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WO1992000845A1 - Fabrication d'un materiau composite - Google Patents

Fabrication d'un materiau composite Download PDF

Info

Publication number
WO1992000845A1
WO1992000845A1 PCT/GB1991/001033 GB9101033W WO9200845A1 WO 1992000845 A1 WO1992000845 A1 WO 1992000845A1 GB 9101033 W GB9101033 W GB 9101033W WO 9200845 A1 WO9200845 A1 WO 9200845A1
Authority
WO
WIPO (PCT)
Prior art keywords
stack
blade
loop
layers
intermediate fabric
Prior art date
Application number
PCT/GB1991/001033
Other languages
English (en)
Inventor
Robert Samuel Wilson
Mark Anthony Braniff
Original Assignee
Short Brothers Plc
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 Short Brothers Plc filed Critical Short Brothers Plc
Priority to BR919106615A priority Critical patent/BR9106615A/pt
Priority to FI925805A priority patent/FI925805A0/fi
Priority to EP91911858A priority patent/EP0648159A1/fr
Publication of WO1992000845A1 publication Critical patent/WO1992000845A1/fr

Links

Classifications

    • D—TEXTILES; PAPER
    • D05—SEWING; EMBROIDERING; TUFTING
    • D05C—EMBROIDERING; TUFTING
    • D05C15/00—Making pile fabrics or articles having similar surface features by inserting loops into a base material
    • D05C15/04—Tufting
    • D05C15/08—Tufting machines
    • D05C15/16—Arrangements or devices for manipulating threads
    • D05C15/24—Loop cutters; Driving mechanisms therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00—Making preforms
    • B29B11/14—Making preforms characterised by structure or composition
    • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding

