JPH02162017A - Manufacture of thick plate-like laminate out of composite material - Google Patents
Manufacture of thick plate-like laminate out of composite materialInfo
- Publication number
- JPH02162017A JPH02162017A JP63318167A JP31816788A JPH02162017A JP H02162017 A JPH02162017 A JP H02162017A JP 63318167 A JP63318167 A JP 63318167A JP 31816788 A JP31816788 A JP 31816788A JP H02162017 A JPH02162017 A JP H02162017A
- Authority
- JP
- Japan
- Prior art keywords
- laminate
- resin
- thick plate
- composite material
- prepreg
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 26
- 238000004519 manufacturing process Methods 0.000 title claims description 11
- 229920005989 resin Polymers 0.000 claims abstract description 32
- 239000011347 resin Substances 0.000 claims abstract description 32
- 239000000463 material Substances 0.000 claims abstract description 29
- 238000000034 method Methods 0.000 claims abstract description 10
- 238000010030 laminating Methods 0.000 claims abstract description 4
- 238000010438 heat treatment Methods 0.000 abstract description 6
- 238000003825 pressing Methods 0.000 abstract description 5
- 239000003822 epoxy resin Substances 0.000 abstract description 3
- 229920000647 polyepoxide Polymers 0.000 abstract description 3
- 230000000740 bleeding effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 238000009826 distribution Methods 0.000 description 4
- 229920001187 thermosetting polymer Polymers 0.000 description 4
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 2
- 239000011151 fibre-reinforced plastic Substances 0.000 description 2
- 239000012783 reinforcing fiber Substances 0.000 description 2
- 239000000565 sealant Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000011089 mechanical engineering Methods 0.000 description 1
- 239000012778 molding material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
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
- B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
- B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
- B29C43/18—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. compression moulding around inserts or for coating 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/36—Moulds for making articles of definite length, i.e. discrete articles
- B29C43/3642—Bags, bleeder sheets or cauls for isostatic pressing
- B29C2043/3644—Vacuum bags; Details thereof, e.g. fixing or clamping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/36—Moulds for making articles of definite length, i.e. discrete articles
- B29C43/3642—Bags, bleeder sheets or cauls for isostatic pressing
- B29C2043/3657—Bags, bleeder sheets or cauls for isostatic pressing additional materials, e.g. permeable bleeder or breather sheets, cloths, blankets
-
- 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
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
- B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
- B29K2105/0854—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns in the form of a non-woven mat
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は中央部と端部との板厚差および余肉部を少なく
した複合材による厚板状積層体を作るための製造方法に
関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a manufacturing method for producing a thick plate-like laminate made of a composite material with a reduced difference in plate thickness between a center portion and an end portion and an excess wall portion.
（従来の技術）
この種の複合材による厚板状積層体の製造方法として、
積層板基材に樹脂を含浸させたプリプレグ材を複数枚積
層した積層体の周縁部および側面部に熱硬化性材料を塗
布し、この熱硬化性材料を硬化させてから積層体を加熱
加圧して厚板状積層体を作るようにしたものは特開昭５
９−４２９３０号公報により知られており、また積層体
の加熱加圧硬化手段としてオートクレーブやホットプレ
スを用いることは応用機械工学１９８５年１月号Ｐ８４
〜Ｐ８７に記載されている。(Prior art) As a method for manufacturing a thick plate-like laminate using this type of composite material,
A thermosetting material is applied to the periphery and side surfaces of a laminate made by laminating multiple sheets of prepreg material impregnated with a resin on a laminate base material, and after the thermosetting material is cured, the laminate is heated and pressurized. A device in which a thick plate-like laminate was made by
It is known from Japanese Patent No. 9-42930, and the use of an autoclave or a hot press as a heat-pressure curing means for a laminate is described in Applied Mechanical Engineering, January 1985 issue, p.84.
- Described on page 87.
一方ＦＲＰ （繊維強化プラスチック）成形用材料は、
樹脂硬化させる際に、内部にボイド等を残さないように
するために、多少の差はあっても樹脂をブリードさせる
ようにしている。On the other hand, FRP (fiber reinforced plastic) molding materials are
When curing the resin, the resin is allowed to bleed even if there is a slight difference in order to avoid leaving voids inside.
