JP2002028944A - Method for molding composite material beam - Google Patents
Method for molding composite material beamInfo
- Publication number
- JP2002028944A JP2002028944A JP2000216560A JP2000216560A JP2002028944A JP 2002028944 A JP2002028944 A JP 2002028944A JP 2000216560 A JP2000216560 A JP 2000216560A JP 2000216560 A JP2000216560 A JP 2000216560A JP 2002028944 A JP2002028944 A JP 2002028944A
- Authority
- JP
- Japan
- Prior art keywords
- laminate
- composite
- forming
- composite material
- laminates
- 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
Landscapes
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は複合材ビームの成形
方法に関する。The present invention relates to a method for forming a composite beam.
【０００２】[0002]
【従来の技術】繊維強化複合材（プリプレグ）からなる
複合材ビームは軽量で高強度であるため、自動車、船
舶、航空機等の構造部材として広く使用されている。従
来、I型、J型、T型等の断面形状を有する複合材ビーム
が多用されている。2. Description of the Related Art Composite beams made of fiber-reinforced composite materials (prepregs) are widely used as structural members for automobiles, ships, aircraft, etc. because of their light weight and high strength. Conventionally, composite beams having a cross-sectional shape such as I-type, J-type, and T-type have been frequently used.
【０００３】図１はウェブとフランジを有する複合材I
型ビームの一例を示す斜視図である。通常、複合材I型
ビーム１を成形する際には２組（４型）の合わせ型を用
いるマッチドダイ成形法が用いられる。この方法では、
図２に示すように一対のコ字状積層体２に複合材からな
る楔形充填材4aを載置し、更に平板状積層体３を配置
し、２個のウェブ成形型5a及び２個のフランジ成形型5b
を用いて成形する。楔形充填材4aの充填量はコ字状積層
体２及び平板状積層体３により形成される楔形空間の空
間量より大きくする。そのため、フランジ成形型5bによ
り強制的にフランジを抑えて、フランジに凸部が形成さ
れてしまうことを防ぐ必要がある。従ってこの方法では
多数の成形型が必須であり高コスト化が避けられない。FIG. 1 shows a composite material I having a web and a flange.
It is a perspective view which shows an example of a mold beam. Usually, when forming the composite I-beam 1, a matched die forming method using two sets (four types) of mating dies is used. in this way,
As shown in FIG. 2, a wedge-shaped filler 4a made of a composite material is placed on a pair of U-shaped laminates 2, a flat laminate 3 is further disposed, and two web forming dies 5a and two flanges are provided. Mold 5b
Mold using. The filling amount of the wedge-shaped filler 4a is larger than the space amount of the wedge-shaped space formed by the U-shaped laminate 2 and the flat laminate 3. Therefore, it is necessary to forcibly suppress the flange by the flange forming die 5b to prevent the formation of a convex portion on the flange. Therefore, in this method, a large number of molds are indispensable, and an increase in cost cannot be avoided.
【０００４】[0004]
【発明が解決しようとする課題】本発明の目的は、成形
不良を抑制でき低コスト化が可能な複合材ビームの成形
方法を提供することである。SUMMARY OF THE INVENTION It is an object of the present invention to provide a method of forming a composite beam which can suppress molding defects and can reduce the cost.
【０００５】[0005]
【課題を解決するための手段】上記課題に鑑み鋭意研究
の結果、本発明者らは、複合材ビームを成形する際に上
記充填材の充填量を特定の値に設定することにより、成
形型の数を削減しても成形不良を抑制でき、成形コスト
を低減できることを発見し、本発明に想到した。Means for Solving the Problems In view of the above problems, as a result of intensive studies, the present inventors have set the filling amount of the filler to a specific value when forming the composite material beam, and It has been found that even if the number is reduced, molding defects can be suppressed and the molding cost can be reduced, and the present invention has been reached.
