WO2011070002A1 - Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres - Google Patents

Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres Download PDF

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Publication number
WO2011070002A1
WO2011070002A1 PCT/EP2010/069052 EP2010069052W WO2011070002A1 WO 2011070002 A1 WO2011070002 A1 WO 2011070002A1 EP 2010069052 W EP2010069052 W EP 2010069052W WO 2011070002 A1 WO2011070002 A1 WO 2011070002A1
Authority
WO
WIPO (PCT)
Prior art keywords
mold
actuators
vacuum
aircraft
stringers
Prior art date
Application number
PCT/EP2010/069052
Other languages
German (de)
English (en)
Other versions
WO2011070002A4 (fr
Inventor
Carsten Barlag
Christian Steiger
Niels Deschauer
Original Assignee
Airbus Operations Gmbh
Premium Aerotec Gmbh
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 Airbus Operations Gmbh, Premium Aerotec Gmbh filed Critical Airbus Operations Gmbh
Priority to EP10794932.3A priority Critical patent/EP2509775B1/fr
Priority to CN201080055364.XA priority patent/CN102686381B/zh
Priority to CA2783135A priority patent/CA2783135C/fr
Publication of WO2011070002A1 publication Critical patent/WO2011070002A1/fr
Publication of WO2011070002A4 publication Critical patent/WO2011070002A4/fr
Priority to US13/489,795 priority patent/US8911585B2/en

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
    • B29C70/28—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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/30—Mounting, exchanging or centering
    • B29C33/307—Mould plates mounted on frames; Mounting the mould plates; Frame constructions therefor
    • 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
    • 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
    • B29C70/443—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 and impregnating by vacuum or injection
    • 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
    • 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
    • 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
    • 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

