[go: up one dir, main page]

WO1989003293A1 - Procede et appareil pour fabriquer des structures composites - Google Patents

Procede et appareil pour fabriquer des structures composites Download PDF

Info

Publication number
WO1989003293A1
WO1989003293A1 PCT/US1988/003429 US8803429W WO8903293A1 WO 1989003293 A1 WO1989003293 A1 WO 1989003293A1 US 8803429 W US8803429 W US 8803429W WO 8903293 A1 WO8903293 A1 WO 8903293A1
Authority
WO
WIPO (PCT)
Prior art keywords
mold
molding
mold member
diaphragm
transverse
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.)
Ceased
Application number
PCT/US1988/003429
Other languages
English (en)
Inventor
Sam Cooper Aker
Pettice Malcolm Phillips
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.)
Lockheed Martin Corp
Original Assignee
Lockheed Corp
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 Lockheed Corp filed Critical Lockheed Corp
Publication of WO1989003293A1 publication Critical patent/WO1989003293A1/fr
Anticipated expiration legal-status Critical
Ceased 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
    • 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
    • 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
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • 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

Definitions

  • This invention relates to the molding and curing of composite structures, and in particular the molding and curing of complex structural shapes that require bonding forces to be exerted in multiple directions.
  • Composite structures such as those formed by graphite and fiberglass, are being used in an ever increasing variety of applications.
  • Composite structures particularly those made of graphite fibers, compare very favorably in strength with competitive metals, but have a significant advantage in weight, making it particularly useful in aircraft structures, where weight is a prime concern.
  • their usefulness has been limited by an inability to mold the composite structures into anything but the most basic shapes, such as a channel or cylinder. Further, the molding must often be performed in a pressurized autoclave, at elevated temperature to activate the resin or binder used to bind the individual graphite or fiberglass fibers.
  • a process for molding composite materials into a complex shape between first and second mold surfaces in a system capable of exerting a molding force in a first direction to mold the composite materials between the mold surfaces.
  • the process includes a step of applying a molding force in a direction transverse to the first direction to mold the composite materials between the mold surfaces.
  • the first mold surface is defined on a first mold member which is capable of dimensional change in the transverse direction
  • the process step of applying the molding force in the transverse direction includes the step of varying the dimensions of the first mold member to generate the molding force.
  • the transverse dimensions of the first mold member can be varied by expansion of an air pressurized diaphragm and the process further includes the step of supplying pressurized air to the air pressure diaphragm at a pressure sufficient to apply the appropriate molding force.
  • the force applied in the first direction can be generated by autoclave pressure, thermal expansion, mechanical press or by another air pressure diaphragm acting along the first direction.
  • an apparatus for molding composite materials into a complex shape.
  • the apparatus includes a first mold member defining a first mold surface and a second mold member defining a second mold surface, the composite materials positioned between the molding surfaces of the mold members.
  • Structure is provided for applying a force along a first direction for molding the composite material between the mold surfaces.
  • the first mold member is capable of dimensional variation in a direction transverse to the first direction and structure is provided for varying the dimensions of the first mold member in this transverse direction.
  • This structure can comprise an air pressure diaphragm expandable by pressurized air to generate the force.
  • the apparatus is thus capable of molding complex shapes not practical using present techniques and technolog .
  • FIGURE 1 is a perspective view Of a composite structure formed by a prior art process which illustrates the limitations of the prior art in molding very simple. shapes, such as a channel;
  • FIGURE 2 is a partial cross-sectional view of a prior art molding apparatus for molding a simple channel shape composite structure;
  • FIGURE 3 is a perspective view of an exemplary composite structure molded with the teachings of the present invention.
  • FIGURE 4 is an exploded view of a molding apparatus constructed in accordance with the teachings of the present invention for molding the shape illustrated in FIGURE 3;
  • FIGURES 5A and 5B illustrate an air pressure diaphragm used in the apparatus of FIGURE 4 non- pressurized and pressurized, respectively;
  • FIGURE 6 is a perspective view of elements of the apparatus of FIGURE 4 configured for lay up of the composite materials prior to molding;
  • FIGURE 7 is an exploded view of the pressure diaphragm illustrating its construction.
