JPH0224720B2 - - Google Patents
Info
- Publication number
- JPH0224720B2 JPH0224720B2 JP57062060A JP6206082A JPH0224720B2 JP H0224720 B2 JPH0224720 B2 JP H0224720B2 JP 57062060 A JP57062060 A JP 57062060A JP 6206082 A JP6206082 A JP 6206082A JP H0224720 B2 JPH0224720 B2 JP H0224720B2
- Authority
- JP
- Japan
- Prior art keywords
- cylindrical body
- resin
- annular member
- hollow body
- cylindrical
- 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.)
- Expired
Links
- 239000002657 fibrous material Substances 0.000 claims description 5
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims 1
- 229920005989 resin Polymers 0.000 description 14
- 239000011347 resin Substances 0.000 description 14
- 239000002131 composite material Substances 0.000 description 9
- 238000000034 method Methods 0.000 description 8
- 239000004744 fabric Substances 0.000 description 4
- 238000009730 filament winding Methods 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 2
- 239000004677 Nylon Substances 0.000 description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 229920001778 nylon Polymers 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 Teflon® Polymers 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000002648 laminated material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000006187 pill Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 239000002990 reinforced plastic Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Landscapes
- Laminated Bodies (AREA)
Description
【発明の詳細な説明】
本発明は、高い曲げ荷重や圧縮荷重に耐えられ
るようにした複合材（例えば、炭素繊維とエポキ
シプリプレグ）製の軽量中空体に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to lightweight hollow bodies made of composite materials (eg, carbon fiber and epoxy prepreg) that are adapted to withstand high bending and compressive loads.
このような中空体は、例えば衛星打上げ用ロケ
ツトにおいて３段ロケツトモータと衛星とを結合
している衛星分離部に用いられているが、ロケツ
トのペイロードが同一でも、より重い衛星の打上
げを可能にするため、上記中空体の強度を十分に
保ちながら、できるだけその軽量化をはかること
が求められている。 Such a hollow body is used, for example, in the satellite separation part that connects the three-stage rocket motor and the satellite in a satellite launch rocket, but even if the payload of the rocket is the same, it is possible to launch a heavier satellite. Therefore, it is required to reduce the weight of the hollow body as much as possible while maintaining sufficient strength.
ところで、複合材製の中空体は全金属製（例え
ばアルミニウム合金製）のものに比べて軽く作れ
るが、複合材製の外板を金属製のフレームで接続
すると全複合材製の場合に比べて重くなるという
問題点があり、また全複合材製の中空体でもその
壁部をコルゲート状に成形したのでは、端部を他
部品と結合する際の端末処理に困難をきたすとい
う問題点がある。 By the way, a hollow body made of composite material can be made lighter than one made entirely of metal (for example, aluminum alloy), but if a composite outer panel is connected with a metal frame, it will be lighter than one made entirely of composite material. There is a problem that it becomes heavy, and even if the hollow body is made entirely of composite materials, if the wall is formed into a corrugated shape, there is a problem that it is difficult to process the end when joining the end with other parts. .
さらに、全複合材製の中空体の壁部に補強用の
ストリンガを２次接着により取付ける場合は、剪
断強度が十分でなく、接着剤の重量がかさむとい
う問題点もある。 Furthermore, when a reinforcing stringer is attached to the wall of a hollow body made entirely of composite material by secondary bonding, there are also problems in that the shear strength is insufficient and the weight of the adhesive increases.
本発明は、上述の諸問題を解決して、十分な強
度を得ながら軽量化をはかれるようにした高荷重
用軽量中空体を提供することを目的とする。 SUMMARY OF THE INVENTION An object of the present invention is to solve the above-mentioned problems and provide a lightweight hollow body for heavy loads that can achieve sufficient strength while reducing weight.
このため本発明の高荷重用軽量中空体は、筒状
本体と、その側壁に一体成形により設けられた補
助用ストリンガとをそなえるとともに、上記筒状
本体の端部周面に沿つて接着された環状部材をそ
なえ、上記環状部材が一方向に大きい強度を有す
る長繊維材を上記筒状部材の周方向のみに配設し
て成形されていることを特徴としている。 For this reason, the lightweight hollow body for high loads of the present invention includes a cylindrical body and an auxiliary stringer integrally molded on the side wall of the cylindrical body. The cylindrical member is characterized in that the annular member is formed by disposing a long fiber material having high strength in one direction only in the circumferential direction of the cylindrical member.
以下、図面により本発明の一実施例としての高
荷重用軽量中空体について説明すると、第１図は
その斜視図、第２図は第１図の―矢視断面
図、第３図はその製作工程図である。 Hereinafter, a lightweight hollow body for heavy loads as an embodiment of the present invention will be explained with reference to the drawings. Fig. 1 is a perspective view thereof, Fig. 2 is a sectional view taken in the direction of - arrow in Fig. 1, and Fig. 3 is its fabrication. It is a process diagram.
