JPH04364929A - Method for molding composite material - Google Patents
Method for molding composite materialInfo
- Publication number
- JPH04364929A JPH04364929A JP3141797A JP14179791A JPH04364929A JP H04364929 A JPH04364929 A JP H04364929A JP 3141797 A JP3141797 A JP 3141797A JP 14179791 A JP14179791 A JP 14179791A JP H04364929 A JPH04364929 A JP H04364929A
- Authority
- JP
- Japan
- Prior art keywords
- composite material
- prepreg
- cylindrical mandrel
- laminated
- composite
- 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 70
- 238000000034 method Methods 0.000 title claims description 17
- 238000000465 moulding Methods 0.000 title description 10
- 229920005989 resin Polymers 0.000 claims abstract description 18
- 239000011347 resin Substances 0.000 claims abstract description 18
- 238000010438 heat treatment Methods 0.000 claims abstract description 14
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims abstract description 11
- 238000006073 displacement reaction Methods 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 11
- 238000002844 melting Methods 0.000 claims description 6
- 230000008018 melting Effects 0.000 claims description 6
- 230000037303 wrinkles Effects 0.000 abstract description 8
- 238000001723 curing Methods 0.000 abstract 1
- 238000003825 pressing Methods 0.000 abstract 1
- 239000000835 fiber Substances 0.000 description 15
- 238000010586 diagram Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 8
- 239000010410 layer Substances 0.000 description 8
- 229920001187 thermosetting polymer Polymers 0.000 description 6
- 238000007796 conventional method Methods 0.000 description 4
- 238000010030 laminating Methods 0.000 description 4
- 238000003475 lamination Methods 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- -1 polypropylene Polymers 0.000 description 4
- 230000003014 reinforcing effect Effects 0.000 description 4
- 239000004744 fabric Substances 0.000 description 3
- 239000011521 glass Substances 0.000 description 3
- 239000004698 Polyethylene Substances 0.000 description 2
- 239000004743 Polypropylene Substances 0.000 description 2
- 238000009730 filament winding Methods 0.000 description 2
- 239000000155 melt Substances 0.000 description 2
- 229920000573 polyethylene Polymers 0.000 description 2
- 229920001155 polypropylene Polymers 0.000 description 2
- 229920003002 synthetic resin Polymers 0.000 description 2
- 239000000057 synthetic resin Substances 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
Landscapes
- Moulding By Coating Moulds (AREA)
Abstract
Description
【０００１】0001
【産業上の利用分野】本発明は、外面にしわおよび内部
に空気溜まりを形成することなく、中空円筒形ないし中
空形状の複合材部品を成形するための複合材の成形方法
に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method of forming a composite material for forming a hollow cylindrical or hollow-shaped composite material part without forming wrinkles on the outer surface or air pockets inside.
【０００２】0002
【従来の技術】中空円筒形ないし中空形状の複合材部品
を成形するには、複合材料（ロービング材およびプリプ
レグ）をフィラメントワインディングにより金属製マン
ドレルの外面に巻き付け、その上に副資材と熱収縮テー
プで覆い、加圧、加熱、硬化して成形するようにしてい
る。[Prior Art] In order to form a hollow cylindrical or hollow-shaped composite part, the composite material (roving material and prepreg) is wound around the outer surface of a metal mandrel by filament winding, and the auxiliary material and heat shrink tape are then wrapped around the outer surface of a metal mandrel. The material is then covered with plastic, pressurized, heated, and hardened to form the material.
【０００３】たとえば、図７に示すように、芯金２０に
熱硬化性樹脂含浸ガラスクロスを巻き付け、この上に２
種類の糸条繊維を図８に示すように袋状あるいは筒状２
２に編み上げて伸縮性をもたせた状態の複合材を装着し
、両端を張り熱硬化性樹脂含浸ガラスクロスへの密着状
態を保持し、この外周面にポリプロピレンやポリエチレ
ン等のテープ２３を巻き付け、加熱、硬化して管状体を
成形する技術手段は特開昭６３−３０７９３３号公報に
記載されている。For example, as shown in FIG. 7, a thermosetting resin-impregnated glass cloth is wrapped around a core bar 20, and two
As shown in Fig.