  • FIGURES 1 and 2 illustrate the limited capability of the present state of the art, represented by a molding apparatus 10 capable only of molding a composite structure into the simplest of shapes, such as a channel 12. Stiffeners 14 must be mechanically mounted to the channel 12 by special fastener 16. In contrast, the present invention, as embodied in FIGURES 3-7, has greatly enhanced flexibility. Molding apparatus 18 is capable of molding composite structures into complex shapes, such as channel 20 which has integral stiffeners.
  • the prior art technique employs a male mold member 22. Sheets of composite material are laid up on the mold surface 24 in the channel shape desired. A pressure bag (not shown) is placed over the exposed surface of the channel 12 and sealed to the member 22. The volume defined by the member 22 and pressure bag, containing the channel 12, is evacuated and the entire apparatus is placed within an autoclave. The autoclave is pressurized to force the composite materials against the mold surface 24. The molding apparatus is also heated to activate the resin binding the composite materials.
  • the channel 12 formed by apparatus 10 has certain disadvantages.
  • the outer surface 26 is molded through the pressure bag, and incorporates the surface irregularities of the bag, as illustrated in FIGURE 2. Further, the presence of corner 28 in the mold member 22 tends to thin the channel 12 at corner 28 as illustrated, reducing the strength of the channel 12. Because of the surface irregularity of outer surface 26, it is very difficult to mount the channel 12 in any precise relationship to surrounding structure through that surface. Often, this irregularity requires shims between the channel 12 and the surrounding structure, requiring expensive and time consuming labor to fit the parts.
  • stiffeners 14 there is often a need to strengthen the channel 12 with stiffeners 14.
  • the stiffeners 14 With molding apparatus 10 capable only of molding the simple channel form, the stiffeners 14 must be formed by separate angle members 30 fastened to the channel 12 by conventional mechanical fasteners 16.
  • a molding apparatus 40 is capable of molding a complex channel 42 with an integral longitudinal stiffener 44 and -transverse stiffener 46.
  • the molding apparatus 40 can be seen to comprise two main assemblies, a female mold member 48 and a male mold member 50 formed of a number of individual blocks 52-60, and also pressure diaphragms 53 and 55.
  • the female mold member 48 can be seen to have a cavity 62 with a mold surface 64 to form the exterior surface of the channel 42. At either end of the cavity 62 beyond mold surface 64 are formed elongated slots 66 and 68.
  • a tool end bar 70 is adapted to fit within the slot 66.
  • a tool end bar 72 is adapted to fit within slot 68.
  • female mold member 48 and tool end bar 70 and 72 are formed of steel.
  • block 52 can be seen to have mold surfaces 74, 76 and 78.
  • Block 54 can be seen to have mold surfaces 80, 82 and 84.
  • a surface 86 on block 52 faces a surface 88 on block 54.
  • the longitudinal portion 90 of pressure diaphragm 53 extends along the length of blocks 52 and 54 between the facing surfaces 86 and 88.
  • Block 56 is formed with mold surfaces 92, 94 and 96.
  • Block 58 is formed with mold surfaces 98, 100 and 102.
  • Surface 104 on block 56 faces surface 106 on block 58.
  • a longitudinal portion 108 of pressure diaphragm 55 extends along the length of blocks 56 and 58 between surfaces 104 and 106.
  • the block 60 is formed with mold surfaces 110, 112 and 114.
  • the blocks 52-60 are pinned in a predetermined orientation on a backing plate 116.
  • the blocks are pinned to the backing plate to provide a gap 118 between blocks 54 and 58 and block 60.
  • a similar gap 120 is formed between blocks 52 and 56 and between blocks 54 and 58.
  • the composite material whether it be graphite, fiberglass or Kevlar, is laid up on the various mold surfaces of the male mold member 50 to form the channel 42 after molding. Gaps capable of width change, such as gaps 118 and 120, are necessary because the thickness of the composite materials as laid up exceeds the final thickness of the corresponding portion of the channel 42.
  • the layers of composite material are oriented at different angles relative to each other to provide the maximum strength and flexibility to the completed channel.
  • the male mold member 50 After being laid up, the male mold member 50, and composite material, is inverted for insertion within the female mold member 48, as illustrated in FIGURE 4.
  • the blocks 52 - 60 are unpinned from the backing plate 116, and the backing plate 116 can be removed, if desired.
  • the blocks are thus capable of limited movement along the longitudinal direction represented by arrow 121 and the lateral direction, represented by arrow 122.
  • a downwardly directed vertical force in the direction of arrow 124 is applied to the male mold member 50 to compress and mold the composite materials between the facing mold surfaces of the mold members 48 and 50.
  • This vertical force can be provided by conventional techniques.
  • a pressure bag can be placed in sealing engagement with the female mold member 48 to enclose the male mold member 50.
  • the interior of the mold can then be evacuated and the molding apparatus 40 placed in a autoclave for pressurization, which generates the force in the direction of arrow 124.
  • a mechanical press could be used to generate this force.
  • the molding apparatus 40 is capable of exerting molding forces both in the longitudinal direction and lateral direction which are necessary to properly mold the complex shape of channel 42. These forces are generated by fluid pressure, namely gas pressure (preferably air or nitrogen) or a pressurized liquid within the pressure diaphragms 53 and 55. Air pressure enters each diaphragm through a port 126.
