WO2007148301A2 - Appareil et procédé de fabrication d'un tronçon de fuselage - Google Patents

Appareil et procédé de fabrication d'un tronçon de fuselage Download PDF

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Publication number
WO2007148301A2
WO2007148301A2 PCT/IB2007/052396 IB2007052396W WO2007148301A2 WO 2007148301 A2 WO2007148301 A2 WO 2007148301A2 IB 2007052396 W IB2007052396 W IB 2007052396W WO 2007148301 A2 WO2007148301 A2 WO 2007148301A2
Authority
WO
WIPO (PCT)
Prior art keywords
mandrel
sectors
radially
circumferentially
fuselage section
Prior art date
Application number
PCT/IB2007/052396
Other languages
English (en)
Other versions
WO2007148301A3 (fr
Inventor
Claudio Berionni
Adriano Moreggia
Original Assignee
Alenia Aeronautica S.P.A.
Moreggia S.P.A.
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 Alenia Aeronautica S.P.A., Moreggia S.P.A. filed Critical Alenia Aeronautica S.P.A.
Publication of WO2007148301A2 publication Critical patent/WO2007148301A2/fr
Publication of WO2007148301A3 publication Critical patent/WO2007148301A3/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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
    • B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
    • B29C33/485—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling cores or mandrels
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/80—Component parts, details or accessories; Auxiliary operations
    • B29C53/82—Cores or mandrels
    • B29C53/821—Mandrels especially adapted for winding and joining
    • B29C53/824—Mandrels especially adapted for winding and joining collapsible, e.g. elastic or inflatable; with removable parts, e.g. for regular shaped, straight tubular articles
    • 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
    • B29C70/32—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 on a rotating mould, former or core
    • 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
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3082—Fuselages