Definitions

  • the present invention relates to apparatus for and a method of manufacturing a composite material such as, for example, a composite material particularly suitable for forming the outer surface material of an aircraft.
  • ⁇ material includes any suitable component or structure, such as for example a laminate joint, depending on the application of the invention.
  • a previously proposed composite material has been manufactured by embedding high strength fibres having a high modulus of elasticity within a homogeneous matrix.
  • the fibres are made of carbon, aramid or boron, and the matrix can be formed of material such as an epoxy, bismalemide or polyimide resin.
  • the fibres are supplied in a uni-directional, woven or fibrous mat format which is pre-impregnated with slightly cured resin to form an intermediate fabric material.
  • This intermediate fabric material is flexible and tacky, and the positions of the fibre filaments therein are not fixed. Layers of these intermediate fabric materials are assembled one upon the other in a mould, and then compressed and heated. The heating action accelerates the curing of the resin, and the combination of the heating and compression joins together the intermediate fabric materials to form the composite material.
  • the present invention is particularly concerned with apparatus for and a method of fastening together the layers of intermediate fabric material at spaced locations thereon.
  • apparatus for fastening together a plurality of layers of intermediate fabric material located in a stack, .
  • said apparatus comprising first means to make a passage through the stack, second means to draw a loop of prepared material through the passage to extend from both faces of the stack, third means to cut the loop at a pre ⁇ selected distance from one face of the stack to form two independent pieces of prepared material, and means to fold back the end portions of each piece onto the opposite faces of the stack to extend away from the other piece.
  • a method of fastening together a plurality of layers of intermediate fabric material located in a stack comprising making a passage through the stack, drawing a loop of prepared material through the passage to extend from both faces of the stack, cutting the loop at a preselected- distance from one face of the stack to form two independent pieces of prepared material, and folding back the end portions of each piece onto the opposite faces of the stack to extend away from the other piece.
  • the stack of fastened layers of intermediate fabric material may then be compressed and heated to cure the resin.
  • a moveable flat, narrow blade having a longitudinal slot adjacent its forward cutting edge may constitute both the first and second means of the invention.
  • the blade is advanced to make a passage through the stack.
  • a loop of prepared material is then threaded through the longitudinal slot in the blade so that the blade is located at the mid-point of the loop, and the blade is withdrawn through the stack so that the loop is located in the passage with the mid portion and end portions of the loop extending from opposite faces of the stack.
  • the third means may comprise a static blade to cut the loop when the mid-point of the loop has been positioned at a pre-selected distance from one face of the stack so as to form two independent pieces of prepared material.
  • the length of the material forming the loop, and the position of the static blade are arranged so that the two pieces each project an equal distance from opposite faces of the stack.
  • Figures l to 7 are diagrammatic illustrations of seven stages in the fastening together of layers of intermediate fabric material previously referred to herein;
  • Figures 0a and Ob are a top plan view and side view respectively of a tow of prepared material for fastening - A - together the layers of intermediate fabric material; and Figures 9 and 10 are illustrations of a modified fastening technique.
  • a stack 2 of intermediate fabric material is supplied on a release film (not shown) which is removed before commencement of the fastening operation.
  • the stack has been compacted or debulked under vacuum at room temperature. This compaction or debulking gives to the stack a degree of structural rigidity which aids assembly of the proposed composite material.
  • the stack consists of a plurality of layers of the material placed together face to face.
  • Each layer of intermediate fabric material is formed by embedding high strength fibres having a high modulus of elasticity in a homogeneous matrix which may be an epoxy, bis alemide or a polyimide resin.
  • the fibres may be uni-directional, woven or in the form of a fibrous mat, and the fibres may be made of materials such as carbon, aramid or boron.
  • Each intermediate fabric material layer is supplied with the resin matrix slightly cured to ensure that the fabric layer is tacky and flexible, and at this stage the fibres are not in a fixed position in the matrix.
  • the stack 2 is rectangular in shape, and is located in a horizontal position beneath a moveable knife blade 4 having a forward cutting edge 6.
  • the blade has its minor dimension in the plane of the drawings, and its major dimension in the plane perpendicular to that of the drawings.
  • the blade 4 is also flat, by which is meant that it lies completely in a plane perpendicular to the plane of the drawings.
  • An elongate longitudinal slot 8 is located in the blade 4 adjacent to the blade cutting edge 6.
  • a second flat, narrow blade 10, similar in form to the first blade 4, is located in sliding contact with the first blade 4.
  • This blade 10 is static, and its forward cutting edge 12 is located a pre-selected distance "h" above the upper surface 13 of the stack 2.
  • the blade 4 is advanced from its rest position illustrated in Figure 1 to cut through the stack 2 thereby forming a slit-shaped passage 14 through the stack 2.
  • the blade 4 is advanced until the slot 0 is clear of the lower face 16 of the stack 2.
  • a pre-cut, pre-selected length of a tow IB of a prepared material is threaded through the slot 0 so as to extend equal distances from each side of the blade 4.
  • the tow 18 is of substantially rectangular cross-section. This tow 18 is made from a ' plurality of layers of woven and/or undirectional material which may be in a pre-impregnated (prepreg) or a dry (without resin) condition.
  • Each layer may be made of thermo-setting and/or thermo-plastic material, including a reinforcement made of Kevlar, carbon or boron.
  • prepreg refers to a reinforcement impregnated with a B-staged resin system.
  • B-staged refers to a resin which has undergone limited curing in order to increase its viscosity and tc.ck so as to improve the handling quality of prepreg fabrics. This is the condition in which thermoset prepregs, whether woven or undirectional, are supplied by the processors and is in no way unique to this particular invention.
  • the layers of tow material (stack) are in a debulked condition which refers to a stack of material consolidated under vacuum at room temperature only.
  • the blade 4 is then withdrawn as shown in Figures 4 and 5, and when the lower edge of the slot 8 is withdrawn to a distance "h" above the upper face 13 of the stack 2, the cutting edge 12 of the static blade 10 cuts the loop of tow 18 to form two independent pieces of tow 20 and 22 as illustrated in Figure 5.
  • the position of the static blade 10, and the length of the tow pieces 20 and 22 are arranged so that the pieces 20 and 22 are of equal length to one another, and each extend equal distances from the upper and lower faces 13 and 16 of the stack 2.
  • the tow pieces 20 and 22 are each folded back onto the upper and lower faces 13 and 16 of the stack 2 so that the end portions of each piece 20 and 22 extend away from one another.
  • the above-mentioned operation is repeated so as to locate a plurality of fastening tows 18 in the stack 2 at required spaced locations from one another, and the stack 2, and the located tow fasteners are then cured.
  • additional layers of intermediate fabric material may be placed over the folded back tow pieces 20 and 22. These additional layers may be dimensioned to cover only the tow pieces 20 and 22, or the entire upper and lower faces 13 and 16 of the stack 2.
  • the stack and the tow fasteners are then cured to encapsulate the tow fasteners.
  • the single stack 2 can be replaced by two stacks of intermediate fabric material which are placed in over lapping relationship as disclosed in our co-pending patent application publication No. GB2238977A.
  • An increase in the thickness of the stack is less than the increase caused by known mechanical fasteners. This is because the cutting blade makes a clean cut through the material of the stack, and any increase in stack thickness is at least partially removed during the subsequent curing process.
  • the joints are self sealing, and in consequence are ideal for use in a hostile environment.
  • One example of such use is for containing fuel in the wing of an aircraft which is used in all weather conditions.
  • the fasteners are lighter than mechanical fasteners.
  • the completed joints are aerodynamically smooth on the outer surfaces of the stack, and consequently it is not necessary to carry out any filling, feathering, smoothing or counter-sinking operations.
  • the joints can be used to provide local reinforcement for the stack, for example at the end of the stack to:-
  • the fastening operation is more labour efficient than the operation with mechanical fasteners because it can be completed in a single automated operation.
  • the fasteners can be located in regions where extra fastening is required, and where fasteners would not normally be used, such as for example with blades and stiffeners webs.
  • the tow fasteners may be employed to increase the structural strength of advanced composite materials, i.e. to prevent delamination of the plies.
  • Galvanic corrosion problems associated with metallic fasteners do not arise with the fasteners_of this invention.
  • High strength or high modulus materials may be selected for the tows in order to accommodate the loading requirements of the fastened material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Textile Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Manufacture Of Motors, Generators (AREA)
  • Linear Motors (AREA)

