FR2440831A1 - Panels with ancillary ribs of resin contg. high tensile fibres - are made by compression using moulds which exclude excess resin - Google Patents

Panels with ancillary ribs of resin contg. high tensile fibres - are made by compression using moulds which exclude excess resin

Info

Publication number
FR2440831A1
FR2440831A1 FR7831442A FR7831442A FR2440831A1 FR 2440831 A1 FR2440831 A1 FR 2440831A1 FR 7831442 A FR7831442 A FR 7831442A FR 7831442 A FR7831442 A FR 7831442A FR 2440831 A1 FR2440831 A1 FR 2440831A1
Authority
FR
France
Prior art keywords
resin
impregnated
fibres
core
panels
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.)
Granted
Application number
FR7831442A
Other languages
French (fr)
Other versions
FR2440831B1 (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 FR7831442A priority Critical patent/FR2440831A1/en
Publication of FR2440831A1 publication Critical patent/FR2440831A1/en
Application granted granted Critical
Publication of FR2440831B1 publication Critical patent/FR2440831B1/fr
Granted legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • 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
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • 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
    • 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
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D22/00—Producing hollow articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/24—Moulded or cast structures
    • 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
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C2027/4733—Rotor blades substantially made from particular materials
    • B64C2027/4736—Rotor blades substantially made from particular materials from composite materials
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Panels made of high tensile filaments impregnated with resin are stiffened by a series of ribs of composite structure having a core of resin-impregnated aligned fibres between zones of similar structure to the surface skin and laminated thereto. The covers of stiffeners are prefabricated in the form of 'U' profiles moulded over a core of material having a relatively high coefft. of thermal expansion, e.g. silicone rubber sleeves over a solid bar. Dilation of the core at moulding temps. compresses the impregnated filaments to express excess resin. Sets of parallel covers are laminated to the main panel, while the gap between adjacent webs is filled with aligned impregnated fibres and the composite lay-up is consolidated by pressure from an impermeable flexible cover over an evacuated mould. Suitable for mfr. of curved semi structural panels for aerofoils etc. to minimise the need for an ancillary skeleton. Esp. claimed are structures reinforced with fibres of c or B impregnated with e.g. epoxy resin.
FR7831442A 1978-11-07 1978-11-07 Panels with ancillary ribs of resin contg. high tensile fibres - are made by compression using moulds which exclude excess resin Granted FR2440831A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7831442A FR2440831A1 (en) 1978-11-07 1978-11-07 Panels with ancillary ribs of resin contg. high tensile fibres - are made by compression using moulds which exclude excess resin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7831442A FR2440831A1 (en) 1978-11-07 1978-11-07 Panels with ancillary ribs of resin contg. high tensile fibres - are made by compression using moulds which exclude excess resin

Publications (2)

Publication Number Publication Date
FR2440831A1 true FR2440831A1 (en) 1980-06-06
FR2440831B1 FR2440831B1 (en) 1981-10-16

Family

ID=9214554

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7831442A Granted FR2440831A1 (en) 1978-11-07 1978-11-07 Panels with ancillary ribs of resin contg. high tensile fibres - are made by compression using moulds which exclude excess resin

Country Status (1)