Definitions

  • the present invention relates to apparatus and a method for fabricating a large-diameter fuselage section, using laminated composite materials.
  • Fibre tapes preimpregnated with resin are automatically deposited by means of one or more delivery heads of a machine on the outer surface of a mandrel having the shape of a solid of rotation about a given axis.
  • the delivery heads of the machine and the mandrel are moved relatively to each other in such a way that the heads apply the tape to the mandrel with a relative translational and rotary movement with respect to the axis of the mandrel.
  • This forms the "skin" of a fuselage section of composite laminate on the outer surface of the mandrel.
  • Machines for the automatic lay-up of composite tapes are described in patent publications WO 2005/082604 A2, WO 2005/018918 Al and WO 2005/018917 A2.
  • the outer surface of the mandrel which forms what is known as the "inner mould line”
  • the outer surface of the mandrel is composed of a plurality of circumferentially adjacent sectors, which are mounted removably on a support structure. These sectors have a set of external longitudinal cavities for receiving corresponding longitudinal reinforcing elements or "stringers”.
  • a set of metal panels is applied around the outer perimeter of the laminate to form what is known as the "outer mould line". The whole assembly is wrapped in a vacuum bag and subjected to a single curing cycle in an autoclave.
  • the sectors making up the mandrel must be mounted on the support structure before lamination and must be dismounted at the end of the polymerization stage.
  • the mounting and dismounting operations are rather lengthy. It is also necessary to have considerable space available around the lay-up machine in which the mandrel sectors can be placed when they have been dismounted.
  • the dismounting operations which must be carried out carefully in order not to damage the cured product, are also complicated by the fact that the cured material adheres to the outer surfaces of the mandrel sectors.
  • the object of the invention is to overcome the aforementioned drawbacks, and in particular to accelerate the fabrication process and optimize the available space in the operating environment. It is also desirable to reduce the risk of damaging the cured product, to produce a fuselage section whose shape and dimensions are within specified tolerances, and to facilitate the cleaning of the mandrel surfaces between two consecutive production cycles.
  • Figures 1 and 2 are a perspective view and a side view of apparatus according to the invention
  • Figure 3 is a perspective view of the apparatus of Figures 1 and 2 without the mandrel sectors;
  • Figure 4 is an exploded view taken in the direction of the arrow IV in Figure 3;
  • Figure 5 is a perspective view of a device for driving a mandrel sector
  • Figures 6 and 7 are schematic front views taken in the direction of the arrow IV in Figure 3, showing the apparatus in two different operating positions;
  • Figures 8-10 are perspective views showing locking devices for locking two adjacent mandrel sectors together.
  • apparatus 10 comprises a mandrel 11 whose outer surface is capable of taking substantially the form of a solid of rotation about a central axis x.
  • the outer surface of the mandrel is cylindrical, for the fabrication of a median portion or section of the fuselage of an aircraft; however, the invention is equally applicable to the making of fuselage sections of tapered or other shapes, according to requirements.
  • the mandrel 11 is supported by an inner lattice structure 12 in the form of a hexagonal prism ( Figure 3), opposite ends of which are supported rotatably about the axis x by means of conical supports 13.
  • Two sets of mandrel sectors 14 and 15 ( Figures 6 and 7) are mounted on the lattice structure 12, being positioned alternately in the circumferential direction.
  • the radially outer surfaces 14a and 15a of all the mandrel sectors serve to define, in combination, in the operating position shown in Figure 6, a circumferentially continuous outer surface on which fibre tapes preimpregnated with resin are automatically deposited.
  • These tapes are deposited by one or more tape delivery heads of a machine which is not shown. The tapes are deposited by making the mandrel rotate about the axis x, while simultaneously translating the tape delivery heads in axial directions in coordination with the rotation of the mandrel.
  • each mandrel sector is fixed to a corresponding block 16 mounted in a radially slidable manner in a corresponding pair of lateral guides 17 (shown in figure 5) fixed to the lattice structure 12.
  • the blocks 16 are moved by driving units comprising an electric motor (not shown), a transmission shaft 18, geared reduction units 19 and helical gear and worm mechanisms which cause the radial translation of the sectors 14 and 15. In this way the sectors can be moved to a radially expanded position ( Figure 6) and a radially retracted position ( Figure 7).
  • the sectors are circumferentially adjacent and thus form, in combination, a circumferentially continuous surface on which the preimpregnated fibre tapes to be cured are deposited for the fabrication of the fuselage section.
  • longitudinal reinforcing elements or "stringers” (not shown) are initially placed in longitudinal cavities 20 formed on the outer surfaces of the sectors.
  • the mandrel is then rotated about the axis x by means of a drive system (not shown), simultaneously with the synchronized operation of the heads of the aforesaid machine which deposits the preimpregnated fibre tape material around the mandrel.
  • the fibre material On completion of the deposition stage, the fibre material is covered with metal panels, wrapped in a vacuum bag and subject to a curing cycle in an autoclave.
  • pairs of gripping members (not shown) positioned at the opposite ends of the mandrel grip the cured body B and tension it longitudinally, in order to support it during the subsequent stage of withdrawal of the mandrel and in order to prevent it from bending to a degree that would damage it.
  • the mandrel sectors which make up the lay-up surface for the tape material preimpregnated with resin do not have to be dismounted and remounted on the apparatus, and the fuselage section production cycles can therefore be accelerated. Since it is unnecessary to provide free space for the temporary location of mandrel sectors dismounted from the apparatus, the space within the factory shed can be optimized. The radial movements of expansion and radial retraction of the sectors can be guided precisely so as to provide a good seal between the adjacent sectors.
  • the hermetic seal between the sectors 14 and 15 in the radially expanded position can be improved further by means of a system of locking devices 21 which are mechanically operated (Figure 8) or pneumatically operated ( Figures 9 and 10), and which, being mounted on the different sectors, operate corresponding hooks 22, each of which, on moving from an open position ( Figure 10) to a closed position ( Figure 9), engages with a corresponding securing pin 23 carried by the adjacent sector, thus tightly locking each pair of adjacent sectors and compressing gaskets (not shown) positioned on the interface along the facing edges of each pair of consecutive sectors.
  • the locking devices 21 also ensure that the edge portions of the outer surfaces of every two consecutive sectors are coaxial, thus preventing the formation of undesirable projections in the fuselage section in the areas of the joints between the sectors.
  • the dimensions and shape of the resulting fuselage section are especially precise if the mandrel sectors 14 and 15 are made from a metal alloy having a low coefficient of thermal expansion, such as an iron alloy with a 36% nickel content, known as Invar 36, which maintains virtually constant dimensions throughout the normal atmospheric temperature range while having a low coefficient of thermal expansion up to about 500 0 C.
  • the outer surfaces of metal alloy are wear-resistant and can also be cleaned easily at the end of each polymerization cycle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Robotics (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