  • the diaphragm 53 as seen in FIGURE 7, is seen to be constructed of three sheets 128, 130 and 132 of flexible material, preferably stainless steel, welded along their edges to form a T-shaped diaphragm secured to the block 127.
  • the sheets 130 and 132 have integral flanges 180 and 182 respectively, bent over at right angles to the direction of diaphragm action, which allows the diaphragm to be bolted to a first block at flange 180 to maintain the proper position of the diaphragm. Because the adjacent block will move relative to the other, the flange 182 has an elongated slot 184 to receive a guide pin on the adjacent block which allows sliding motion between the diaphragm and adjacent blocks. Diaphragm 55 only requires two sheets in its construction as it only has an expandable longitudinal portion 108, and no expandable lateral portion, as does diaphragm 53.
  • the blocks 52-60 are free to move slightly in both longitudinal direction 121 and lateral direction 122, the forces exerted by the longitudinal portion of pressure diaphragms 53 and 55 will force blocks 52 and 56 laterally so that surfaces 74 and 92 of blocks 52 and 56 mold leg 140 of the channel 42 against the wall of mold surface 64.
  • the longitudinal portions 90 and 108 will ' also force blocks 54 and 58 in the opposite lateral direction to mold longitudinal stiffener 44 between mold surfaces 84, 102 and 110.
  • the force will be conveyed through the block 60 to mold the other leg 142 of channel 42 between mold surface 114 and the opposite wall of mold surface 64.
  • the lateral portion 144 of the pressure diaphragm 53 will act between the longitudinal ends of blocks 52-58 and the adjacent tool end bars 70 and 72 to force blocks 52-58 longitudinally inward toward the transverse stiffener 46 to mold the stiffener 46 between the mold surfaces 78, 82, 96 and 100 of the blocks.
  • the relative movement between the blocks as the pressure diaphragms are expanded is best illustrated in FIGURES 5A and 5B.
  • the final dimensions of the channel 42 are set by the final gap dimensions when diaphragms 53 and 55 move the blocks into contact with each other and mold member 48 as seen in FIGURE 5b.
  • the teachings of the present invention allow multi-dimensional forces to be exerted on the composite materials for molding into a complex shaped composite structure.
  • the pressure diaphragms can be configured in a position to provide the necessary forces for a specific composite structure design, as desired.
  • shop air pressure in the range of 100 - 150 psi, was found satisfactory to generate the forces necessary to properly mold a graphite composite structure of the shape of channel 42.
  • the channel 42 was held within 0.005 inch tolerances and would require no trimming or other surface treatment for use in an environment even as " critical as an aircraft wing.
  • the sheet employed in the pressure diaphragms had a thickness in the range from 0.008 inches to 0.015 inches, with the preferred thickness being in the range of 0.008 inches to 0.012 inches.
  • the present invention permits the molding forces necessary for molding the complex shape to be independent of the temperature of the mold apparatus.
  • the molding forces can be applied to cause the composite materials to flow to their final position within the structure being molded prior to activating the binding resin with heat, resulting in a stronger structure.
  • the forces exerted by the molding apparatus need not be applied simultaneously. For example, a vertical force could be applied initially to smooth a portion of the composite structure and extrude or flow the material out the edges. The transverse forces could then be applied to smooth the composite material under their direct influence. Because the technique of the present invention is independent of the relative coefficient of thermal expansion of the materials, it is entirely suitable for use with new high temperature composite materials which require a temperature of 700° F to bond properly.
  • the invention is not dependent upon thermal effects, and thus does not need to be restricted to an autoclave.
  • a simple mechanical press could be used to provide force along one direction. Even a larger pressure diaphragm could be substituted for the press if desired.
  • the present invention can employ all three common composite materials, graphite, fiberglass and Kevlar, in a single molding apparatus. A flexibility not previously known in the industry.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Un appareil de moulage perfectionné (40) permet de mouler une forme complexe, telle qu'un canal (42), à partir de matériaux composites. Un élément de moule mâle (50) est constitué de blocs individuels (52-60) séparés par des membranes de pression (53, 55). L'entrée d'air sous pression à l'intérieur des membranes de pression (53, 55) écarte les blocs, dilatant efficacement l'élément de moule mâle (50) à l'intérieur de l'élément de moule femelle (48) afin de donner par moulage au matériau composite une forme complexe telle que le canal (42).
PCT/US1988/003429 1987-10-15 1988-10-06 Procede et appareil pour fabriquer des structures composites Ceased WO1989003293A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10991687A 1987-10-15 1987-10-15
US109,916 1987-10-15