The composite material 2 is knitted to give it elasticity, and both ends are stretched to keep it in close contact with the thermosetting resin-impregnated glass cloth.A tape 23 made of polypropylene or polyethylene is wrapped around the outer circumferential surface of the composite material and heated. A technical means for curing and forming a tubular body is described in Japanese Patent Application Laid-Open No. 63-307933.
【０００４】また、図９に示すように、芯金２４に高強
度繊維樹脂含浸プリプレグ２５を巻き付け、その上に高
強度繊維樹脂補強テープ２６を５〜１０ｋｇの張力で巻
き付けることでプリプレグに密着させ、この補強テープ
の外周面に合成樹脂製熱収縮チューブ２７を装着し、加
熱炉で焼成して管状体を成形する技術手段は特開平２−
９６２１号公報に記載されている。Further, as shown in FIG. 9, a high-strength fiber resin-impregnated prepreg 25 is wrapped around the core bar 24, and a high-strength fiber resin reinforcing tape 26 is wrapped thereon with a tension of 5 to 10 kg to tightly adhere to the prepreg. A technical means of attaching a synthetic resin heat shrink tube 27 to the outer circumferential surface of this reinforcing tape and firing it in a heating furnace to form a tubular body is disclosed in Japanese Patent Application Laid-Open No. 2000-2-
It is described in Publication No. 9621.
【０００５】また、図１０に示すように、スチールやア
ルミニウムのような金属パイプまたは棒状のマンドレル
２８に、スリップ層２９を介してプリプレグ３０を３〜
５層積層し、これらをバギング材３１で覆い、樹脂が溶
融する温度にプリプレグを加熱し、プリプレグの樹脂を
吸い取りながら積層を繰り返し行ない、ついで加圧、加
熱、硬化して管状体を成形する技術手段は特公昭５９−
３３２８６号公報に記載されている。Further, as shown in FIG. 10, three to three prepregs 30 are attached to a metal pipe or rod-shaped mandrel 28 such as steel or aluminum with a slip layer 29 interposed therebetween.
A technique of laminating five layers, covering them with bagging material 31, heating the prepreg to a temperature where the resin melts, repeating the lamination while sucking up the resin from the prepreg, and then pressurizing, heating, and hardening to form a tubular body. The means is Special Public Service 1984-
It is described in Publication No. 33286.
【０００６】[0006]
【発明が解決しようとする課題】熱硬化性樹脂含浸ガラ
スクロスの上に２種類の糸条繊維の袋状あるいは筒状体
を装着する方法では、ポリプロピレンやポリエチレン等
のテープの熱硬化時の熱収縮作用により、図１１に示す
ように、筒状体３２にしわやすじ３３が形成され、また
、熱硬化時に発生するガス等３４が外部に流出されずに
内部に残ってしまう。また、高強度繊維樹脂含浸プリプ
レグの上に高強度繊維樹脂補強テープを張力を加えなが
ら巻き付け、この補強テープの外面に合成樹脂製熱収縮
チューブを装着して焼成する方法では、加熱焼成時に熱
収縮チューブが収縮し、同じように筒状体の表面にしわ
または凹部が形成され、熱硬化時に発生するガス等が外
部に流出されずに内部に残ってしまう。また、金属マン
ドレルに、スリップ層を介してプリプレグを積層し、こ
れらをバギング材で覆い、樹脂が溶融する温度にプリプ
レグを加熱して、プリプレグの樹脂を吸い取る方法では
、樹脂抜きされたプリプレグの積層径は、樹脂抜き前の
積層径より小径となるため、繊維がだぶついた状態とな
り、樹脂抜き各積層単位表面層にしわが発生し、繊維の
だぶつきによる繊維の重なりやしわの形成により積層時
に巻き込んだ空気が内部に残ってしまう。[Problems to be Solved by the Invention] In the method of attaching a bag-like or cylindrical body made of two types of yarn fibers onto a glass cloth impregnated with a thermosetting resin, it is difficult to avoid heat generation during thermosetting of polypropylene, polyethylene, etc. Due to the shrinkage action, wrinkles and streaks 33 are formed in the cylindrical body 32, as shown in FIG. 11, and gases etc. 34 generated during thermosetting are not discharged to the outside but remain inside. In addition, a method in which a high-strength fiber resin reinforcing tape is wrapped around a high-strength fiber resin-impregnated prepreg while applying tension, and a synthetic resin heat-shrinkable tube