（発明が解決しようとする課題）
積層板基材に樹脂を含浸させたプリプレグ材を素材とし
て厚板状積層体を製造する場合には、プリプレグ材を複
数枚積層した積層体を、真空状態で加熱加圧して硬化し
て行うが、樹脂のフロー温度までのブリードは、表面か
らより側面からの方が多くなり、作られる厚板状積層体
の板厚は、均一さに欠け、厚板状積層体内部の樹脂と強
化繊維との分布が不均一となり、周辺部に位置する樹脂
に対する強化繊維分布過剰部分を厚板状積層体から切り
捨てるようにしている。またこのようにして作られた厚
板状積層体は、表面側と裏面側との樹脂含有率が異なる
ために、硬化処理後において反り現象が発生することが
ある。(Problem to be solved by the invention) When manufacturing a thick plate-like laminate using a prepreg material in which a laminate base material is impregnated with a resin, the laminate in which a plurality of prepreg materials are laminated is placed in a vacuum state. This is done by heating and pressurizing and curing, but the bleeding up to the flow temperature of the resin is more from the sides than from the surface, and the thickness of the thick plate-like laminate that is produced lacks uniformity. The distribution of the resin and reinforcing fibers inside the laminate becomes non-uniform, and the portion where the reinforcing fibers are excessively distributed relative to the resin located at the periphery is cut off from the thick plate-like laminate. In addition, since the resin content of the thick plate-like laminate produced in this way is different between the front side and the back side, warpage may occur after the curing process.
また上記積層体の周縁部および側面部に熱硬化性材料を
塗布し、この熱硬化性材料を硬化させてから積層体を加
熱加圧して厚板状積層体を作るようにしたものでは、厚
板状積層体が比較的薄いものには有効であっても、１．
６ミリ程度の厚さの航空宇宙機を対称とする厚板状積層
体には適していない。Furthermore, in the case where a thermosetting material is applied to the peripheral edge and side surfaces of the laminate, the thermosetting material is cured, and then the laminate is heated and pressed to form a thick plate-like laminate. Although it is effective for relatively thin plate-like laminates, 1.
It is not suitable for thick plate-like laminates intended for aerospace aircraft with a thickness of about 6 mm.
本発明は上記した点に鑑みてなされたもので、中央部と
端部との板厚差および余肉部を少なくした複合材による
厚板状積層体の製造方法を提供することを目的とする。The present invention has been made in view of the above-mentioned points, and an object of the present invention is to provide a method for manufacturing a thick plate-like laminate made of a composite material that reduces the thickness difference between the center and end portions and the excess thickness. .
（課題を解決するための手段）
本発明の複合材による厚板状積層体の製造方法は、積層
板基材に樹脂を含浸させたプリプレグ材を複数枚積層し
た積層体を、真空状態で樹脂のフロー温度で加圧して複
合材シートを作り、この複合材シートを所要枚数積層し
、この積層体を真空状態で加熱加圧して硬化した工程を
有して構成されている。(Means for Solving the Problems) The method for manufacturing a thick plate-like laminate using a composite material of the present invention is to laminate a laminate in which a plurality of prepreg materials in which a laminate base material is impregnated with resin is laminated in a vacuum state. The method includes the following steps: forming a composite sheet by applying pressure at a flow temperature of , laminating the required number of composite sheets, and curing the laminate by heating and pressurizing it in a vacuum state.