Abstract

L'appareil servant à attacher les unes aux autres une pluralité de couches horizontales de matériau textile intermédiaire pour former un empilage (2) comprend une première lame de couteau (4). La lame (4) possède un bord coupant avant (6) dans lequel est ménagé un oeillet longitudinal (8). Une seconde lame de couteau plate (10) se trouve en contact avec la première (4) et peut glisser sur celle-ci. La seconde lame (10) est immobile et son bord coupant (12) se trouve à une distance prédéterminée au-dessus de la surface supérieure (13) de l'empilage (2). La première lame (4) s'avance et perce l'empilage (2) jusqu'à ce que l'oeillet (8) dépasse entièrement la face inférieure (16) dudit empilage. Une longueur prédéterminée de filasse (18) est enfilée dans l'oeillet (8) de sorte qu'elle s'étende sur des distances égales des deux côtés de la lame (4). Ensuite, on retire cette lame (4) jusqu'à ce que le bord coupant (12) de la seconde lame (10) sectionne la boucle de filasse ainsi formée pour créer deux morceaux de filasse indépendants (20, 22), puis l'on replie ces morceaux (20, 22) sur les faces supérieure (13) et inférieure (16) de l'empilage (2), et l'on cuit ce dernier.
PCT/GB1991/001033 1990-07-03 1991-06-26 Fabrication d'un materiau composite WO1992000845A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
BR919106615A BR9106615A (pt) 1990-07-03 1991-06-26 Aparelho e processo para fixacao simultanea de uma pluralidade de camadas de material de tecido intermediario,localizadas em uma pilha
FI925805A FI925805A0 (fi) 1990-07-03 1991-06-26 Framstaellning av kompositmaterial
EP91911858A EP0648159A1 (fr) 1990-07-03 1991-06-26 Fabrication d'un materiau composite

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9014770.3 1990-07-03
GB909014770A GB9014770D0 (en) 1990-07-03 1990-07-03 Manufacture of a composite material

Publications (1)

Publication Number Publication Date
WO1992000845A1 true WO1992000845A1 (fr) 1992-01-23

Family

ID=10678613

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1991/001033 WO1992000845A1 (fr) 1990-07-03 1991-06-26 Fabrication d'un materiau composite

Country Status (9)