L'invention concerne une section de fuselage (B) fabriquée en déposant automatiquement des rubans en fibre préimbibés de résine sur une surface extérieure d'un mandrin cylindrique (11) composé de secteurs de mandrin radialement rétractables (14, 15).
PCT/IB2007/052396 2006-06-23 2007-06-21 Appareil et procédé de fabrication d'un tronçon de fuselage WO2007148301A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITTO2006A000463 2006-06-23
ITTO20060463 ITTO20060463A1 (it) 2006-06-23 2006-06-23 Apparecchiatura e procedimento per la fabbricazione di un tronco di fusoliera

Publications (2)

Publication Number Publication Date
WO2007148301A2 true WO2007148301A2 (fr) 2007-12-27
WO2007148301A3 WO2007148301A3 (fr) 2008-03-06

Family

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Application Number Title Priority Date Filing Date
PCT/IB2007/052396 WO2007148301A2 (fr) 2006-06-23 2007-06-21 Appareil et procédé de fabrication d'un tronçon de fuselage

Country Status (2)

Country Link
IT (1) ITTO20060463A1 (fr)
WO (1) WO2007148301A2 (fr)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2062814A1 (fr) * 2006-08-31 2009-05-27 Airbus Espana, S.L. Composants tubulaires pour fuselages aéronautiques et procédés et outils de fabrication
GB2460741A (en) * 2008-06-13 2009-12-16 Advanced Composites Group Ltd Tooling for the manufacture of composite structures
EP2181043A1 (fr) * 2007-07-31 2010-05-05 Vought Aircraft Industries, Inc. Configuration de joint de mandrin de positionnement de fibre automatisé
WO2011070002A1 (fr) * 2009-12-07 2011-06-16 Airbus Operations Gmbh Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres
FR2953754A1 (fr) * 2009-12-16 2011-06-17 Airbus Operations Sas Outillage pour la fabrication d'un panneau en materiau composite, en particulier d'un fuselage d'aeronef
EP2572852A1 (fr) * 2011-09-26 2013-03-27 Rolls-Royce plc Mandrin pour former un composant
WO2013102462A1 (fr) * 2012-01-04 2013-07-11 Dencam Composite A/S Structure de maître-modèle
EP2631062A1 (fr) * 2012-02-27 2013-08-28 The Boeing Company Positionnement de fibre automatisé comprenant un outil de mandrinage de superposition
ITTO20120287A1 (it) * 2012-03-30 2013-10-01 Alenia Aermacchi Spa Sistema posizionamento settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo
ITTO20120286A1 (it) * 2012-03-30 2013-10-01 Alenia Aermacchi Spa Sistema di vincolo settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo
ITTO20120285A1 (it) * 2012-03-30 2013-10-01 Alenia Aermacchi Spa Sistema bloccaggio settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo
WO2013153537A2 (fr) 2012-04-12 2013-10-17 Alenia Aermacchi S.P.A. Procédé de fabrication de corps de cylindre en une seule pièce dans un matériau composite
JP2013212833A (ja) * 2012-03-30 2013-10-17 Alenia Aermacchi Spa 航空機胴体を製造するためのデバイスの扇状体を作動させるシステム
US20130340927A1 (en) * 2010-11-19 2013-12-26 Klaus Schuermann Method and device for producing large cylindrical structures
US20140008015A1 (en) * 2011-02-07 2014-01-09 Airbus Operations Gmbh Setup device and method for manufacturing a fuselage barrel for an aircraft
WO2013009907A3 (fr) * 2011-07-12 2014-02-20 The Boeing Company Support rotatif pour mandrin