Country Link
FR (1) FR2440831A1 (en)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2533013A1 (en) * 1982-09-09 1984-03-16 Alkan R & Cie METHOD FOR IMPLANTING A METAL REINFORCEMENT IN A FIBER-RESIN COMPOSITE MATERIAL STRUCTURE
FR2638673A1 (en) * 1988-11-08 1990-05-11 Aerospatiale TOOLS FOR MOLDING SELF-RAIDED PANELS OF COMPOSITE MATERIAL
WO1992018324A1 (en) * 1991-04-19 1992-10-29 United Technologies Corporation Elliptically ended stiffener for composite structural member, and moulding method for its manufacture
EP0758607A3 (en) * 1995-08-11 1998-04-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Shear-proof aircraft wing box formed from fibre reinforced material
EP0862978A1 (en) * 1997-03-06 1998-09-09 Hispano-Suiza Aerostructures Method of manufacturing hollow articles from a composite material
EP1134070A1 (en) * 2000-03-07 2001-09-19 Construcciones Aeronauticas, S.A. Process for manufacturing pre-cured parts of composite material with green-applied stiffeners
EP0976650A3 (en) * 1998-07-30 2002-06-05 Fuji Jukogyo Kabushiki Kaisha Composite aircraft structures and their fabrication methods
EP1231046A2 (en) * 2001-02-13 2002-08-14 Eads Construcciones Aeronauticas S.A. Method for manufacturing elements of composite materials by the cobonding technique
EP1666354A1 (en) * 2004-12-01 2006-06-07 Airbus Deutschland GmbH Structural component, process for manufacturing a structural component and use of a structural component for an aircraft skin
US7198097B2 (en) * 2003-12-18 2007-04-03 Valeo, Inc. Angled ribs for heat exchanger tanks
GB2447271A (en) * 2007-03-06 2008-09-10 Rolls Royce Plc A composite reinforced structure
WO2008132251A1 (en) * 2007-04-30 2008-11-06 Airbus España, S.L. Multispar torsion box made from composite material
US7546864B2 (en) 2000-09-07 2009-06-16 Airbus Uk Limited Stiffening means for structural components, method of manufacturing and apparatus therefor
WO2010092309A1 (en) 2009-02-16 2010-08-19 Airbus Operations Sas Method for making a stiffened panel made of a composite material
WO2013178917A1 (en) * 2012-05-29 2013-12-05 Airbus Operations Self-stiffened composite panel and method of producing same
WO2014200393A1 (en) * 2013-06-10 2014-12-18 Saab Ab Manufacturing method and apparatus for stringer reinforced composite skin
EP2815862A1 (en) * 2006-08-14 2014-12-24 Airbus Operations Limited Moulding tool and method for manufacturing a hollow part
FR3015347A1 (en) * 2013-12-19 2015-06-26 Aerolia DEVICE AND METHOD FOR MANUFACTURING A SELF-RAIDI PANEL OF COMPOSITE MATERIAL
US9597844B2 (en) 2012-12-20 2017-03-21 Airbus Operations (S.A.S.) Process for manufacturing a textile preform with continuous fibres by circulation of hot gas flow through a fibrous array
US10443409B2 (en) 2016-10-28 2019-10-15 Rolls-Royce North American Technologies Inc. Turbine blade with ceramic matrix composite material construction
US10577939B2 (en) 2016-11-01 2020-03-03 Rolls-Royce Corporation Turbine blade with three-dimensional CMC construction elements

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110450937B (en) * 2019-08-23 2020-12-04 中国商用飞机有限责任公司北京民用飞机技术研究中心 I-shaped long-purlin wallboard structure made of composite material, forming die and forming method

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410609A (en) * 1943-07-17 1946-11-05 Joseph S Pecker Aircraft rotor wing construction
US2572924A (en) * 1948-07-07 1951-10-30 Holoplast Ltd Hollow plastic product and method of making the same
DE1949209A1 (en) * 1969-09-30 1971-04-01 Fritz Reinke Method and device for manufacturing components
FR2088413A1 (en) * 1970-05-08 1972-01-07 Ibm

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410609A (en) * 1943-07-17 1946-11-05 Joseph S Pecker Aircraft rotor wing construction
US2572924A (en) * 1948-07-07 1951-10-30 Holoplast Ltd Hollow plastic product and method of making the same
DE1949209A1 (en) * 1969-09-30 1971-04-01 Fritz Reinke Method and device for manufacturing components
FR2088413A1 (en) * 1970-05-08 1972-01-07 Ibm