Definitions

  • the present invention relates to a device and a method for
  • the field of application of the present invention extends primarily to aircraft construction.
  • Hulls are usually manufactured in shell construction, in particular half-shell construction. Under half-shell construction is understood in aircraft construction of the body of the hull in usually two shells. Joined together, the two shells give a nearly round or oval cross-section of a fuselage section.
  • Fiber composites such as glass fiber or carbon fiber reinforced plastics used.
  • the shells are usually equipped with stiffening elements, eg. B. T or Omega stringer.
  • stiffening elements eg. B. T or Omega stringer.
  • the half shell for the fuselage is in a negative adhesive form
  • Laminating Adhesive Device produced by introducing fiber material and resin in various processes and cured.
  • the LKV gives the component the corresponding outer contour. After removal from the mold, machining is often carried out before assembly of the half-shells modeled in this way can be carried out.
  • a device for an efficient serial production of a fuselage shell consisting of fiber composite materials for an aircraft emerges.
  • this is provided with spaced strippers.
  • a grid of a plurality of support walls of different lengths is fixed such that their ends form a semicircle, wherein said support walls are arranged below given by the radius of the semicircle angles to the base support.
  • modular profiles are attached, which cover the spaces between the support walls and whose outer surfaces of the inner contour of the produced integral structural component in the negative correspond.
  • the grid of the supporting walls and the division of the modular profiles are designed such that the joint gap of the modular profiles is arranged in each case under the position of a stringer.
  • a suitable LKV is placed after making the complete structure of the component and the auxiliaries above this mounting substrate accurately and the previously applied to the vacuum film circumferential sealant so precompressed that a vacuum-tight seal between the vacuum skin and the LKV arises. Subsequently, the structure is evacuated on the LCP side.
  • the fuselage shell provided with the stringers is with the previously described
  • the positioning of the stringer is done via the matching geometry of recess and fitting.
  • all skin layers made of fiber composite materials are applied individually or as a package on outer surfaces of the modular profiles of the mounting carrier covered by the vacuum skin / film and the stringer profiles.
  • a sealing compound in an optimized amount is applied to the vacuum film.
  • the circulating sealing compound is compacted in such a way that a vacuum-tight seal is produced between the said vacuum skin / film and the laminating adhesive device.
  • the side of an additional ARV is vented and then vacuum pulled on the LKV side.
  • the entire structure is pressed against the LKV with atmospheric pressure.
  • ARV and LKV are moved apart and the LKV turned, to then feed them to a hardening process.
  • the manufacturing solution is quite problematic at quite strong opening angles of large hull shells. Because of the strong opening angle, the auxiliaries and the Stringerfuss vom rubbing when entering a laminating adhesive device with the adhesive skin located therein at the outer sites, so that the
  • Form surface must be designed slightly smaller. So now the stringers and the When transferring substances within the laminating adhesive device, they do not uncontrollably bridge the required gap by using them
  • Transferring vacuum film can be easily taken along, is a defined
  • the object is achieved on the basis of a device according to the preamble of claim 1 in conjunction with its characterizing features.
  • the invention includes the technical teaching that a plurality of radially outwardly extending and longitudinally adjustable actuators are mounted on the curved mounting surface of a Aufrüstmays, at the distal ends of each mold grooves are secured to receive the stringers, which with each other with flexible intermediate elements and / or other mold channels are connected to form a vacuum-tight closed curved molding surface.
  • the solution according to the invention makes it possible to press a sealing seam, which is normally present in vacuum assemblies, against the laminating adhesive device. If necessary, the adjustment of the actuators could also be carried out to varying degrees, since a larger offset gap is usually required on the side flanks than in the region of the center of the fuselage shell.
  • the contact pressure of the stringer on the component in the transfer process can be adjusted accurately, so that overpressing can be excluded. An overpressure would be possible, for example, in large, very heavy devices by unintentional bending of the ARV. Then a big load would be on the stringer, which could lead to damage.
  • the Aufrüstvoroplasty invention consists of a supporting framework, such as a steel pipe, frame and a curved molding surface, which consists of the mold channels, which may be made of plastic or metal. Furthermore, the mold channels are adjustably mounted on the basic structure by the actuators, for example pneumatic cylinders. Depending on the requirements of the fuselage shell to be produced, it is also possible to actuate several mold channels in a combined manner via a single actuator. According to a measure improving the invention, it is proposed that the actuators are mounted pivotably on the mounting surface of the basic structure via respective associated joints. As a result, the actuator together with the end attached thereto mold channel according to the planned target position can be easily installed and adjust if necessary.
  • the actuators for example pneumatic cylinders.
  • the set position remains unchangeable. This can be done by blocking the joint with the aid of clamping means or the like or can be achieved by appropriate slots during assembly.