WO2015028736A1 (fr) * 2013-08-28 2015-03-05 Aircelle Outillage à clés et panneau composite notamment pour nacelle de moteur d'aéronef fabriqué à l'aide d'un tel outillage
EP2517857A4 (fr) * 2009-12-25 2015-09-23 Kawasaki Heavy Ind Ltd Moule de fabrication d'une structure de matériau composite
EP2944454A1 (fr) * 2014-05-15 2015-11-18 The Boeing Company Procédé et appareil pour outillage d'empilement
US10173348B2 (en) 2015-09-14 2019-01-08 Bell Helicopter Textron Inc. Modular mandrel for monolithic composite fuselage
US10906210B2 (en) 2017-01-25 2021-02-02 The Boeing Company Mandrel for composite part fabrication and repair
FR3100232A1 (fr) * 2019-08-30 2021-03-05 Airbus Ensemble comportant une tour support et au moins deux systemes de support pour des panneaux d’un troncon de fuselage d’un aeronef
US20210299958A1 (en) * 2020-03-28 2021-09-30 Karl Joseph Dodds Gifford Shrinkable platform for 3D printer
EP4015182A1 (fr) * 2020-12-18 2022-06-22 The Boeing Company Mandrin segmenté pour fabrication composite
EP4067040A1 (fr) 2021-04-01 2022-10-05 Airbus Operations Outil pour la fabrication d'un panneau auto-raidi et procédé de fabrication d'un panneau auto-raidi utilisant un tel outil
IT202200007511A1 (it) * 2022-04-14 2023-10-14 Leonardo Spa Attrezzatura e procedimento per la realizzazione di un elemento strutturale in materiale composito

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1467476A (fr) * 1966-02-03 1967-01-27 Mandrin de moulage à section réductible
DE2011566A1 (en) * 1970-03-11 1971-09-23 Robert Adam & Sohn Ohg Und App Adjustable core for moulding reinforced synt
US4436574A (en) * 1982-12-13 1984-03-13 Eagle-Picher Industries, Inc. Radial mandrel
EP0206268A2 (fr) * 1985-06-21 1986-12-30 BASF Aktiengesellschaft Axe de bobinage pour fabriquer des corps tubulaires en faisceaux de fibres imprégnés de résine
CA2299487A1 (fr) * 2000-02-24 2001-08-24 Lembit Siilats Mandrin retractable
EP1375111A2 (fr) * 2002-06-27 2004-01-02 Airbus France Outillage de moulage à clef notamment pour la réalisation d'entrée d'air sans éclisse
US20050039843A1 (en) * 2003-08-22 2005-02-24 Johnson Brice A. Multiple head automated composite laminating machine for the fabrication of large barrel section components

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1467476A (fr) * 1966-02-03 1967-01-27 Mandrin de moulage à section réductible
DE2011566A1 (en) * 1970-03-11 1971-09-23 Robert Adam & Sohn Ohg Und App Adjustable core for moulding reinforced synt
US4436574A (en) * 1982-12-13 1984-03-13 Eagle-Picher Industries, Inc. Radial mandrel
EP0206268A2 (fr) * 1985-06-21 1986-12-30 BASF Aktiengesellschaft Axe de bobinage pour fabriquer des corps tubulaires en faisceaux de fibres imprégnés de résine
CA2299487A1 (fr) * 2000-02-24 2001-08-24 Lembit Siilats Mandrin retractable
EP1375111A2 (fr) * 2002-06-27 2004-01-02 Airbus France Outillage de moulage à clef notamment pour la réalisation d'entrée d'air sans éclisse
US20050039843A1 (en) * 2003-08-22 2005-02-24 Johnson Brice A. Multiple head automated composite laminating machine for the fabrication of large barrel section components