第１，２図に示すように、複合積層材としての
強化プラスチツクで作られた筒状本体１はその端
部において上部フランジ２および下部フランジ３
を有し、また筒状本体１の内側壁には、これと同
じ複合積層材から成る多数の補強用ストリンガ４
が一体成形により列設されている。 As shown in FIGS. 1 and 2, a cylindrical body 1 made of reinforced plastic as a composite laminate has an upper flange 2 and a lower flange 3 at its ends.
The inner wall of the cylindrical body 1 has a large number of reinforcing stringers 4 made of the same composite laminated material.
are arranged in a row by integral molding.
さらに、この筒状本体１の上部フランジ２に
は、フイラメントワインデイング法で炭素繊維の
ごとき一方向に大きい強度を有する長繊維材を筒
状本体１の周方向のみに配設して成形された環状
部材５が、常温接着剤により接着して取付けられ
ている。なお、上記長繊維材は、ロービング
（roving）処理などにより生成される。 Further, the upper flange 2 of the cylindrical body 1 is formed by disposing a long fiber material such as carbon fiber having high strength in one direction only in the circumferential direction of the cylindrical body 1 using a filament winding method. An annular member 5 is attached by adhesively using a room-temperature adhesive. Note that the long fiber material is produced by a roving process or the like.
次に、本発明の高荷重軽量中空体の製作工程に
つき、第３図を参照して説明する。 Next, the manufacturing process of the high-load, lightweight hollow body of the present invention will be explained with reference to FIG.
（工程１）
ストリンガ用モールドは、工程７の完了後に離
脱するので、離型性のよいテフロンを使用する。
またマンドレルおよびシリンダは金属製のものを
使用する。(Step 1) Since the stringer mold will be removed after Step 7 is completed, Teflon, which has good mold releasability, is used.
Also, the mandrel and cylinder are made of metal.
（工程２）
マンドレルおよびシリンダとカーボンFRPと
の離型をよくするために、マンドレルおよびシリ
ンダにシリコン塗布、シリコン塗布焼付け等の離
型処理を行なう。(Step 2) In order to improve the release of the carbon FRP from the mandrel and cylinder, the mandrel and cylinder are subjected to mold release treatment such as silicon coating and silicon coating baking.
（工程３）
工程１で準備されたモールドおよびシリンダ
に、それぞれエポキシプリプレグを積層させレジ
ンの吸い取りを行なつて、ストリンガおよび筒状
本体の成形を行なう。(Step 3) Epoxy prepreg is laminated on the mold and cylinder prepared in Step 1, and the resin is sucked off to form a stringer and a cylindrical body.
特に、筒状本体のフランジ部分については積層
枚数が多く（全積層枚数は110ply）、一度にレジ
ンを吸い取ることは困難なため、二度にわけてレ
ジンの吸い取りを行なう。 In particular, the flange portion of the cylindrical body has a large number of layers (the total number of layers is 110 plies), and it is difficult to vacuum the resin at once, so the resin is vacuumed in two parts.
一般に180℃硬化タイプのエポキシ樹脂では120
℃×30分程度でよい。このレジン吸い取りは、各
積層体を最終的硬化のための組付け前に成形品寸
度（厚さ）近くにするために行なわれるもので、
いわゆるプリプレグ中の余剰樹脂を吸い取ること
（脱レジン）である。 Generally, 120 for 180℃ curing type epoxy resin.
℃ x 30 minutes is sufficient. This resin blotting is done to make each laminate close to the molded product size (thickness) before assembly for final curing.
This is the so-called removal of resin from the prepreg (resin removal).
このレジン吸い取りを行なうと、つぎの利点が
ある。 This resin blotting has the following advantages.
(1) 組付け時のマツチイングが容易になる。(1) Matching during assembly becomes easier.
(2) 硬化後の寸法精度が向上する。(2) Improved dimensional accuracy after curing.
(3) 硬化時のブリーダクロスが不要になる。(3) No need for a bleeder cloth during curing.
なお、環状部材についてはフイラメントワイン
デイング法のため、レジンの吸い取りは行なわれ
ない。 Note that the resin is not sucked off for the annular member because of the filament winding method.
工程３における筒状本体についてのバツギイン
グの説明図における符号ａはシリンダ壁を示し、
ｂ，ｃおよびｄはそれぞれバツギイング材として
のバキユームフイルム（ナイロン）、ブリーダク
ロス（ガラスクロス）およびピルプライ（ナイロ
ンクロス）を示し、ｅはプリプレグ、ｆはシール
を示す。 The symbol a in the explanatory diagram of butting the cylindrical body in step 3 indicates the cylinder wall,
b, c, and d indicate vacuum film (nylon), bleeder cloth (glass cloth), and pill ply (nylon cloth) as binding materials, e indicates prepreg, and f indicates seal.
（工程４）
筒状本体フランジ部分については、第一次積層
してから、レジンの吸い取りを行なつたのち、そ
の上に第二次積層を行なう。(Step 4) For the flange portion of the cylindrical main body, after the first lamination is performed, the resin is blotted, and then the second lamination is performed thereon.