（作 用）
本発明の複合材による厚板状積層体の製造方法において
は、まず積層板基材に樹脂を含浸させたプリプレグ材を
複数枚積層した積層体を真空状態で樹脂のフロー温度で
加圧して均一な樹脂ブリードとし、作られた複合材シー
トを所要枚数積層し、この積層体を真空状態で加熱加圧
して硬化して硬化時において端部からの過大な樹脂ブリ
ードを防ぎ、中央部と端部との板厚差および余肉部を少
なくした複合材による厚板状積層体を作る。(Function) In the method for manufacturing a thick plate-like laminate using a composite material of the present invention, first, a laminate in which a plurality of prepreg materials in which a laminate base material is impregnated with a resin is laminated in a vacuum state at a resin flow temperature. Pressure is applied to achieve uniform resin bleed, the required number of composite sheets are laminated, and this laminate is cured by heating and pressurizing in a vacuum to prevent excessive resin bleed from the edges during curing. To produce a thick plate-like laminate made of composite material with reduced plate thickness difference between parts and ends and excess thickness.
（実施例） 以下本発明の一実施例を図面につき説明する。(Example) An embodiment of the present invention will be described below with reference to the drawings.
第２図は本発明の複合材による厚板状積層体の製造方法
に使用される真空バッグ成形硬化装置を示し、□この真
空バッグ成形硬化装置は、定板１と、プリプレグ材２を
囲む空間を形成するダム３と、プリプレグ材２の上面に
穴あき離型フィルム４を介して置かれるブリーダ５と、
バッグシーラント６を介して定板１の上方に真空空間７
を形成するバッグ８とを有して構成されている。FIG. 2 shows a vacuum bag forming and curing apparatus used in the method for manufacturing a thick plate-like laminate made of composite materials of the present invention. a dam 3 that forms a
A vacuum space 7 is provided above the fixed plate 1 via the bag sealant 6.
The bag 8 is configured to include a bag 8 that forms a
本発明の複合材による厚板状積層体の製造方法において
は、第１図に示すように積層板基材に樹脂を含浸させた
プリプレグ材を複数枚積層した積層体が用意される。こ
のプリプレグ材の厚さすなわちプリプレグ材の積層枚数
は、作られるべき厚板状積層体をたとえば４枚の複合材
シートで作る場合には厚板状積層体の厚さの１／４の厚
さに成形される枚数に設定される。In the method for manufacturing a thick plate-like laminate using a composite material according to the present invention, a laminate is prepared in which a plurality of prepreg materials in which a laminate base material is impregnated with a resin are laminated, as shown in FIG. The thickness of this prepreg material, that is, the number of layers of prepreg material, is 1/4 of the thickness of the thick plate-like laminate when the thick plate-like laminate to be made is made of, for example, four composite material sheets. It is set to the number of sheets to be molded.
このように積層した積層体は、定板１の上に離型フィル
ム９を介して置かれ、図示しない真空装置を介して内部
空間７を真空状態にした後、たとえばプリプレグ材が１
８０℃硬化タイプのエポキシ樹脂の場合には、樹脂のフ
ロー温度の６０℃〜１３０℃の適切な条件下でプリプレ
グ４イを加熱加圧して複合材シート１０を成形する。こ
の複合材シート１０は、主部１１と余肉部１２とからな
っている。The laminate thus laminated is placed on the fixed plate 1 with a release film 9 in between, and after the internal space 7 is evacuated via a vacuum device (not shown), for example, the prepreg material is
In the case of an 80° C. curing type epoxy resin, the composite sheet 10 is formed by heating and pressing the prepreg 4 under appropriate conditions of the resin flow temperature of 60° C. to 130° C. This composite sheet 10 consists of a main portion 11 and an extra portion 12.
上記複合材シート１０は、複数枚たとえば４枚積層され
、定板１の土に離型フィルム９を介して置かれ、図示し
ない真空装置を介して内部空間７を真空状態にした後、
プリプレグ材が１８０℃硬化タイプのエポキシ樹脂の場
合には、１８０℃で加熱、３〜７ ｋｇ ／ ｃ−で加
圧して厚板状積層体を成形する。A plurality of composite sheets 10, for example four, are laminated and placed on the soil of the fixed plate 1 with a release film 9 in between, and after the internal space 7 is evacuated via a vacuum device (not shown),
When the prepreg material is a 180°C curing type epoxy resin, it is heated at 180°C and pressurized at 3 to 7 kg/c- to form a thick plate-like laminate.