Cited By (71)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2062814A4 (fr) * 2006-08-31 2012-01-25 Airbus Operations Sl Composants tubulaires pour fuselages aéronautiques et procédés et outils de fabrication
EP2062814A1 (fr) * 2006-08-31 2009-05-27 Airbus Espana, S.L. Composants tubulaires pour fuselages aéronautiques et procédés et outils de fabrication
EP2181043A1 (fr) * 2007-07-31 2010-05-05 Vought Aircraft Industries, Inc. Configuration de joint de mandrin de positionnement de fibre automatisé
EP2181043A4 (fr) * 2007-07-31 2014-05-21 Boeing Co Configuration de joint de mandrin de positionnement de fibre automatisé
US9662843B2 (en) 2008-06-13 2017-05-30 Cytec Industrial Materials (Derby) Limited Tool and method for the manufacture of composite structures
GB2460741A (en) * 2008-06-13 2009-12-16 Advanced Composites Group Ltd Tooling for the manufacture of composite structures
WO2009150401A1 (fr) 2008-06-13 2009-12-17 Advanced Composites Group Limited Outil et procédé pour la fabrication de structures composites
GB2460741B (en) * 2008-06-13 2012-10-10 Umeco Structural Materials Derby Ltd Tooling
WO2011070002A1 (fr) * 2009-12-07 2011-06-16 Airbus Operations Gmbh Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres
US8911585B2 (en) 2009-12-07 2014-12-16 Airbus Operations Gmbh Device and method for manufacturing a fiber-reinforced composite fuselage shell for an aircraft
FR2953754A1 (fr) * 2009-12-16 2011-06-17 Airbus Operations Sas Outillage pour la fabrication d'un panneau en materiau composite, en particulier d'un fuselage d'aeronef
US8869402B2 (en) 2009-12-16 2014-10-28 Airbus Operations (Sas) Methods for manufacturing a tool equipment including a plurality of removable modules and for molding a fuselage panel
EP3444093A1 (fr) * 2009-12-25 2019-02-20 Kawasaki Jukogyo Kabushiki Kaisha Moule de fabrication d'une structure de matériau composite
EP2517857A4 (fr) * 2009-12-25 2015-09-23 Kawasaki Heavy Ind Ltd Moule de fabrication d'une structure de matériau composite
US20130340927A1 (en) * 2010-11-19 2013-12-26 Klaus Schuermann Method and device for producing large cylindrical structures
US9180638B2 (en) * 2010-11-19 2015-11-10 Siempelkamp Maschinen-Und Anlagenbau Gmbh Method and device for producing large cylindrical structures
US20140008015A1 (en) * 2011-02-07 2014-01-09 Airbus Operations Gmbh Setup device and method for manufacturing a fuselage barrel for an aircraft
US10124541B2 (en) 2011-02-07 2018-11-13 Airbus Operations Gmbh Setup device and method for manufacturing a fuselage barrel for an aircraft
US8955206B2 (en) 2011-07-12 2015-02-17 The Boeing Company Method and apparatus for creating a layup of reinforcing fibers
WO2013009907A3 (fr) * 2011-07-12 2014-02-20 The Boeing Company Support rotatif pour mandrin
CN103826831A (zh) * 2011-07-12 2014-05-28 波音公司 旋转心轴工具支撑件
EP2572852A1 (fr) * 2011-09-26 2013-03-27 Rolls-Royce plc Mandrin pour former un composant
US20130074572A1 (en) * 2011-09-26 2013-03-28 Rolls-Royce Plc Mandrel for forming a component