【０００６】すなわち、本発明の複合材ビームの成形方
法は、(a)成形型上に板厚Tを有する複合材積層体を敷い
て、ウェブ部及びフランジ部、並びにそれらの間に形成
された内側曲率半径Rを有するコーナー部を含む積層体
Ｉを成形する工程、(b)一対の積層体Ｉを組み合わせ、
それらのコーナー部に、板厚tと幅Cを有する複合材積層
体からなる充填材を載置し、その上に複合材からなる平
板状の積層体IIを配置する工程、及び(c)加熱・加圧に
より積層体Ｉ、充填材及び積層体IIを一体硬化する工程
を含み、積層体Ｉのコーナー部及び積層体IIにより形成
される楔形空間の面積Sは下記式： S＝(4−π)・(R＋T)2/2 により表され、充填材の側面積(t・C)が下記式： t・C＝S を満たすように板厚t及び幅Cを設定することを特徴とす
る。That is, the method of forming a composite beam according to the present invention comprises the steps of: (a) laying a composite laminate having a thickness T on a forming die, forming a web portion and a flange portion, and forming the web portion and the flange portion therebetween; Forming a laminate I including a corner having an inner radius of curvature R, (b) combining a pair of laminates I,
A step of placing a filler composed of a composite laminate having a thickness t and a width C on those corners, and disposing a flat laminate II composed of the composite thereon, and (c) heating. The method includes a step of integrally curing the laminate I, the filler, and the laminate II by pressing, and the area S of the corner portion of the laminate I and the wedge-shaped space formed by the laminate II is represented by the following formula: S = (4- π) · (R + T) is expressed by 2/2, the side area of the filler (t · C) satisfies the following formula: and sets the sheet thickness t and the width C so as to satisfy the t · C = S .
【０００７】本発明の複合材ビームの成形方法において
は、一体硬化する際に積層体IIの上に平板状成形板を載
置するのが好ましい。また、本発明の複合材ビームの成
形方法はI型の断面形状を有する複合材ビームの成形に
特に好ましく適用できる。In the method of molding a composite material beam according to the present invention, it is preferable to place a flat molded plate on the laminate II when integrally curing. The method for forming a composite beam of the present invention can be particularly preferably applied to the formation of a composite beam having an I-shaped cross section.
【０００８】[0008]
【発明の実施の形態】本発明の複合材ビームの成形方法
は、(a)成形型上に複合材積層体を敷いて、ウェブ部及
びフランジ部、並びにそれらの間に形成されたコーナー
部を含む積層体Ｉを成形する工程、(b)一対の積層体Ｉ
を組み合わせ、それらのコーナー部に充填材を載置し、
その上に平板状の積層体IIを配置する工程、及び(c)加
熱・加圧により積層体Ｉ、充填材及び積層体IIを一体硬
化する工程を含む。BEST MODE FOR CARRYING OUT THE INVENTION The method for forming a composite material beam according to the present invention comprises the steps of (a) laying a composite material laminate on a forming die and forming a web portion, a flange portion, and a corner portion formed therebetween. Forming a laminate I including: (b) a pair of laminates I
And put the filler in those corners,
The method includes a step of disposing a flat laminate II thereon, and a step (c) of integrally curing the laminate I, the filler and the laminate II by heating and pressing.
【０００９】上記積層体Ｉ、充填材及び積層体IIは繊維
強化複合材からなる。本発明では、炭素繊維、ガラス繊
維、アラミド繊維等の強化繊維に熱硬化性樹脂（エポキ
シ樹脂、ビスマレイミド樹脂、フェノール樹脂等）又は
熱可塑性樹脂（PEEK、ナイロン６、ナイロン６６、ポリ
エチレンテレフタレート等）を含浸させてなる繊維強化
複合材が使用可能である。熱硬化性樹脂としてはエポキ
シ樹脂が好ましく、熱可塑性樹脂としてはナイロンが好
ましい。強化繊維と熱硬化性樹脂又は熱可塑性樹脂との
配合割合は任意に調整しうる。積層体Ｉ、充填材及び積
層体IIを形成する繊維強化複合材は同じでも異なってい
てもよいが、同じであるのが好ましい。The laminate I, the filler and the laminate II are made of a fiber-reinforced composite material. In the present invention, a thermosetting resin (epoxy resin, bismaleimide resin, phenol resin, etc.) or a thermoplastic resin (PEEK, nylon 6, nylon 66, polyethylene terephthalate, etc.) is used for reinforcing fibers such as carbon fiber, glass fiber, and aramid fiber. Can be used. As the thermosetting resin, an epoxy resin is preferable, and as the thermoplastic resin, nylon is preferable. The mixing ratio of the reinforcing fiber and the thermosetting resin or the thermoplastic resin can be arbitrarily adjusted. The laminate I, filler and fiber reinforced composite forming the laminate II can be the same or different, but are preferably the same.
【００１０】本発明で用いる複合材積層体の積層構造
（各複合材の繊維方向）は特に限定されず、例えば(±4
5°／０°／０°／０°／0-90°)等に配列してよい。ま
た積層数も任意に決定すればよい。The laminated structure (fiber direction of each composite material) of the composite laminate used in the present invention is not particularly limited.
5 ° / 0 ° / 0 ° / 0 ° / 0-90 °) or the like. The number of layers may be arbitrarily determined.