is attached to the outer surface of this reinforcing tape and then fired, heat shrinks during heating and baking. When the tube contracts, wrinkles or depressions are similarly formed on the surface of the cylindrical body, and gas generated during thermosetting remains inside without flowing out. In addition, in the method of laminating prepregs on a metal mandrel through a slip layer, covering them with bagging material, heating the prepregs to a temperature where the resin melts, and sucking up the resin from the prepregs, the resin-free prepregs are laminated. Since the diameter is smaller than the laminated diameter before resin removal, the fibers become loose and wrinkles occur on the surface layer of each laminated unit after resin removal. However, air remains inside.
【０００７】本発明は上記した点に鑑みてなされたもの
で、中空複合材部品の表面にしわやすじがなくかつ内部
に空気やガスの溜まりがなく、しかも内径の精度を高く
する複合材の成形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 is a composite material that has no wrinkles or streaks on the surface of the hollow composite material part, no air or gas accumulation inside, and has high precision in the inner diameter. The purpose is to provide a molding method.
【０００８】[0008]
【課題を解決するための手段】本発明の複合材の成形方
法は、複合材のプリプレグを温度で変位する形状記憶合
金で形成した筒状マンドレルに積層し、積層した複合材
のプリプレグを通気性シートで覆い、その上に真空バッ
クフィルムを被せ、筒状マンドレルを複合材のプリプレ
グの樹脂の溶融温度より低い温度で加熱して、筒状マン
ドレルを形状記憶合金に記憶された変位量だけ膨張させ
、ついで、筒状マンドレルに積層した複合材のプリプレ
グを加圧、加熱、硬化して構成される。[Means for Solving the Problems] The method for forming a composite material of the present invention involves laminating composite material prepregs on a cylindrical mandrel made of a shape memory alloy that changes with temperature, and making the laminated composite material prepregs air-permeable. Cover the sheet with a vacuum backing film, heat the cylindrical mandrel at a temperature lower than the melting temperature of the composite prepreg resin, and expand the cylindrical mandrel by the amount of displacement memorized by the shape memory alloy. Then, the composite material prepreg is laminated on a cylindrical mandrel and then pressurized, heated, and cured.
【０００９】[0009]
【作用】本発明の複合材の成形方法においては、形状記
憶合金で形成した筒状マンドレルに積層した複合材のプ
リプレグは、加熱加圧成形を行なう際に、複合材のプリ
プレグの樹脂の溶融が始まる前の温度で、筒状マンドレ
ルが変位して大径になり、この筒状マンドレルの変位に
より、積層した複合材のプリプレグは均一に内側より外
側に押し広げられ、複合材の繊維が均一に広がることで
、成形時に巻き込んだ空気や硬化時に内部に発生するガ
スは容易に外部に流出され、成形される成形品は表面に
しわやすじのない内径精度を高いものとなる。[Function] In the composite material forming method of the present invention, the composite material prepreg laminated on the cylindrical mandrel formed of the shape memory alloy is heated and pressed, and the resin of the composite material prepreg is melted. At the temperature before starting, the cylindrical mandrel is displaced and becomes larger in diameter. Due to the displacement of the cylindrical mandrel, the prepreg of the laminated composite material is evenly spread from the inside to the outside, and the fibers of the composite material are evenly distributed. By expanding, the air drawn in during molding and the gas generated inside during curing can easily flow out to the outside, resulting in a molded product with high inner diameter accuracy without wrinkles or streaks on the surface.