US9289950B2 (en) 2011-09-26 2016-03-22 Rolls-Royce Plc Mandrel for forming a component
WO2013102462A1 (fr) * 2012-01-04 2013-07-11 Dencam Composite A/S Structure de maître-modèle
JP2013173352A (ja) * 2012-02-27 2013-09-05 Boeing Co:The レイアップマンドレルツールを含む自動繊維配置
US8714226B2 (en) 2012-02-27 2014-05-06 The Boeing Company Automated fiber placement including layup mandrel tool
EP2631062A1 (fr) * 2012-02-27 2013-08-28 The Boeing Company Positionnement de fibre automatisé comprenant un outil de mandrinage de superposition
US20130220521A1 (en) * 2012-02-27 2013-08-29 The Boeing Company Automated fiber placement including layup mandrel tool
EP2644359A1 (fr) * 2012-03-30 2013-10-02 Alenia Aermacchi S.p.A. Système de contrainte de secteurs d'un dispositif de fabrication de fuselage d'avion
RU2619403C2 (ru) * 2012-03-30 2017-05-15 Аления Аэрмакки С.П.А Приводная система секторов устройства для изготовления фюзеляжа летательного аппарата
CN103358562A (zh) * 2012-03-30 2013-10-23 阿莱尼亚·马基公司 用于制造飞机机身的装置的扇区的约束系统
CN103358561A (zh) * 2012-03-30 2013-10-23 阿莱尼亚·马基公司 用于对制造飞机机身的装置的扇区进行定位的系统
JP2013212833A (ja) * 2012-03-30 2013-10-17 Alenia Aermacchi Spa 航空機胴体を製造するためのデバイスの扇状体を作動させるシステム
JP2013212686A (ja) * 2012-03-30 2013-10-17 Alenia Aermacchi Spa 航空機胴体を製造するためのデバイスの扇状体を位置付けるシステム
KR102053102B1 (ko) 2012-03-30 2020-01-08 알레니아 아르마치 에스.피.에이. 항공기 기체를 생산하기 위한 장치의 섹터들의 위치조정 시스템
JP2013212685A (ja) * 2012-03-30 2013-10-17 Alenia Aermacchi Spa 航空機胴体を製造するためのデバイスの扇状体を制約するシステム
KR102053090B1 (ko) 2012-03-30 2019-12-06 알레니아 아르마치 에스.피.에이. 항공기 기체를 생산하기 위한 장치의 섹터들의 속박 시스템
ITTO20120287A1 (it) * 2012-03-30 2013-10-01 Alenia Aermacchi Spa Sistema posizionamento settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo
US9038686B2 (en) 2012-03-30 2015-05-26 Alenia Aermacchi S.P.A. Positioning system of sectors of a device for producing an airplane fuselage
US9038687B2 (en) 2012-03-30 2015-05-26 Alenia Aermacchi, S.p.A. Constraint system of sectors of a device for producing an airplane fuselage
KR20130111479A (ko) * 2012-03-30 2013-10-10 알레니아 아르마치 에스.피.에이. 항공기 기체를 생산하기 위한 장치의 섹터들의 위치조정 시스템
KR20130111478A (ko) * 2012-03-30 2013-10-10 알레니아 아르마치 에스.피.에이. 항공기 기체를 생산하기 위한 장치의 섹터들의 속박 시스템
ITTO20120286A1 (it) * 2012-03-30 2013-10-01 Alenia Aermacchi Spa Sistema di vincolo settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo
RU2622121C2 (ru) * 2012-03-30 2017-06-13 Аления Аэрмакки С.П.А. Система позиционирования секторов устройства для изготовления фюзеляжа летательного аппарата
ITTO20120285A1 (it) * 2012-03-30 2013-10-01 Alenia Aermacchi Spa Sistema bloccaggio settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo
EP2644360A1 (fr) * 2012-03-30 2013-10-02 Alenia Aermacchi S.p.A. Système de positionnement de secteurs d'un dispositif de fabrication de fuselage d'avion
US9376219B2 (en) 2012-03-30 2016-06-28 Alenia Aermacchi S.P.A. Actuating system of sectors of a device for producing an airplane fuselage
CN103358561B (zh) * 2012-03-30 2016-12-07 阿莱尼亚·马基公司 用于对制造飞机机身的装置的扇区进行定位的系统