【００１１】成形型としては、例えば鉄、アルミ、繊維
強化複合材等からなるものが使用できる。As the molding die, for example, a molding die made of iron, aluminum, fiber-reinforced composite material or the like can be used.
【００１２】積層体Ｉ、充填材及び積層体IIを一体硬化
する際の加熱・加圧はオートクレーブ等を用いて行うの
が好ましい。加熱温度は120〜250℃とするのが好まし
い。加熱温度が250℃より高いと樹脂が劣化し、120℃よ
り低いと樹脂が未反応となるため好ましくない。また加
圧は６〜７kg/cm2とするのが好ましい。７kg/cm2より大
きいと樹脂不足となり、６kg/cm2より小さいとボイドが
発生しやすくなるため好ましくない。加熱・加圧は積層
体と成形型をバギングフィルム、真空バッグ等で覆って
行うことができる。The heating and pressurization when the laminate I, the filler and the laminate II are integrally cured are preferably performed using an autoclave or the like. The heating temperature is preferably from 120 to 250 ° C. If the heating temperature is higher than 250 ° C., the resin deteriorates, and if the heating temperature is lower than 120 ° C., the resin does not react, which is not preferable. The pressure is preferably set to 6 to 7 kg / cm 2 . If it is larger than 7 kg / cm 2 , the resin will be insufficient, and if it is smaller than 6 kg / cm 2 , voids are likely to be generated, which is not preferable. Heating and pressing can be performed by covering the laminate and the mold with a bagging film, a vacuum bag, or the like.
【００１３】本発明はI型、J型、T型等の断面形状を有
する複合材ビームの成形に好ましく適用できる。以下、
本発明により図１に示す複合材I型ビーム１を成形する
場合について図面を用いて詳細に説明するが、本発明は
それらにより限定されるものではない。The present invention can be preferably applied to the formation of a composite beam having a cross-sectional shape such as an I-shape, a J-shape or a T-shape. Less than,
The case of forming the composite I-beam 1 shown in FIG. 1 according to the present invention will be described in detail with reference to the drawings, but the present invention is not limited thereto.
【００１４】図３に示すように、まず成形型5cに複合材
積層体を敷いて、ウェブ部及びフランジ部、並びにそれ
らの間に形成されたコーナー部を含むコ字状積層体２を
得る。複合材積層体は所定の板厚Tを有する。また、コ
ーナー部は所定の内側曲率半径Rを有する。As shown in FIG. 3, first, a composite laminate is laid on a mold 5c to obtain a U-shaped laminate 2 including a web portion, a flange portion, and a corner portion formed therebetween. The composite laminate has a predetermined plate thickness T. The corner has a predetermined inner radius of curvature R.
【００１５】上記のように得られた一対のコ字状積層体
２をウェブ部で組み合わせ、それらのコーナー部に充填
材4bを載置し、更にその上に平板状積層体３を配置す
る。続いてこれらを一体硬化し、I型ビームを得る。充
填材4bは、図４(a)に示す板厚tと幅Cを有する複合材積
層体７を用いて、図４(b)のように丸めて作製してよ
い。The pair of U-shaped laminates 2 obtained as described above are combined at the web portion, the filler 4b is placed at the corners, and the flat laminate 3 is further disposed thereon. Subsequently, these are integrally cured to obtain an I-shaped beam. The filler 4b may be produced by using a composite laminate 7 having a thickness t and a width C shown in FIG.
【００１６】コ字状積層体２のコーナー部の外側曲率半
径は実質的に(R＋T)として良いので、該コーナー部及び
平板状積層体３により形成される楔形空間の面積Sは下
記式： S＝2(R＋T)2−2[π/4(R＋T)2] ＝(4−π)・(R＋T)2/2 により表される。本発明では上記充填材の側面積(t・C)
を上記楔形空間の面積Sに等しくなるように設定する。
即ち、下記式： t・C＝S を満たすように板厚t及び幅Cを設定する。例えば、成形
型5cに厚さ0.2mmの複合材10枚を積層して板厚Tが２mm、
内側曲率半径Rが３mmのコ字状積層体２を成形し、この
コ字状積層体２のコーナー部に板厚tが0.2mmの複合材１
枚からなる充填材4bを載置し、更に平板状積層体３を配
置して一体硬化する場合には、上記楔形空間の面積はS
＝(4−π)・(3＋2)2/2＝10.73［mm2］であるので、充填
材4bをなす複合材の幅Cは、C＝S/t＝10.73/0.2＝53.65
［mm］に設定すればよい。これによりフランジ部に凸部
が生じず、フランジ成形型が実質不要となる。Since the outer radius of curvature of the corner of the U-shaped laminate 2 may be substantially (R + T), the area S of the wedge-shaped space formed by the corner and the flat laminate 3 is represented by the following formula: S = 2 (R + T) 2 -2 [π / 4 (R + T) 2] = (4-π) · (R + T) is expressed by 2/2. In the present invention, the side area of the filler (tC)
Is set to be equal to the area S of the wedge-shaped space.