Country Link
EP (1) EP0648159A1 (fr)
JP (1) JPH05508362A (fr)
AU (1) AU8006791A (fr)
BR (1) BR9106615A (fr)
CA (1) CA2085253A1 (fr)
FI (1) FI925805A0 (fr)
GB (2) GB9014770D0 (fr)
IL (1) IL98585A0 (fr)
WO (1) WO1992000845A1 (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0818289A3 (fr) * 1996-07-13 2000-01-26 Institut für Polymerforschung Dresden e.V. Multicouche préformée renforcée par des fibres, ayant au moins une partie des renforcements alignées suivant l'axe Z, et procédé pour sa fabrication
US6645333B2 (en) * 2001-04-06 2003-11-11 Ebert Composites Corporation Method of inserting z-axis reinforcing fibers into a composite laminate
US7056576B2 (en) 2001-04-06 2006-06-06 Ebert Composites, Inc. 3D fiber elements with high moment of inertia characteristics in composite sandwich laminates
US7105071B2 (en) 2001-04-06 2006-09-12 Ebert Composites Corporation Method of inserting z-axis reinforcing fibers into a composite laminate
US7217453B2 (en) 2001-04-06 2007-05-15 Ebert Compoistes Corporation Composite laminate structure
WO2009013241A1 (fr) * 2007-07-20 2009-01-29 Airbus Operations Gmbh Dispositif et procédé de préparation de mèches découpées à une certaine longueur ainsi que machine pour renforcer une ébauche textile
US7731046B2 (en) 2001-04-06 2010-06-08 Ebert Composites Corporation Composite sandwich panel and method of making same
US7785693B2 (en) 2001-04-06 2010-08-31 Ebert Composites Corporation Composite laminate structure
KR101319703B1 (ko) 2005-07-27 2013-10-17 에보니크 룀 게엠베하 샌드위치 구조물 내 코어 재료의 강화 방법 및 강화된 샌드위치 구조물
US8915201B2 (en) 2007-11-21 2014-12-23 Airbus Operations Gmbh Device and method for producing a reinforced foam material
US9289927B2 (en) 2005-05-27 2016-03-22 Airbus Operations Gmbh Reinforcement of cellular materials
WO2016180420A1 (fr) * 2015-05-12 2016-11-17 Vestas Wind Systems A/S Améliorations apportées à la production de composants d'éolienne
CN109562544A (zh) * 2016-08-09 2019-04-02 日产自动车株式会社 复合材料的成型方法以及复合材料用中间构件
EP3470214A1 (fr) * 2017-10-10 2019-04-17 Groz-Beckert KG Dispositif et procédé de fabrication d'une partie support comportant une pluralité des faisceaux de fibres
WO2021005107A1 (fr) * 2019-07-08 2021-01-14 Societe Internationale Pour Le Commerce Et L'industrie Procede de renforcement d'un panneau et un procede de fabrication de panneau composite mettant en oeuvre un tel procede

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE509755T1 (de) * 2001-08-02 2011-06-15 Ebert Composites Corp Verfahren zum crimpen der oberen und unteren endteile von in der z-achse orientierten fasern in die entsprechende obere und untere oberfläche eines verbundlaminats und verbundlaminat
DE102009010292A1 (de) * 2009-02-24 2010-08-26 Bayerische Motoren Werke Aktiengesellschaft Verfahren zur Herstellung eines faserverstärkten Kunststoffbauteils

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB600177A (en) * 1945-09-29 1948-04-01 Francis Colin Curtis A tufting needle embodying a cutter, wool-feeding action, and length of stitch adjuster
US3142276A (en) * 1962-06-25 1964-07-28 Roger H Mullen Inc Device for forming cut pile fabrics and the like
AU3984772A (en) * 1971-05-05 1973-09-13 Rheem Australia Limited Reinforced plastic mechanical fasteners and method and means for forming them
GB2132134A (en) * 1982-12-17 1984-07-04 Messerschmitt Boelkow Blohm A method of producing component parts from layers of fibre-reinforced plastics material
US4628846A (en) * 1984-05-29 1986-12-16 Societe Europeenne De Propulsion Method for the production of a multi-directional fibrous structure and device for carrying out said method

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB600177A (en) * 1945-09-29 1948-04-01 Francis Colin Curtis A tufting needle embodying a cutter, wool-feeding action, and length of stitch adjuster
US3142276A (en) * 1962-06-25 1964-07-28 Roger H Mullen Inc Device for forming cut pile fabrics and the like
AU3984772A (en) * 1971-05-05 1973-09-13 Rheem Australia Limited Reinforced plastic mechanical fasteners and method and means for forming them
GB2132134A (en) * 1982-12-17 1984-07-04 Messerschmitt Boelkow Blohm A method of producing component parts from layers of fibre-reinforced plastics material
US4628846A (en) * 1984-05-29 1986-12-16 Societe Europeenne De Propulsion Method for the production of a multi-directional fibrous structure and device for carrying out said method