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2533013A1 (en) * 1982-09-09 1984-03-16 Alkan R & Cie METHOD FOR IMPLANTING A METAL REINFORCEMENT IN A FIBER-RESIN COMPOSITE MATERIAL STRUCTURE
EP0103518A1 (en) * 1982-09-09 1984-03-21 R. ALKAN & Cie. Metallic reinforcement for implantation in a junction of a fibres-resin composite material structure
FR2638673A1 (en) * 1988-11-08 1990-05-11 Aerospatiale TOOLS FOR MOLDING SELF-RAIDED PANELS OF COMPOSITE MATERIAL
EP0368734A1 (en) * 1988-11-08 1990-05-16 AEROSPATIALE Société Nationale Industrielle Moulding device for composite self-reinforced panels
US5015168A (en) * 1988-11-08 1991-05-14 Societe Nationale Industrielle Et Aerospatiale Tool for moulding self-stiffened panels made from a composite material
WO1992018324A1 (en) * 1991-04-19 1992-10-29 United Technologies Corporation Elliptically ended stiffener for composite structural member, and moulding method for its manufacture
US5271986A (en) * 1991-04-19 1993-12-21 United Technologies Corporation Structural member having a stiffener bead therein and comprising plies of composite material extending for the full length and width of the structural member and continuously through the stiffener bead, and the article so made
EP0758607A3 (en) * 1995-08-11 1998-04-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Shear-proof aircraft wing box formed from fibre reinforced material
EP0862978A1 (en) * 1997-03-06 1998-09-09 Hispano-Suiza Aerostructures Method of manufacturing hollow articles from a composite material
FR2760399A1 (en) * 1997-03-06 1998-09-11 Hispano Suiza Sa PROCESS FOR THE MANUFACTURE OF HOLLOW PARTS OF COMPOSITE MATERIAL
WO1998039151A1 (en) * 1997-03-06 1998-09-11 Hispano Suiza Aerostructures Method for making hollow parts of composite material
EP0976650A3 (en) * 1998-07-30 2002-06-05 Fuji Jukogyo Kabushiki Kaisha Composite aircraft structures and their fabrication methods
US6508909B1 (en) 2000-03-07 2003-01-21 Construcciones Aeronauticas S.A. Process for manufacturing pre-cured parts of composite material with green-applied stiffeners
ES2185443A1 (en) * 2000-03-07 2003-04-16 Airbus Espana Sl Process for manufacturing pre-cured parts of composite material with green-applied stiffeners
EP1134070A1 (en) * 2000-03-07 2001-09-19 Construcciones Aeronauticas, S.A. Process for manufacturing pre-cured parts of composite material with green-applied stiffeners
US7546864B2 (en) 2000-09-07 2009-06-16 Airbus Uk Limited Stiffening means for structural components, method of manufacturing and apparatus therefor
EP1231046A2 (en) * 2001-02-13 2002-08-14 Eads Construcciones Aeronauticas S.A. Method for manufacturing elements of composite materials by the cobonding technique
EP1231046A3 (en) * 2001-02-13 2002-10-30 Eads Construcciones Aeronauticas S.A. Method for manufacturing elements of composite materials by the cobonding technique
ES2205961A1 (en) * 2001-02-13 2004-05-01 Eads Construcciones Aeronauticas, S.A. Method for manufacturing elements of composite materials by the cobonding technique
US7198097B2 (en) * 2003-12-18 2007-04-03 Valeo, Inc. Angled ribs for heat exchanger tanks
US7850118B2 (en) 2004-12-01 2010-12-14 Airbus Deutschland Gmbh Structural element, method for manufacturing a structural element and use of a structural element for an aircraft hull
EP1666354A1 (en) * 2004-12-01 2006-06-07 Airbus Deutschland GmbH Structural component, process for manufacturing a structural component and use of a structural component for an aircraft skin
US9481115B2 (en) 2006-08-14 2016-11-01 Airbus Operations Limited Moulding tool and method of manufacturing a part
EP2815862A1 (en) * 2006-08-14 2014-12-24 Airbus Operations Limited Moulding tool and method for manufacturing a hollow part
GB2447271A (en) * 2007-03-06 2008-09-10 Rolls Royce Plc A composite reinforced structure
GB2447271B (en) * 2007-03-06 2010-02-17 Rolls Royce Plc A composite structure
US8715809B2 (en) 2007-03-06 2014-05-06 Rolls-Royce Plc Composite structure
WO2008132251A1 (en) * 2007-04-30 2008-11-06 Airbus España, S.L. Multispar torsion box made from composite material
WO2010092309A1 (en) 2009-02-16 2010-08-19 Airbus Operations Sas Method for making a stiffened panel made of a composite material
FR2942165A1 (en) * 2009-02-16 2010-08-20 Airbus France METHOD FOR MANUFACTURING A RAIDI PANEL IN COMPOSITE MATERIAL
GB2520438A (en) * 2012-05-29 2015-05-20 Airbus Operations Sas Self-stiffened composite panel and method of producing same
CN104428127A (en) * 2012-05-29 2015-03-18 空中客车运营简化股份公司 Self-stiffened composite panel and method of producing same
FR2991228A1 (en) * 2012-05-29 2013-12-06 Airbus Operations Sas METHOD AND DEVICE FOR MAKING A SELF-RAIDI COMPOSITE PANEL
WO2013178917A1 (en) * 2012-05-29 2013-12-05 Airbus Operations Self-stiffened composite panel and method of producing same
GB2520438B (en) * 2012-05-29 2017-07-26 Airbus Operations (Societe Par Actions Simplifiee) Self-stiffened composite panel and method of producing same
US10105938B2 (en) 2012-05-29 2018-10-23 Airbus Operations (S.A.S.) Self-stiffened composite panel and method of producing same
US9597844B2 (en) 2012-12-20 2017-03-21 Airbus Operations (S.A.S.) Process for manufacturing a textile preform with continuous fibres by circulation of hot gas flow through a fibrous array
WO2014200393A1 (en) * 2013-06-10 2014-12-18 Saab Ab Manufacturing method and apparatus for stringer reinforced composite skin
FR3015347A1 (en) * 2013-12-19 2015-06-26 Aerolia DEVICE AND METHOD FOR MANUFACTURING A SELF-RAIDI PANEL OF COMPOSITE MATERIAL
US10443409B2 (en) 2016-10-28 2019-10-15 Rolls-Royce North American Technologies Inc. Turbine blade with ceramic matrix composite material construction
US10577939B2 (en) 2016-11-01 2020-03-03 Rolls-Royce Corporation Turbine blade with three-dimensional CMC construction elements

Also Published As

Publication number Publication date
FR2440831B1 (en) 1981-10-16

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