【００１０】0010
【実施例】以下本発明の一実施例を図面につき説明する
。図１は本発明の複合材の成形方法の工程順を示す図で
あり、（ａ）には形状記憶合金で形成した筒状マンドレ
ル１が示されている。この形状記憶合金はたとえばＴｉ
−Ｎｉ系合金であって、複合材のプリプレグの樹脂の溶
融温度より低い温度（８５〜９５℃）で体積が１３％程
度大きくなる特性を有するものが選定される。この筒状
マンドレル１の外面に、複合材のプリプレグを巻き付け
ることでプリプレグ２が形成される。この複合材のプリ
プレグ積層方法は、（ｂ）に示すように複合材のプリプ
レグ２ａを積層するものと、（ｃ）に示すようにプリプ
レグ２ａおよびロービング材２ｂを積層するものと、（
ｄ）に示すようにロービング材２ｂを積層するものに分
けられる。このロービング材２ｂの巻き付けは、通常の
フィラメントワインディング手段により行われる。DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is a diagram showing the process order of the method for forming a composite material of the present invention, and (a) shows a cylindrical mandrel 1 formed of a shape memory alloy. This shape memory alloy is, for example, Ti
A -Ni-based alloy is selected that has the characteristic that the volume increases by about 13% at a temperature (85 to 95°C) lower than the melting temperature of the resin of the prepreg of the composite material. A prepreg 2 is formed by wrapping a composite material prepreg around the outer surface of the cylindrical mandrel 1. There are two methods for laminating prepregs of this composite material: as shown in (b), the prepreg 2a of the composite material is laminated, as shown in (c), the prepreg 2a and the roving material 2b are laminated, and (
As shown in d), roving materials 2b are laminated. This winding of the roving material 2b is performed by a normal filament winding means.
【００１１】ついで、筒状マンドレル１に積層された複
合材のプリプレグ層２は、（ｅ）で示すように通気性シ
ート３で覆われ、その上に真空バックフィルム４が被せ
られる。この真空バックフィルム４に設けた吸込口５は
図示しない真空装置に連結され、真空バックフィルム４
の内部空間を真空にする。符号６は複合材のプリプレグ
の加熱温度を検出するための温度センサである。[0011] Next, the prepreg layer 2 of the composite material laminated on the cylindrical mandrel 1 is covered with a breathable sheet 3, as shown in (e), and a vacuum backing film 4 is placed thereon. The suction port 5 provided in the vacuum back film 4 is connected to a vacuum device (not shown), and the vacuum back film 4
evacuate the internal space of the Reference numeral 6 is a temperature sensor for detecting the heating temperature of the prepreg of the composite material.
【００１２】図２は筒状マンドレル１に積層された複合
材のプリプレグ層２を加熱する前の状態を示し、プリプ
レグ層２と真空バックフィルム４の間に、離型フィルム
７、熱収縮テープ８および通気性シート３が配置されて
いる。図１の（ｅ）で示す筒状マンドレル１に積層され
た複合材のプリプレグ層２は、真空バックフィルム４の
内部を真空にすることにより積層時に巻き込んだ空気を
外部に除去した後、図示しないオートクレーブに送られ
、ここで加圧、加熱、硬化処理を施される。FIG. 2 shows the prepreg layer 2 of the composite material laminated on the cylindrical mandrel 1 before heating. and a breathable sheet 3 are arranged. The prepreg layer 2 of the composite material laminated on the cylindrical mandrel 1 shown in FIG. It is sent to an autoclave, where it is pressurized, heated, and hardened.