That is, the plate thickness t and the width C are set so as to satisfy the following expression: t · C = S. For example, ten composite materials each having a thickness of 0.2 mm are laminated on a mold 5c, and the thickness T is 2 mm.
A U-shaped laminate 2 having an inner radius of curvature R of 3 mm is formed, and a composite material 1 having a thickness t of 0.2 mm is formed at a corner of the U-shaped laminate 2.
When the filler 4b composed of a plurality of sheets is placed, and the plate-shaped laminate 3 is further arranged and cured integrally, the area of the wedge-shaped space is S
= (4−π) · (3 + 2) 2 /2=10.73 [mm 2 ], so the width C of the composite material forming the filler 4b is C = S / t = 10.73 / 0.2 = 53.65
It may be set to [mm]. As a result, no convex portion is formed on the flange portion, and a flange forming die is substantially unnecessary.
【００１７】一体硬化する際には平板状積層体３の上に
薄い平板状成形板６（プレッシャープレート）を載置す
るのが好ましい。平板状成形板は鉄、アルミ、繊維強化
複合材等の材質からなるのが好ましい。平板状成形板の
厚みは0.5〜1.5mmであるのが好ましい。このように本発
明で用いる平板状成形板は非常に薄く軽量であるので、
形状になじみやすく、取り扱いが容易である。When integrally hardening, it is preferable to place a thin flat plate 6 (pressure plate) on the flat laminate 3. The flat plate is preferably made of a material such as iron, aluminum, or a fiber-reinforced composite material. The thickness of the flat formed plate is preferably 0.5 to 1.5 mm. As described above, since the flat molded plate used in the present invention is very thin and lightweight,
Easy to adapt to shape and easy to handle.
【００１８】以上の通り、図面を参照して本発明を説明
したが、本発明はそれらに限定されず本発明の趣旨を変
更しない限り種々の変更を加えることができる。As described above, the present invention has been described with reference to the drawings. However, the present invention is not limited thereto, and various changes can be made without changing the gist of the present invention.
【００１９】[0019]
【発明の効果】以上詳述したように、本発明の複合材ビ
ームの成形方法によれば、成形不良のない複合材ビーム
を低コストで成形できる。As described above in detail, according to the method for forming a composite beam of the present invention, a composite beam free from molding defects can be formed at low cost.
【図１】 複合材I型ビームの一例を示す斜視図であ
る。FIG. 1 is a perspective view showing an example of a composite I-beam.
【図２】 従来のマッチドダイ成形法により図１に示す
複合材I型ビームを成形する様子を示す正面図である。FIG. 2 is a front view showing how the composite I-beam shown in FIG. 1 is formed by a conventional matched die forming method.
【図３】 本発明の成形方法により図１に示す複合材I
型ビームを成形する様子を示す正面図である。FIG. 3 shows a composite material I shown in FIG. 1 by the molding method of the present invention.
It is a front view which shows a mode that a shape | mold beam is shape | molded.
【図４】 本発明で用いる充填材を作製する様子を示す
斜視図である。FIG. 4 is a perspective view showing a state of producing a filler used in the present invention.