RU2619740C2 (ru) * 2012-03-30 2017-05-17 Аления Аэрмакки С.П.А Ограничивающая система секторов устройства для изготовления фюзеляжа летательного аппарата
CN103448256A (zh) * 2012-03-30 2013-12-18 阿莱尼亚·马基公司 用于制造飞机机身的装置的扇区的致动系统
US9962917B2 (en) 2012-04-12 2018-05-08 Alenia Aermacchi S.P.A. Method of manufacturing single piece fuselage barrels in composite material
WO2013153537A2 (fr) 2012-04-12 2013-10-17 Alenia Aermacchi S.P.A. Procédé de fabrication de corps de cylindre en une seule pièce dans un matériau composite
FR3009992A1 (fr) * 2013-08-28 2015-03-06 Aircelle Sa Outillage a cles et panneau composite notamment pour nacelle de moteur d’aeronef fabrique a l’aide d’un tel outillage
WO2015028736A1 (fr) * 2013-08-28 2015-03-05 Aircelle Outillage à clés et panneau composite notamment pour nacelle de moteur d'aéronef fabriqué à l'aide d'un tel outillage
US9597843B2 (en) 2014-05-15 2017-03-21 The Boeing Company Method and apparatus for layup tooling
JP2015218903A (ja) * 2014-05-15 2015-12-07 ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ レイアップツーリングのための方法及び装置
CN105082564A (zh) * 2014-05-15 2015-11-25 波音公司 铺叠工具的方法和装置
US10118347B2 (en) 2014-05-15 2018-11-06 The Boeing Company Apparatuses for layup tooling
EP2944454A1 (fr) * 2014-05-15 2015-11-18 The Boeing Company Procédé et appareil pour outillage d'empilement
US10173348B2 (en) 2015-09-14 2019-01-08 Bell Helicopter Textron Inc. Modular mandrel for monolithic composite fuselage
US10906210B2 (en) 2017-01-25 2021-02-02 The Boeing Company Mandrel for composite part fabrication and repair
FR3100232A1 (fr) * 2019-08-30 2021-03-05 Airbus Ensemble comportant une tour support et au moins deux systemes de support pour des panneaux d’un troncon de fuselage d’un aeronef
US11260994B2 (en) 2019-08-30 2022-03-01 Airbus (S.A.S.) Assembly comprising a support tower and at least two support systems for panels of a fuselage section of an aircraft
US20210299958A1 (en) * 2020-03-28 2021-09-30 Karl Joseph Dodds Gifford Shrinkable platform for 3D printer
EP4015182A1 (fr) * 2020-12-18 2022-06-22 The Boeing Company Mandrin segmenté pour fabrication composite
EP4067040A1 (fr) 2021-04-01 2022-10-05 Airbus Operations Outil pour la fabrication d'un panneau auto-raidi et procédé de fabrication d'un panneau auto-raidi utilisant un tel outil
FR3121383A1 (fr) * 2021-04-01 2022-10-07 Airbus Operations Outil pour la fabrication d’un panneau auto-raidi et procédé de fabrication d’un panneau auto-raidi utilisant un tel outil
US11679567B2 (en) 2021-04-01 2023-06-20 Airbus Operations Sas Tool for manufacturing a self-stiffened panel, and method for manufacturing a self-stiffened panel using said tool
IT202200007511A1 (it) * 2022-04-14 2023-10-14 Leonardo Spa Attrezzatura e procedimento per la realizzazione di un elemento strutturale in materiale composito
WO2023199236A1 (fr) * 2022-04-14 2023-10-19 Leonardo S.P.A. Équipement et procédé de fabrication d'un élément structural en matériau composite

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