  • the invention improving additional aspect is proposed to connect the individual mold channels with each other along the longitudinal edges with an elastic band as a flexible intermediate element airtight. In this way, the required flexibility of the device according to the invention can be generated in the radial direction in a simple manner.
  • the flexible intermediate element as a kind of hinge, wherein the actuator is provided for folding down a side edge of the molding surface which can be pivoted over it.
  • a hinge would preferably be designed to be elastic, for example as a rubber compound.
  • About the actuator can be folded down preferably rigidly connected longitudinally rigidly connected molding channels through the actuator to the inside.
  • the groove base of the molding channel is provided with vacuum connections for the molding surface.
  • the mold surface is vacuum-sealed and through the vacuum ports and associated manifold system, holes or grooves / channels for vacuum guidance can be created as needed.
  • the cavity region of the molding channel has a plurality of spaced-apart ones Having kavticiansqueritessverringernde and the desired position of the stringer to be inserted corresponding positioning.
  • the cross-section of the molding channel is preferably reduced by a few millimeters down to the outside dimensions of the stringer to be inserted thereon.
  • the stringer is then guided in a simple manner and accurately positioned.
  • magnets for fixing the stringers or the like can preferably also be attached on the back side.
  • Transfer cars with lifting mechanism are driven under the turned LKV.
  • the ARV can be mounted in a hub-reversing station to drive the rotated ARV with the permanent LKV.
  • Positioning of ARV and laminating adhesive device can e.g. B. by
  • Shell and stringers done in an autoclave. After the vacuum construction has been prepared for the hull shell in the manner according to the invention, the curing and thus the bonding of skin and stringers can be carried out in an autoclave. After curing, the auxiliaries and vacuum film are removed and the body shell removed from the laminating adhesive device taken and should preferably immediately thereafter optionally a mech. Processing and quality inspection are supplied. Subsequently, the assembly can be carried out to the finished hull.
  • FIGS. 1 shows a schematic front view of an upgrade device for
  • Figure 2 is a schematic front view of an upgrade device for
  • Figure 3 is a perspective view of an exemplary mold channel with integrated positioning
  • FIGS. 4a-4h show a schematic figure sequence for illustrating the device preferably to be carried out with the device
  • an upgrade essentially consists of a
  • Backbone 1 to form a curved Montagefikiee 3 and for producing a rigid substructure.
  • On the mounting surface 3 a plurality of radially outwardly extending actuators 4 are attached.
  • the actuators 4 are pivotally mounted by the mounting surface 3 via joints / elongated holes 5 and each have at their distal end mold grooves 6 for receiving - not shown - stringer of the fuselage shell.
  • the individual mold channels 6 are connected to each other with flexible / elastic intermediate elements 7 such that a total of a vacuum-tight closed mold surface 8 is formed.
  • the flexible intermediate elements 7 are executed in this embodiment as elastic bands.
  • a plurality of adjacent mold channels 6a, 6b are rigidly connected to one another and are articulated to the basic structure 1 via a flexible intermediate element 7 'designed as a hinge.
  • the rigidly interconnected mold channels 6a and 6b are pivotable via a common actuator 4 'in the joint produced by the flexible intermediate element 7', so that the two opposite side parts of this
  • the backbone 1 is here mounted on a sliding carriage 9 with a lifting mechanism to align the entire device for positioning relative to an overlying - not shown - laminating adhesive device.
  • the molding channel 6 of the device consisting here of a metal is provided with vacuum connections 10, via which the molding surface 8 can be evacuated.
  • the groove region of the molding channel 6 further has a groove section reducing positioning section 11, to which during production a stringer comes to rest in order to align it exactly within the device.
  • FIGS. 4a to 4h the production steps for a fuselage shell are illustrated on the basis of the device described above in FIG. 1.
  • FIG. 4a a transfer position of the device is assumed in which the actuators 4 are extended in the direction of the arrow. This results in a corresponding to the desired position curved mold surface 8, in which the arranged between the individual mold grooves 6 flexible intermediate elements 7 are stretched.
  • the molding surface 8 is subsequently covered with a vacuum film 12 in order to seal it.
  • the molding surface 8 is subsequently prefabricated
  • stringer 14 made of carbon-fiber reinforced plastic, which are respectively associated with them, are then inserted into the mold channels in such a way that, depending on the design and production method, they do not overlap at the edge, partially or completely with the auxiliary material webs 13.
  • the actuators are then retracted, so that relax the flexible intermediate elements 7 to the mold surface 8 in a
  • Upgrading associated lamination adhesive device 15 fed above or below and the actuators 4 are then returned to a transfer position extended to effect the pressing of the occupied mold surface 8 and thus the stringer on a corresponding thereto shaped counter surface of the laminating adhesive device with skin 15.
  • Atmospheric pressure is pressed to the LKV and is thus transferred to the laminating adhesive device 15.
  • the actuators 4 are retracted again in order to move the device into the retracted position (avoiding undercuts), so that the strongly curved body shell 16 can be easily removed from the mold.
  • the invention is not limited to the two previously described
  • the retraction position for strongly curved hull shells can also be effected by other intermediate elements which can be changed over the forming surface.

