FR2241410B1
FR2241410B1 FR7318135A FR7318135A FR2241410B1 FR 2241410 B1 FR2241410 B1 FR 2241410B1 FR 7318135 A FR7318135 A FR 7318135A FR 7318135 A FR7318135 A FR 7318135A FR 2241410 B1 FR2241410 B1 FR 2241410B1
Authority
FR
France
Prior art keywords
fibres
epoxy resin
sheet
boron
sheets
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
Application number
FR7318135A
Other languages
French (fr)
Other versions
FR2241410A1 (en
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.)
Dassault Aviation SA
Original Assignee
Avions Marcel Dassault Breguet Aviation SA
Dassault Aviation SA
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 Avions Marcel Dassault Breguet Aviation SA, Dassault Aviation SA filed Critical Avions Marcel Dassault Breguet Aviation SA
Priority to FR7318135A priority Critical patent/FR2241410B1/fr
Priority to GB2098274A priority patent/GB1468030A/en
Priority to DE2424068A priority patent/DE2424068C3/en
Publication of FR2241410A1 publication Critical patent/FR2241410A1/fr
Application granted granted Critical
Publication of FR2241410B1 publication Critical patent/FR2241410B1/fr
Expired legal-status Critical Current

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
    • 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
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • 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
    • B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • 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
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
    • B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
    • B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2063/00—Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/0809—Fabrics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2307/00—Use of elements other than metals as reinforcement
    • B29K2307/02—Boron
    • 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)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)

Abstract

1468030 Repairing aircraft structures AVIONS MARCEL DASSAULT-BREGUET AVIATION 13 May 1974 [18 May 1973] 20982/74 Heading B7W [Also in Divisions B5 and D1] A method of producing a laminated patch or reinforcement on a surface of an aircraft comprises cleaning the surface to be covered and depositing thereon an epoxy resin associated with a fibrous reinforcement, the reinforcement consisting of coherent sheets of parallel boron fibres interwoven with transverse fibres of another material, the sheets being not prior coated and being superposed and coated with a cold-hardenable epoxy resin. The sheet shown in Fig. 1 comprises boron fibres 1 almost in contact and spaced transverse fibres 2 of another material, e.g. polyester or glass fibres, the fibres 2 being extended a few millimetres at the two edges of the sheet and woven together with glass or polyester fibres or filaments 3, parallel to the boron fibres to form safety borders holding the boron fibres in position. In the embodiment described with reference to Figs. 2 and 3, a patch is applied to an aircraft skin having two fuselage elements 4, 5 assembled end-to-end with back plate 6 positioned underneath and attached thereto by countersunk rivets 7, fatigue having developed a crack 8 between two rivets. In forming the patch, the surface is cleaned with a mixture of sulphuric and chromic acids, rinsed and coated with a dilute epoxy resin containing a cold hardener which is allowed to dry prior to the application of a commercial concentration epoxy resin containing a cold hardener. This coating being immediately overlaid with a sheet of the boron fibres, the boron fibres being parallel to the crack and the sheet impregnated, e.g. by brushing with the epoxy resin/hardener, further sheets up to desired number being applied by similar methods. The assembly is overlaid with a sheet 10 of plastics material and vacuum applied through connector 12 until the epoxy resin is cured and the sheet 10 removed, the sheets being preferably of decreasing width.
FR7318135A 1973-05-18 1973-05-18 Expired FR2241410B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR7318135A FR2241410B1 (en) 1973-05-18 1973-05-18
GB2098274A GB1468030A (en) 1973-05-18 1974-05-13 Laminatedstructures
DE2424068A DE2424068C3 (en) 1973-05-18 1974-05-17 Process for the production of a composite layer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7318135A FR2241410B1 (en) 1973-05-18 1973-05-18

Publications (2)

Publication Number Publication Date
FR2241410A1 FR2241410A1 (en) 1975-03-21
FR2241410B1 true FR2241410B1 (en) 1976-05-07

Family

ID=9119565

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7318135A Expired FR2241410B1 (en) 1973-05-18 1973-05-18

Country Status (3)

Country Link
DE (1) DE2424068C3 (en)
FR (1) FR2241410B1 (en)
GB (1) GB1468030A (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2650859C3 (en) * 1976-11-06 1979-10-04 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Process for the production of large components from fiber-reinforced plastic and device for carrying out the process
FR2497726A1 (en) * 1981-01-12 1982-07-16 Brochier Fils J MULTILAYER TEXTILE ARTICLE FOR REINFORCING LAMINATED MATERIALS AND PROCESS FOR OBTAINING THE SAME
US4842912A (en) * 1985-09-04 1989-06-27 Physical Systems, Inc. Adhesive attachment and mounting fixture
US4778702A (en) * 1985-09-04 1988-10-18 Physical Systems, Inc. Adhesive attachment and mounting fixture
US4822656A (en) * 1985-09-04 1989-04-18 Physical Systems, Inc. Fixture for securing an adhesive attachment to a substrate
GB2203713A (en) * 1987-03-10 1988-10-26 Fischer Gmbh Removable or hinged component for covering openings in the fuselage of an aircraft
AT390771B (en) * 1988-02-19 1990-06-25 Fischer Gmbh Component which can be removed or pivoted, for lining (cladding) openings in the fuselage of an aircraft
GB201115080D0 (en) 2011-09-01 2011-10-19 Airbus Operations Ltd An aircraft structure
US20180208330A1 (en) 2015-07-23 2018-07-26 Sikorsky Aircraft Corporation Structure reinforcement with polymer matrix composite
CN113146142A (en) * 2021-04-14 2021-07-23 芜湖创联新材料科技有限公司 Device and method for rapidly repairing cracks on hole edge of metal skin of airplane by using composite material

Also Published As

Publication number Publication date
GB1468030A (en) 1977-03-23
DE2424068A1 (en) 1974-12-05
DE2424068B2 (en) 1977-12-15
FR2241410A1 (en) 1975-03-21
DE2424068C3 (en) 1978-08-10

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Legal Events

Date Code Title Description
ST Notification of lapse