このようにして作られる厚板状積層体は、たとえば航空
宇宙機の翼構造部材に適用される。The thick plate-like laminate produced in this manner is applied, for example, to a wing structural member of an aerospace vehicle.
第３図は厚板状積層体の１ブライ当たりの平均板厚分布
と積層プリプレグ樹脂ブリード条件との関係を示す図で
あり、厚板状積層体を複数に分割した複合材シートを積
層したもので構成すれば、１ブライ当たりの平均板厚分
布を目標値０．１３〜０．１４の範囲内に入れることが
できた。Figure 3 is a diagram showing the relationship between the average plate thickness distribution per brie of a thick plate-like laminate and the laminated prepreg resin bleed conditions, and shows the relationship between the average plate thickness distribution per brie of a thick plate-like laminate and the laminated prepreg resin bleed conditions. With this structure, the average plate thickness distribution per braai could be kept within the target value range of 0.13 to 0.14.
第４図は厚板状積層体の樹脂含有量と測定部位との関係
を示す図であり、厚板状積層体における樹脂含有量が各
部位でほぼ等しく、厚板状積層体に反りが生じないこと
が分かる。Figure 4 is a diagram showing the relationship between the resin content of the thick plate-like laminate and the measurement site, and shows that the resin content in the thick plate-like laminate is almost equal in each part, and the thick plate-like laminate is warped. I can see that there isn't.
（発明の効果）
以上述べたように本発明によれば、櫃層板基材に樹脂を
含浸させたプリプレグ材を複数枚積層した積層体を、真
空状態で樹脂のフロー温度で加圧して複合材シートを作
り、この複合材シートを所要枚数積層し、この積層体を
真空状態で加熱加圧して硬化し厚板状積層体を作るよう
にしたので、最終積層体の硬化時に端部からの過大な樹
脂ブリードを防ぐことができ、また作られる厚板状積層
体の樹脂含有量は各部位でほぼ等しく、製品に反りが生
ぜず、しかも余肉部を従来の５０ミリから５ミリ程度ま
で減少できた。(Effects of the Invention) As described above, according to the present invention, a laminate in which a plurality of prepreg materials, each of which is a resin-impregnated resin-impregnated laminate is laminated in a vacuum state, is composited by applying pressure at the flow temperature of the resin. The required number of composite sheets were laminated, and the laminate was cured by heating and pressure in a vacuum to create a thick plate-like laminate, so that when the final laminate was cured, there was no leakage from the edges. Excessive resin bleed can be prevented, and the resin content of the thick plate-like laminate produced is almost equal in each part, so the product does not warp, and the excess thickness can be reduced from the conventional 50 mm to about 5 mm. I was able to reduce it.
本発明の複合材による厚板状積層体の製造方法に使用さ
れる真空バック成形硬化装置を示す図、第３図はは厚板
状積層体の１ブライ当たりの平均板厚と積層プリプレグ
樹脂ブリード条件との関係を示す図、第４図は厚板状積
層体の樹脂含有ｍとＡｐｌ定部位との関係を示す図であ
る。A diagram showing a vacuum bag molding and curing device used in the method for producing a thick plate-like laminate made of composite materials of the present invention, and Fig. 3 shows the average plate thickness per brie of the thick plate-like laminate and the laminated prepreg resin bleed. FIG. 4 is a diagram showing the relationship between the resin content m and the Apl constant portion of the thick plate-like laminate.
１・・・定板、２・・・プリプレグ材、５・・・ブリー
ダ、６・・・バッグシーラント、７・・・真空空間、８
・・・バッグ。DESCRIPTION OF SYMBOLS 1... Fixed plate, 2... Prepreg material, 5... Bleeder, 6... Bag sealant, 7... Vacuum space, 8
···bag.