【００１３】オートクレーブで加熱される筒状マンドレ
ル１は、加熱前では直径Ｄ１ （図２）であるが、筒状
マンドレル１は、複合材のプリプレグの樹脂の溶融温度
より低い温度（８５〜９５℃）で体積が１３％程度大き
くなる特形状記憶合金で形成されているため、加熱され
ることにより直径はＤ２ （図３）に拡径し、この筒状
マンドレル１の拡径に伴ない、熱収縮テープ８により拘
束された複合材のプリプレグ層２は半径方向に均一に押
し広げられ、複合材のプリプレグは、図５に示す加熱前
直径Ｄ１ の状態から、図６に示す直径Ｄ２に拡径し、
複合材のプリプレグの繊維束Ｆ、Ｆの間隔は図５の密の
状態から図６の疎の状態に変化する。さらに加熱処理を
受け、加熱温度が複合材のプリプレグの樹脂の溶融温度
に達すると、プリプレグの樹脂が溶融し、硬化処理され
て中空円筒形ないし中空形状の複合材部品を成形する。
この場合、樹脂を溶融し硬化するときに発生するガス等
は複合材のプリプレグの繊維束Ｆ、Ｆの間隔が図６の疎
の状態にあるため、繊維束Ｆ、Ｆの間を通って外部に流
れ、また、複合材のプリプレグは、図５に示す直径Ｄ１
から図６に示す直径Ｄ２ に拡径するので、複合材の
プリプレグは積層時の巻径より大きくなり、積層後バギ
ングによって生じた繊維束のだぶつきやねじれがない。The cylindrical mandrel 1 heated in an autoclave has a diameter D1 (FIG. 2) before heating, but the cylindrical mandrel 1 is heated at a temperature lower than the melting temperature of the resin of the composite prepreg (85 to 95°C). ), the diameter increases to D2 (Fig. 3) when heated, and as the diameter of the cylindrical mandrel 1 increases, the heat The prepreg layer 2 of the composite material restrained by the shrink tape 8 is uniformly spread in the radial direction, and the prepreg of the composite material expands from the diameter D1 before heating shown in FIG. 5 to the diameter D2 shown in FIG. 6. death,
The spacing between the fiber bundles F, F of the prepreg of the composite material changes from the dense state shown in FIG. 5 to the sparse state shown in FIG. It is further subjected to heat treatment, and when the heating temperature reaches the melting temperature of the resin of the prepreg of the composite material, the resin of the prepreg is melted and hardened to form a hollow cylindrical or hollow-shaped composite part. In this case, the gas generated when melting and curing the resin passes between the fiber bundles F and F of the prepreg of the composite material and goes outside because the spacing between the fiber bundles F and F of the composite prepreg is sparse as shown in Figure 6. The prepreg of the composite material has a diameter D1 shown in FIG.
Since the diameter is expanded from 1 to 2 to the diameter D2 shown in FIG. 6, the prepreg of the composite material becomes larger than the winding diameter at the time of lamination, and there is no bagging or twisting of the fiber bundles caused by bagging after lamination.
【００１４】本発明の複合材の成形方法により成形され
た複合材部品は、表面にしわやすじがなく、滑らかな面
となる。上記筒状マンドレル１は、加熱硬化後温度を下
げることすなわち全体を冷却することにより、筒状マン
ドレル１の直径は、図３の直径Ｄ２ から図４の直径Ｄ
１に変化し、成形された複合材部品と筒状マンドレル１
の外面との間に間隙Ｌ（Ｄ２ −Ｄ１ ）が形成され、
複合材部品の筒状マンドレル１からの抜き取りが容易と
なる。Composite parts molded by the composite molding method of the present invention have smooth surfaces without wrinkles or streaks. The diameter of the cylindrical mandrel 1 is changed from the diameter D2 in FIG. 3 to the diameter D in FIG.