Publications (1)

Publication Number Publication Date
WO1989003293A1 true WO1989003293A1 (fr) 1989-04-20

Family

ID=22330253

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1988/003429 Ceased WO1989003293A1 (fr) 1987-10-15 1988-10-06 Procede et appareil pour fabriquer des structures composites

Country Status (3)

Country Link
ES (1) ES2010822A6 (fr)
IL (1) IL87589A0 (fr)
WO (1) WO1989003293A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993009928A1 (fr) * 1991-11-18 1993-05-27 United Technologies Corporation Moule destine a la fabrication d'articles en materiaux composites incorporant des raidisseurs colles solidaires
US5382150A (en) * 1991-12-24 1995-01-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Apparatus for molding a composite material article
WO2013122524A1 (fr) * 2012-02-17 2013-08-22 Saab Ab Procédé et système de moule pour moulage en filet d'une structure intégrée co-durcie
EP2670571A1 (fr) * 2011-02-04 2013-12-11 Compose Outillage de moulage pour la realisation d'une piece en materiau composite au moyen d'une preforme souple composee d'une peau et de preformes profilees solidarisees sur la dite peau
EP2133263B2 (fr) † 2008-06-13 2016-06-29 The Boeing Company Procédé et appareil de formation et d'installation de serres
US20220134687A1 (en) * 2017-09-07 2022-05-05 Kawasaki Jukogyo Kabushiki Kaisha Mold for manufacturing composite material molded product, and method for manufacturing composite material molded product

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2852807A (en) * 1954-05-11 1958-09-23 Robert L Altschuler Machine for making building panels
US3348476A (en) * 1963-02-04 1967-10-24 Parsons Corp Flat-formed inflatable pressure bags
US3892831A (en) * 1970-07-29 1975-07-01 Jacques Andre Robin Method of manufacture of tennis rackets of reinforced synthetic material
US4017572A (en) * 1974-02-04 1977-04-12 The Upjohn Company Method of molding articles of polymeric foam substantially free from flashing
US4388263A (en) * 1981-10-13 1983-06-14 General Dynamics Corp./Convair Division Controlled elastomeric tooling for plastic fabrication
US4492607A (en) * 1983-02-22 1985-01-08 Rockwell International Corporation Method for producing integrally stiffened fiber reinforced plastic panels
US4544518A (en) * 1982-04-30 1985-10-01 Lindskog Kjell J Method and apparatus for the manufacture of shaped articles from fibre-reinforced plastics material
US4591400A (en) * 1984-05-15 1986-05-27 United Technologies Corporation Method of forming a fiber reinforced composite article of a complex configuration
US4624820A (en) * 1984-06-22 1986-11-25 Rolls-Royce Plc Molding of composite materials
US4704240A (en) * 1986-09-10 1987-11-03 United Technologies Corporation Method of fabricating tubular composite structures
US4721593A (en) * 1986-05-15 1988-01-26 Canadair Inc. Process for molding and curing a composite skin-stiffeners assembly
US4724115A (en) * 1986-04-21 1988-02-09 The Budd Company Method of forming composite structures having sections extending in different diections