Claims (1)
層した積層体を、真空状態で樹脂のフロー温度で加圧し
て複合材シートを作り、この複合材シートを所要枚数積
層し、この積層体を真空状態で加熱加圧して硬化し厚板
状積層体を作るようにしたことを特徴とする複合材によ
る厚板状積層体の製造方法。A laminate made by laminating multiple sheets of prepreg material with resin impregnated into a laminate base material is pressurized at the flow temperature of the resin in a vacuum state to create a composite sheet, and the required number of composite sheets are laminated to create a composite sheet. 1. A method for manufacturing a thick plate-like laminate using a composite material, characterized in that the body is heated and pressurized in a vacuum to harden the plate-like laminate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63318167A JP2685554B2 (en) | 1988-12-16 | 1988-12-16 | Method for manufacturing a slab laminate with a composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63318167A JP2685554B2 (en) | 1988-12-16 | 1988-12-16 | Method for manufacturing a slab laminate with a composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH02162017A true JPH02162017A (en) | 1990-06-21 |
| JP2685554B2 JP2685554B2 (en) | 1997-12-03 |
Family
ID=18096222
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63318167A Expired - Fee Related JP2685554B2 (en) | 1988-12-16 | 1988-12-16 | Method for manufacturing a slab laminate with a composite material |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2685554B2 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008501555A (en) * | 2004-06-09 | 2008-01-24 | インダストリアル コンポジテス エンジニアリング プロプライエタリー リミテッド | Method for forming or curing polymer composite |
| FR2929167A1 (en) * | 2008-03-27 | 2009-10-02 | Airbus France Sa | METHOD FOR MANUFACTURING FLAN OF THERMOPLASTIC COMPOSITE MATERIAL, ASSOCIATED TOOLING FOR MANUFACTURING AND APPLICATION OF PROCESS TO REALIZATION OF AIRCRAFT STRUCTURE PARTS |
| JP2010503549A (en) * | 2006-09-15 | 2010-02-04 | エアバス・フランス | Method for manufacturing a panel formed of a thermoplastic composite |
| US8545744B2 (en) | 2007-03-29 | 2013-10-01 | Gurit (Uk) Ltd. | Fibre-reinforced composite moulding and manufacture thereof |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5686997B2 (en) | 2010-07-15 | 2015-03-18 | 三菱重工業株式会社 | Method for producing resin matrix composite |
-
1988
- 1988-12-16 JP JP63318167A patent/JP2685554B2/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008501555A (en) * | 2004-06-09 | 2008-01-24 | インダストリアル コンポジテス エンジニアリング プロプライエタリー リミテッド | Method for forming or curing polymer composite |
| JP4836205B2 (en) * | 2004-06-09 | 2011-12-14 | インダストリアル コンポジテス エンジニアリング プロプライエタリー リミテッド | Method for forming or curing polymer composite |
| JP2010503549A (en) * | 2006-09-15 | 2010-02-04 | エアバス・フランス | Method for manufacturing a panel formed of a thermoplastic composite |
| US8545744B2 (en) | 2007-03-29 | 2013-10-01 | Gurit (Uk) Ltd. | Fibre-reinforced composite moulding and manufacture thereof |
| US9199431B2 (en) | 2007-03-29 | 2015-12-01 | Gurit (Uk) Ltd. | Fibre-reinforced composite molding and manufacture thereof |
| FR2929167A1 (en) * | 2008-03-27 | 2009-10-02 | Airbus France Sa | METHOD FOR MANUFACTURING FLAN OF THERMOPLASTIC COMPOSITE MATERIAL, ASSOCIATED TOOLING FOR MANUFACTURING AND APPLICATION OF PROCESS TO REALIZATION OF AIRCRAFT STRUCTURE PARTS |
| WO2009125122A2 (en) * | 2008-03-27 | 2009-10-15 | Airbus France | Method for manufacturing a blank made of a thermoplastic composite, associated manufacturing tool and application of the method to the production of structural aircraft parts |
| WO2009125122A3 (en) * | 2008-03-27 | 2009-11-26 | Airbus Operations | Method for manufacturing a blank made of a thermoplastic composite, associated manufacturing tool and application of the method to the production of structural aircraft parts |
| US8425705B2 (en) | 2008-03-27 | 2013-04-23 | Airbus Operations | Method of manufacturing a blank made from thermoplastic composite material, associated manufacturing tool and use of the method to produce structural aircraft parts |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2685554B2 (en) | 1997-12-03 |
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