Abstract

L'invention concerne un dispositif et un procédé pour fabriquer une coque de fuselage (16) d'un aéronef dans un matériau composite renforcé par des fibres, cette coque de fuselage (16) étant pourvue de plusieurs lisses (14) de renforcement disposées à distance les unes des autres. Le dispositif selon l'invention comprend une ossature de base (1) comprenant plusieurs parois de soutien (2) de longueur différente pour former une surface de montage (3) cintrée pour la coque de fuselage (16) à fabriquer. Plusieurs actionneurs (4) mobiles longitudinalement s'étendant radialement vers l'extérieur sont placés sur la surface de montage (3), une rigole de façonnage (6) respective destinée à recevoir une lisse (14) étant fixée à l'extrémité distale de chaque actionneur (4). Les rigoles de façonnage (6) sont reliées les unes aux autres par des éléments intermédiaires (7) flexibles et/ou par d'autres rigoles de façonnage (6) pour former une surface de façonnage (8) étanche au vide.
PCT/EP2010/069052 2009-12-07 2010-12-07 Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres WO2011070002A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP10794932.3A EP2509775B1 (fr) 2009-12-07 2010-12-07 Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres
CN201080055364.XA CN102686381B (zh) 2009-12-07 2010-12-07 用于制造用于飞行器的由纤维复合材料制成的机身外壳的装置和方法
CA2783135A CA2783135C (fr) 2009-12-07 2010-12-07 Dispositif et procede de production d'une enveloppe de fuselage formee de materiau fibreux composite destinee a un aeronef
US13/489,795 US8911585B2 (en) 2009-12-07 2012-06-06 Device and method for manufacturing a fiber-reinforced composite fuselage shell for an aircraft

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US26722209P 2009-12-07 2009-12-07
DE102009056978A DE102009056978A1 (de) 2009-12-07 2009-12-07 Vorrichtung und Verfahren zur Herstellung einer aus einem Faserverbundwerkstoff bestehenden Rumpfschale für ein Luftfahrzeug
DE102009056978.2 2009-12-07
US61/267,222 2009-12-07

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US13/489,795 Continuation US8911585B2 (en) 2009-12-07 2012-06-06 Device and method for manufacturing a fiber-reinforced composite fuselage shell for an aircraft

Publications (2)

Publication Number Publication Date
WO2011070002A1 true WO2011070002A1 (fr) 2011-06-16
WO2011070002A4 WO2011070002A4 (fr) 2011-08-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/069052 WO2011070002A1 (fr) 2009-12-07 2010-12-07 Dispositif et procédé pour fabriquer une coque de fuselage d'un aéronef dans un matériau composite renforcé par des fibres

Country Status (6)

Country Link
US (1) US8911585B2 (fr)
EP (1) EP2509775B1 (fr)
CN (1) CN102686381B (fr)
CA (1) CA2783135C (fr)
DE (1) DE102009056978A1 (fr)
WO (1) WO2011070002A1 (fr)

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US8557826B2 (en) 2009-10-08 2013-10-15 Merck Sharp & Dohme Corp. Pentafluorosulfur imino heterocyclic compounds as BACE-1 inhibitors, compositions, and their use
US20140117159A1 (en) * 2011-07-18 2014-05-01 The Boeing Company Flexible Truss Frame and Method of Making the Same
US9302759B2 (en) * 2011-07-18 2016-04-05 The Boeing Company Flexible truss frame and method of making the same
RU2619403C2 (ru) * 2012-03-30 2017-05-15 Аления Аэрмакки С.П.А Приводная система секторов устройства для изготовления фюзеляжа летательного аппарата

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CN102686381A (zh) 2012-09-19
CA2783135A1 (fr) 2011-06-16
CN102686381B (zh) 2015-08-26
WO2011070002A4 (fr) 2011-08-18
DE102009056978A1 (de) 2011-06-09
EP2509775A1 (fr) 2012-10-17
CA2783135C (fr) 2016-10-18
EP2509775B1 (fr) 2016-04-20
US8911585B2 (en) 2014-12-16

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