1, molded composite parts and cylindrical mandrel 1
A gap L (D2 - D1) is formed between the outer surface of the
The composite material component can be easily removed from the cylindrical mandrel 1.
【００１５】[0015]
【発明の効果】以上述べたように本発明によれば、複合
材のプリプレグを温度で変位する形状記憶合金で形成し
た筒状マンドレルに積層し、積層した複合材のプリプレ
グを通気性シートで覆い、その上に真空バックフィルム
を被せ、筒状マンドレルを加熱して、筒状マンドレルを
形状記憶合金に記憶された変位量だけ膨張させ、ついで
、筒状マンドレルに積層した複合材のプリプレグを加圧
、加熱、硬化して成形するので、積層時やバギング時に
生じた繊維のねじれ、だぶつき、ちぢみは筒状マンドレ
ルの拡径により解消され、硬化時に発生するガス等は複
合材のプリプレグの広げられた繊維間を通り外部に放出
され、ガスの内部溜まりが残らず、したがって表面が滑
らかでかつ内径の精度の高い中空円筒形ないし中空形状
の複合材部品成形品を成形できる。As described above, according to the present invention, composite prepregs are laminated on a cylindrical mandrel made of a shape memory alloy that changes with temperature, and the laminated composite prepregs are covered with a breathable sheet. , a vacuum backing film is placed on top of it, the cylindrical mandrel is heated, the cylindrical mandrel is expanded by the amount of displacement memorized by the shape memory alloy, and then the composite material prepreg laminated on the cylindrical mandrel is pressurized. Since it is formed by heating and curing, the twisting, bagging, and shrinkage of the fibers that occur during lamination and bagging are eliminated by expanding the diameter of the cylindrical mandrel, and gases generated during curing are removed by spreading the composite material prepreg. The gas is released to the outside through the fibers, leaving no internal pockets of gas, making it possible to mold hollow cylindrical or hollow-shaped composite parts with smooth surfaces and highly accurate inner diameters.
【図１】本発明による複合材の成形方法の工程順を示す
図。FIG. 1 is a diagram showing the process order of a method for molding a composite material according to the present invention.
【図２】筒状マンドレルの変形前の状態を示す図。FIG. 2 is a diagram showing a state of a cylindrical mandrel before deformation.
【図３】筒状マンドレルの変形後の状態を示す図。FIG. 3 is a diagram showing the state of the cylindrical mandrel after deformation.
【図４】複合材のプリプレグの成形された後の状態を示
す図。FIG. 4 is a diagram showing the state of a composite prepreg after being molded.
【図５】複合材のプリプレグの繊維束の筒状マンドレル
の変形前の状態を示す図。FIG. 5 is a diagram showing a state before deformation of a cylindrical mandrel of a fiber bundle of prepreg of a composite material.
【図６】複合材のプリプレグの繊維束の筒状マンドレル
の変形後の状態を示す図。FIG. 6 is a diagram showing the state of the cylindrical mandrel of the composite material prepreg fiber bundle after deformation.
【図７】従来の複合材の成形方法の複合材のプリプレグ
を巻き付けた状態を示す図。FIG. 7 is a diagram showing a state in which prepreg of a composite material is wound in a conventional method of molding a composite material.
【図８】従来の複合材の成形方法の巻き付けられた複合
材のプリプレグの上にテープを巻き付けた状態を示す図
。FIG. 8 is a diagram illustrating a state in which a tape is wound around a wrapped prepreg of a composite material in a conventional method for molding a composite material.
【図９】従来の複合材の成形方法の他の例を示す図。FIG. 9 is a diagram showing another example of a conventional method for molding a composite material.
【図１０】従来の複合材の成形方法のさらに他の例を示
す図。FIG. 10 is a diagram showing still another example of a conventional method for molding a composite material.
【図１１】従来の複合材の成形方法により成形された中
空形状の複合材部品の斜視図。FIG. 11 is a perspective view of a hollow composite part molded by a conventional composite molding method.