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0818289A3 (fr) * 1996-07-13 2000-01-26 Institut für Polymerforschung Dresden e.V. Multicouche préformée renforcée par des fibres, ayant au moins une partie des renforcements alignées suivant l'axe Z, et procédé pour sa fabrication
US6645333B2 (en) * 2001-04-06 2003-11-11 Ebert Composites Corporation Method of inserting z-axis reinforcing fibers into a composite laminate
US7056576B2 (en) 2001-04-06 2006-06-06 Ebert Composites, Inc. 3D fiber elements with high moment of inertia characteristics in composite sandwich laminates
US7105071B2 (en) 2001-04-06 2006-09-12 Ebert Composites Corporation Method of inserting z-axis reinforcing fibers into a composite laminate
US7217453B2 (en) 2001-04-06 2007-05-15 Ebert Compoistes Corporation Composite laminate structure
US7387147B2 (en) 2001-04-06 2008-06-17 Ebert Composites Corporation Apparatus for inserting z-axis reinforcing fibers into a composite laminate
US7731046B2 (en) 2001-04-06 2010-06-08 Ebert Composites Corporation Composite sandwich panel and method of making same
US7785693B2 (en) 2001-04-06 2010-08-31 Ebert Composites Corporation Composite laminate structure
US9289927B2 (en) 2005-05-27 2016-03-22 Airbus Operations Gmbh Reinforcement of cellular materials
KR101319703B1 (ko) 2005-07-27 2013-10-17 에보니크 룀 게엠베하 샌드위치 구조물 내 코어 재료의 강화 방법 및 강화된 샌드위치 구조물
WO2009013241A1 (fr) * 2007-07-20 2009-01-29 Airbus Operations Gmbh Dispositif et procédé de préparation de mèches découpées à une certaine longueur ainsi que machine pour renforcer une ébauche textile
US8307621B2 (en) 2007-07-20 2012-11-13 Airbus Operations Gmbh Device and method for the provision of cut rovings and machine for the reinforcement of a semi-finished textile product
US8915201B2 (en) 2007-11-21 2014-12-23 Airbus Operations Gmbh Device and method for producing a reinforced foam material
CN107743440B (zh) * 2015-05-12 2020-03-13 维斯塔斯风力系统有限公司 有关风轮机部件生产的改进
WO2016180420A1 (fr) * 2015-05-12 2016-11-17 Vestas Wind Systems A/S Améliorations apportées à la production de composants d'éolienne
CN107743440A (zh) * 2015-05-12 2018-02-27 维斯塔斯风力系统有限公司 有关风轮机部件生产的改进
US10800114B2 (en) 2016-08-09 2020-10-13 Nissan Motor Co., Ltd. Molding method for composite material and intermediate member for composite material
CN109562544A (zh) * 2016-08-09 2019-04-02 日产自动车株式会社 复合材料的成型方法以及复合材料用中间构件
WO2019072641A1 (fr) * 2017-10-10 2019-04-18 Groz-Beckert Kommanditgesellschaft Dispositif et procédé de fabrication d'un élément de support présentant plusieurs faisceaux de fibres
EP3470214A1 (fr) * 2017-10-10 2019-04-17 Groz-Beckert KG Dispositif et procédé de fabrication d'une partie support comportant une pluralité des faisceaux de fibres
US10858771B2 (en) 2017-10-10 2020-12-08 Groz-Beckert Kg Device and method for producing a carrier part having a plurality of fiber bundles
WO2021005107A1 (fr) * 2019-07-08 2021-01-14 Societe Internationale Pour Le Commerce Et L'industrie Procede de renforcement d'un panneau et un procede de fabrication de panneau composite mettant en oeuvre un tel procede
FR3098444A1 (fr) * 2019-07-08 2021-01-15 Societe Internationale Pour Le Commerce Et L'industrie Procédé de renforcement d’un panneau et un procédé de fabrication de panneau composite mettant en œuvre un tel procédé
CN114080317A (zh) * 2019-07-08 2022-02-22 国际贸易和工业协会 用于加固面板的方法和用于使用此方法制造复合面板的方法
EP4238745A3 (fr) * 2019-07-08 2023-12-13 Sicomin Holding Procede de renforcement d'un panneau et un procede de fabrication de panneau composite mettant en oeuvre un tel procede
US11951693B2 (en) 2019-07-08 2024-04-09 Societe Internationale Pour Le Commerce Et L'industrie Method for reinforcing a panel and a method for manufacturing a composite panel implementing such a method
CN114080317B (zh) * 2019-07-08 2024-04-09 国际贸易和工业协会 用于加固面板的方法和用于使用此方法制造复合面板的方法

Also Published As

Publication number Publication date
AU8006791A (en) 1992-02-04
GB9113766D0 (en) 1991-08-14
CA2085253A1 (fr) 1992-01-04
BR9106615A (pt) 1993-06-01
IL98585A0 (en) 1992-07-15
GB9014770D0 (en) 1990-08-22
JPH05508362A (ja) 1993-11-25
GB2245862B (en) 1994-01-26
EP0648159A1 (fr) 1995-04-19
FI925805A7 (fi) 1992-12-21
FI925805L (fi) 1992-12-21
GB2245862A (en) 1992-01-15
FI925805A0 (fi) 1992-12-21

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