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2852807A (en) * 1954-05-11 1958-09-23 Robert L Altschuler Machine for making building panels
US3348476A (en) * 1963-02-04 1967-10-24 Parsons Corp Flat-formed inflatable pressure bags
US3892831A (en) * 1970-07-29 1975-07-01 Jacques Andre Robin Method of manufacture of tennis rackets of reinforced synthetic material
US4017572A (en) * 1974-02-04 1977-04-12 The Upjohn Company Method of molding articles of polymeric foam substantially free from flashing
US4388263A (en) * 1981-10-13 1983-06-14 General Dynamics Corp./Convair Division Controlled elastomeric tooling for plastic fabrication
US4544518A (en) * 1982-04-30 1985-10-01 Lindskog Kjell J Method and apparatus for the manufacture of shaped articles from fibre-reinforced plastics material
US4492607A (en) * 1983-02-22 1985-01-08 Rockwell International Corporation Method for producing integrally stiffened fiber reinforced plastic panels
US4591400A (en) * 1984-05-15 1986-05-27 United Technologies Corporation Method of forming a fiber reinforced composite article of a complex configuration
US4624820A (en) * 1984-06-22 1986-11-25 Rolls-Royce Plc Molding of composite materials
US4724115A (en) * 1986-04-21 1988-02-09 The Budd Company Method of forming composite structures having sections extending in different diections
US4721593A (en) * 1986-05-15 1988-01-26 Canadair Inc. Process for molding and curing a composite skin-stiffeners assembly
US4704240A (en) * 1986-09-10 1987-11-03 United Technologies Corporation Method of fabricating tubular composite structures

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993009928A1 (fr) * 1991-11-18 1993-05-27 United Technologies Corporation Moule destine a la fabrication d'articles en materiaux composites incorporant des raidisseurs colles solidaires
US5382150A (en) * 1991-12-24 1995-01-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Apparatus for molding a composite material article
EP2133263B2 (fr) † 2008-06-13 2016-06-29 The Boeing Company Procédé et appareil de formation et d'installation de serres
EP2670571A1 (fr) * 2011-02-04 2013-12-11 Compose Outillage de moulage pour la realisation d'une piece en materiau composite au moyen d'une preforme souple composee d'une peau et de preformes profilees solidarisees sur la dite peau
WO2013122524A1 (fr) * 2012-02-17 2013-08-22 Saab Ab Procédé et système de moule pour moulage en filet d'une structure intégrée co-durcie
US20220134687A1 (en) * 2017-09-07 2022-05-05 Kawasaki Jukogyo Kabushiki Kaisha Mold for manufacturing composite material molded product, and method for manufacturing composite material molded product
US12459170B2 (en) * 2017-09-07 2025-11-04 Kawasaki Jukogyo Kabushiki Kaisha Mold for manufacturing composite material molded product, and method for manufacturing composite material molded product

Also Published As

Publication number Publication date
IL87589A0 (en) 1989-01-31
ES2010822A6 (es) 1989-12-01

Similar Documents

Publication Publication Date Title
EP1943087B1 (fr) Outil de compactage expansible et procédé de fabrication de structures composites
EP3115185B1 (fr) Réduction du plissement de raidisseurs profilés en forme de chapeau formés à partir d'une charge composite unique
RU2479424C2 (ru) Способ формования заготовки
US5639535A (en) Composite interleaving for composite interfaces
US5714179A (en) Rigid tooling with compliant forming surface for forming parts from composite materials
US5087187A (en) Apparatus for molding hollow composite articles having internal reinforcement structures
US5292475A (en) Tooling and process for variability reduction of composite structures
JP6563284B2 (ja) 繊維強化プラスチック成型品の製造装置及びその製造方法
US20110308714A1 (en) Method and shaping device for producing a composite fibre component for air and space travel
US4869770A (en) Method and apparatus for laminating composite materials
US8551382B2 (en) Modified blade stiffener and fabrication method therefor
US4721593A (en) Process for molding and curing a composite skin-stiffeners assembly
EP2364837B1 (fr) Procédé de fabrication de montants, longerons et poutres de fuselage à section transversale H variable
CN101909862A (zh) 由复合纤维材料生产型材的方法
CA2120505A1 (fr) Moules pour la fabrication d'articles composites avec elements raidisseurs integres
EP2835252A1 (fr) Outillage et procédé de consolidation de structures composites hautement intégrées
CN110406082A (zh) 制造用于交通工具的复合桁梁的方法
EP0591324A1 (fr) Procede de production d'une structure composite possedant un tissu tridimensionnel intermediaire, et structure ainsi obtenue.
US20140291889A1 (en) Device and method for molding fiber-reinforced plastic member
EP0030522A2 (fr) Panneau autoportant en résines de polyuréthane ou similaires, procédé et dispositif de fabrication
EP3785890B1 (fr) Système, procédé de mise en forme de préforme et procédé de moulage de matériau composite
WO1989003293A1 (fr) Procede et appareil pour fabriquer des structures composites
US5124196A (en) Prestressed article and method
EP0572248A1 (fr) Fabrication d'articles à partir de matériau composite
US4995931A (en) Method for forming components from fibre-reinforced thermoplastic materials

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): BR JP KR NO

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE FR GB IT LU NL SE