１ 筒状マンドレル ２ 複合材のプリプレグ層 ３ 通気性シート ４ 真空バックフィルム 1. Cylindrical mandrel 2 Composite prepreg layer 3. Breathable sheet 4 Vacuum back film
Claims (1)
記憶合金で形成した筒状マンドレルに積層し、積層した
複合材のプリプレグを通気性シートで覆い、その通気性
シートの上に真空バックフィルムを被せ、筒状マンドレ
ルを複合材のプリプレグの樹脂の溶融温度より低い温度
で加熱して、筒状マンドレルを形状記憶合金に記憶され
た変位量だけ膨張させ、ついで、筒状マンドレルに積層
した複合材のプリプレグを加圧、加熱、硬化して成形す
ることを特徴とする複合材の成形方法。Claim 1: Composite prepregs are laminated on a cylindrical mandrel made of a shape memory alloy that changes with temperature, the laminated composite prepregs are covered with a breathable sheet, and a vacuum backing film is placed on the breathable sheet. The cylindrical mandrel is heated at a temperature lower than the melting temperature of the resin of the composite material prepreg to expand the cylindrical mandrel by the amount of displacement memorized by the shape memory alloy, and then the composite layer laminated on the cylindrical mandrel is A method for forming composite materials, which is characterized by pressurizing, heating, and curing prepreg material to form the material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP03141797A JP3121861B2 (en) | 1991-06-13 | 1991-06-13 | Composite material molding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP03141797A JP3121861B2 (en) | 1991-06-13 | 1991-06-13 | Composite material molding method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH04364929A true JPH04364929A (en) | 1992-12-17 |
| JP3121861B2 JP3121861B2 (en) | 2001-01-09 |
Family
ID=15300364
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP03141797A Expired - Fee Related JP3121861B2 (en) | 1991-06-13 | 1991-06-13 | Composite material molding method |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3121861B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014504218A (en) * | 2010-11-11 | 2014-02-20 | スピリット アエロシステムズ，アイエヌシー． | Method and system for forming an integral composite part using an SMP device |
| EP2977166A1 (en) * | 2014-07-25 | 2016-01-27 | The Boeing Company | An apparatus and method for a shape memory alloy mandrel |
| KR102244322B1 (en) * | 2020-09-01 | 2021-04-23 | 한경대학교 산학협력단 | Composite material manufacturing method |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9566746B2 (en) * | 2013-11-06 | 2017-02-14 | The Boeing Company | Methods and tools for forming contoured composite structures with shape memory alloy |
| KR102337118B1 (en) * | 2021-07-29 | 2021-12-09 | (유)한성산기 | Method for manufacturing carbon wear ring having improved wear resistance |
| KR102502735B1 (en) * | 2021-07-29 | 2023-02-24 | (유)한성산기 | Device for manufacturing carbon wear ring molded body |
-
1991
- 1991-06-13 JP JP03141797A patent/JP3121861B2/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014504218A (en) * | 2010-11-11 | 2014-02-20 | スピリット アエロシステムズ，アイエヌシー． | Method and system for forming an integral composite part using an SMP device |
| EP2977166A1 (en) * | 2014-07-25 | 2016-01-27 | The Boeing Company | An apparatus and method for a shape memory alloy mandrel |
| CN105299026A (en) * | 2014-07-25 | 2016-02-03 | 波音公司 | Apparatus and method for a shape memory alloy mandrel |
| JP2016030443A (en) * | 2014-07-25 | 2016-03-07 | ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ | Apparatus and method for shape memory alloy mandrel |
| US9919505B2 (en) | 2014-07-25 | 2018-03-20 | The Boeing Company | Apparatus and method for a shape memory alloy mandrel |
| KR102244322B1 (en) * | 2020-09-01 | 2021-04-23 | 한경대학교 산학협력단 | Composite material manufacturing method |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3121861B2 (en) | 2001-01-09 |
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