１・・・複合材I型ビーム ２・・・コ字状積層体 ３・・・平板状積層体 4a、4b・・・充填材 5a、5b、5c・・・成形型 ６・・・平板状成形板 ７・・・複合材積層体 DESCRIPTION OF SYMBOLS 1 ... Composite I-beam 2 ... U-shaped laminated body 3 ... Flat laminated body 4a, 4b ... Filler 5a, 5b, 5c ... Mold 6: Flat plate Molded plate 7: Composite laminate
───────────────────────────────────────────────────── フロントページの続き (72)発明者 平山 明 埼玉県和光市中央一丁目４番１号 株式会 社本田技術研究所内 Ｆターム(参考） 4F204 AA36 AD16 AH81 FA01 FB01 FB12 FF05 FG02 FN11 ──────────────────────────────────────────────────続 き Continued on the front page (72) Inventor Akira Hirayama 1-4-1 Chuo, Wako-shi, Saitama F-term in Honda R & D Co., Ltd. (Reference) 4F204 AA36 AD16 AH81 FA01 FB01 FB12 FF05 FG02 FN11
Claims (3)
体を敷いて、ウェブ部及びフランジ部、並びにそれらの
間に形成された内側曲率半径Rを有するコーナー部を含
む積層体Ｉを成形する工程、(b)一対の前記積層体Ｉを
組み合わせ、それらの前記コーナー部に、板厚tと幅Cを
有する複合材積層体からなる充填材を載置し、その上に
複合材からなる平板状の積層体IIを配置する工程、及び
(c)加熱・加圧により前記積層体Ｉ、充填材及び積層体I
Iを一体硬化する工程を含む複合材ビームの成形方法に
おいて、 前記積層体Ｉのコーナー部及び前記積層体IIにより形成
される楔形空間の面積Sは下記式： S＝(4−π)・(R＋T)2/2 により表され、前記充填材の側面積(t・C)が下記式： t・C＝S を満たすように前記板厚t及び幅Cを設定することを特徴
とする複合材ビームの成形方法。1. A laminating method comprising the steps of: (a) laying a composite laminate having a plate thickness T on a molding die, and including a web portion, a flange portion, and a corner portion having an inner radius of curvature R formed therebetween. Forming a body I, (b) combining the pair of laminates I, placing a filler composed of a composite laminate having a thickness t and a width C on the corners thereof, and Arranging a flat laminate II made of a composite material, and
(c) The laminate I, filler and laminate I by heating and pressing
In the method of forming a composite beam including a step of integrally curing I, an area S of a corner portion of the laminate I and a wedge-shaped space formed by the laminate II is represented by the following formula: S = (4-π) · ( R + T) is expressed by 2/2, the lateral area of the filler (t · C) satisfies the following formula: t · C = composite and sets the thickness t and the width C so as to satisfy the S Beam forming method.
法において、前記一体硬化する際に前記積層体IIの上に
平板状成形板を載置することを特徴とする複合材ビーム
の成形方法。2. The method of forming a composite beam according to claim 1, wherein a flat plate is placed on the laminate II during the integral curing. Method.
成形方法において、前記積層体Ｉはコ字状であり、前記
複合材ビームはI型の断面形状を有することを特徴とす
る複合材ビームの成形方法。3. The method of forming a composite beam according to claim 1, wherein the laminate I has a U-shape, and the composite beam has an I-shaped cross-sectional shape. Method of forming beam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000216560A JP4459401B2 (en) | 2000-07-17 | 2000-07-17 | Composite beam forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000216560A JP4459401B2 (en) | 2000-07-17 | 2000-07-17 | Composite beam forming method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2002028944A true JP2002028944A (en) | 2002-01-29 |
| JP4459401B2 JP4459401B2 (en) | 2010-04-28 |
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| JP2000216560A Expired - Fee Related JP4459401B2 (en) | 2000-07-17 | 2000-07-17 | Composite beam forming method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004330785A (en) * | 2003-04-30 | 2004-11-25 | Airbus Deutschland Gmbh | Method and apparatus for producing fiber pre-molded article from fiber half-finished good |
| JP2006104649A (en) * | 2004-09-10 | 2006-04-20 | Toray Ind Inc | Rod-shaped preform and method for producing the same |
| JP2007001299A (en) * | 2005-05-23 | 2007-01-11 | Toray Ind Inc | Rod-shaped preform for filling gap, its manufacturing method, and manufacturing device |
| WO2014135798A1 (en) * | 2013-03-07 | 2014-09-12 | Snecma | Fibrous insert intended to fill an empty space in a fibrous preform for the production of a turbomachine part made from composite material |
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| JP2018177088A (en) * | 2017-04-18 | 2018-11-15 | サノヤス造船株式会社 | Structure for ship and production method of the same |
-
2000
- 2000-07-17 JP JP2000216560A patent/JP4459401B2/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004330785A (en) * | 2003-04-30 | 2004-11-25 | Airbus Deutschland Gmbh | Method and apparatus for producing fiber pre-molded article from fiber half-finished good |
| JP2006104649A (en) * | 2004-09-10 | 2006-04-20 | Toray Ind Inc | Rod-shaped preform and method for producing the same |
| JP2007001299A (en) * | 2005-05-23 | 2007-01-11 | Toray Ind Inc | Rod-shaped preform for filling gap, its manufacturing method, and manufacturing device |
| WO2014135798A1 (en) * | 2013-03-07 | 2014-09-12 | Snecma | Fibrous insert intended to fill an empty space in a fibrous preform for the production of a turbomachine part made from composite material |
| JP2018177088A (en) * | 2017-04-18 | 2018-11-15 | サノヤス造船株式会社 | Structure for ship and production method of the same |
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
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| Publication number | Publication date |
|---|---|
| JP4459401B2 (en) | 2010-04-28 |
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