第二次のレジンの吸い取りは、工程６の硬化時
にレジンの吸い取りができるので、ここでのレジ
ンの吸い取りは不要である。 The second resin blotting can be done during curing in step 6, so the resin blotting here is not necessary.
（工程５）
本体にストリンガを組付ける。バツギイング工
程３と同じ方法で行なう。ただし、レジンの吸い
取りは工程４の第二次積層した部分だけとする。(Step 5) Assemble the stringer to the main body. It is carried out in the same manner as Butging Step 3. However, the resin should be blotted only from the second laminated area in step 4.
（工程６）
硬化（１例として180℃×２時間、90psi）はプ
リプレグレジンの硬化特性に合わせて温度および
時間をセツト（１例として180℃×２時間）する。
圧力はオートクレーブなどを用いて3.5〜７Kg／
cm2ゲージ圧を加えると繊維含有率の多いボイドの
少ない成形品が得られる。(Step 6) For curing (for example, 180°C x 2 hours, 90psi), the temperature and time are set (for example, 180°C x 2 hours) according to the curing characteristics of the prepreg resin.
The pressure is 3.5-7Kg/using an autoclave etc.
By applying cm 2 gauge pressure, molded products with high fiber content and few voids can be obtained.
（工程７） ストリンガ用のモールドを離脱する。(Step 7) Remove the stringer mold.
（工程８）
工程９で接着される、フイラメントワインデイ
ング法で成形した環状部材と、筒状本体のフラン
ジ部分とを加工する。(Step 8) Process the annular member formed by the filament winding method and the flange portion of the cylindrical body to be bonded in Step 9.
（工程９）
プリプレグのレジンと親和性（Affinity）のよ
い常温型接着剤を使用して、筒状本体の端部周面
に沿い環状部材を接着する。(Step 9) Using a room-temperature adhesive that has good affinity with the prepreg resin, adhere the annular member along the circumferential surface of the end of the cylindrical body.
なお、筒状本体の断面形状は、円形のほか角形
など、適宜の中空形状とすることができる。 Note that the cross-sectional shape of the cylindrical body may be circular, square, or any other suitable hollow shape.
このようにして製作された本発明の中空体は、
複合材によるセミモノコツク構造となり、軽量
で、しかも高強度が得られるのであつて、特にそ
の筒状本体の端部においては、フイラメントワイ
ンデイング法で一方向に大きい強度を有する長繊
維材を上記筒状本体の周方向のみに配設し成形し
た環状部材を接着することにより、軽量化をはか
りながら、高い強度と剛性とが得られるのであ
る。 The hollow body of the present invention manufactured in this way is
It has a semi-monocot structure made of composite material, which is lightweight and has high strength.Especially at the end of the cylindrical body, a long fiber material having high strength in one direction is used by filament winding method to form the cylindrical shape. By bonding the molded annular members arranged only in the circumferential direction of the main body, high strength and rigidity can be obtained while reducing the weight.
第１，２図は本発明の一実施例としての高荷重
用軽量中空体を示すもので、第１図はその斜視
図、第２図は第１図の―矢視断面図、第３図
はその製作工程図である。
１…筒状本体、２…上部フランジ、３…下部フ
ランジ、４…ストリンガ、５…環状部材。
Figures 1 and 2 show a lightweight hollow body for heavy loads as an embodiment of the present invention, with Figure 1 being a perspective view thereof, Figure 2 being a cross-sectional view taken along the - arrow in Figure 1, and Figure 3 is a diagram of its manufacturing process. DESCRIPTION OF SYMBOLS 1... Cylindrical main body, 2... Upper flange, 3... Lower flange, 4... Stringer, 5... Annular member.
Claims (1)
られた補強用ストリンガとをそなえるとともに、
上記筒状本体の端部周面に沿つて接着された環状
部材をそなえ、上記環状部材が一方向に大きい強
度を有する長繊維材を上記筒状本体の周方向のみ
に配設して成形されていることを特徴とする、高
荷重用軽量中空体。1. It has a cylindrical body and a reinforcing stringer integrally formed on the side wall thereof, and
The cylindrical body has an annular member glued along the peripheral surface of the end thereof, and the annular member is formed by arranging a long fiber material having high strength in one direction only in the circumferential direction of the cylindrical body. A lightweight hollow body for heavy loads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57062060A JPS58179637A (en) | 1982-04-14 | 1982-04-14 | Light hollow body for high load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57062060A JPS58179637A (en) | 1982-04-14 | 1982-04-14 | Light hollow body for high load |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58179637A JPS58179637A (en) | 1983-10-20 |
| JPH0224720B2 true JPH0224720B2 (en) | 1990-05-30 |
Family
ID=13189203
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57062060A Granted JPS58179637A (en) | 1982-04-14 | 1982-04-14 | Light hollow body for high load |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58179637A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7527222B2 (en) * | 2004-04-06 | 2009-05-05 | The Boeing Company | Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections |
-
1982
- 1982-04-14 JP JP57062060A patent/JPS58179637A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS58179637A (en) | 1983-10-20 |
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