JPH0455859B2 - - Google Patents
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- Publication number
- JPH0455859B2 JPH0455859B2 JP9170488A JP9170488A JPH0455859B2 JP H0455859 B2 JPH0455859 B2 JP H0455859B2 JP 9170488 A JP9170488 A JP 9170488A JP 9170488 A JP9170488 A JP 9170488A JP H0455859 B2 JPH0455859 B2 JP H0455859B2
- Authority
- JP
- Japan
- Prior art keywords
- fastener
- joint
- hole
- laminated
- parts
- 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 - Lifetime
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- Laminated Bodies (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、繊維強化プラスチクスを積層した複
合材製部品の、フアスナ継手構造に関する。
〔従来の技術〕
従来の複合材製部品のフアスナ継手構造は、第
９図に示されるように、プリプレグを積層して硬
化させた板等の母材１に機械的に孔をあけ、継手
金具２等をフアスナ３で締結する構造であつた。
この継手部は、フアスナ３が分担する面圧荷重及
び全体的に負荷される引張又は圧縮荷重を同時に
受け、孔部の応力集中により、継手部以外の一般
部に比較し大幅に強度が低下する。
そこで従来は、継手部強度要求を満足させるた
め、全体に強度余裕をもたせるか、あるいは部分
的に補強するかにより、重量を費やしていた。
〔発明が解決しようとする課題〕
複合材製の構造にそのまま機械的に孔をあけフ
アスナで締結する、従来のフアスナ継手構造にお
いては、次のような解決すべき課題があつた。
(ア) フアスナが分担する面圧荷重及び全体的に負
荷される引張又は圧縮荷重を同時に受ける。
(イ) フアスナ孔部に応力集中がある。
(ウ) 上記(ア)、(イ)によりフアスナ継手部は、継手部
以外の一般部に比し、強度低下が大きい。
この発明は、従来のものが持つ上記のような欠
点を極力小さくし、フアスナ継手強度を画期的に
向上させる構造様式を提案することを目的とす
る。
〔課題を解決するための手段〕
前記目的を達成するために、この発明は次のよ
うな手段を用いる。
(1) 繊維強化プラスチツクを積層した複合材のフ
アスナ継手において、フアスナ継手部またはフ
アスナ孔端部の材料が他の部分の材料よりも伸
びが大きく剛性が低いことを特徴とする複合材
のフアスナ継手。
(2) 繊維強化プラスチクスを積層した複合材のフ
アスナ継手において、フアスナ継手部またはフ
アスナ孔端部の繊維の方法が他の部分の繊維の
方向と異なることを特徴とする複合材のフアス
ナ継手。
(3) 繊維強化プラスチクスを積層した複合材のフ
アスナ継手において、フアスナ継手部またはフ
アスナ孔端部の積層数が他の部分の積層数より
も多いことを特徴とする複合材のフアナス継
手。
〔作用〕
ア フアスナ継手部の剛性を局部的に下げること
により、全体の引張又は圧縮荷重は、剛性の高
いフアスナ孔のない部位に殆んど流れてしま
い、フアスナ孔部はフアスナの分担する面圧荷
重が加わる。このように面圧荷重と全体の引張
又は圧縮荷重がフアスナ孔部では分離されるこ
とになり、これらの荷重の相互影響と応力集中
による強度低下がなくなり、大幅なフアスナ継
手強度の向上を達成できる。
イ フアスナ孔端部の剛性を局部的に下げ破壊時
の伸びを増すことにより、孔端の応力集中が緩
和されフアスナ継手強度の向上を達成できる。
〔実施例〕
本発明の一実施例を第１図および第２図により
説明する。第１図は平面図、第２図は第１図の
−断面図である。
これらの図において、１は繊維強化プラスチク
スをａ、ｂ、ｃ……のように積層した複合材より
成る母材、４はフアスナ孔である。母材１の積層
ａ、ｂ、ｃ……の繊維の方向は、たとえば、
〔45／０／−45／02／90／０／−45／０／45／
02／90／０〕sとなつている。ただし、添字ｓは鏡
面対称に積層することを示し、添字２は２枚積層
することを示す（以後も同様）。
本実施例では0°層（ｂ、ｄ、ｅ、ｇ、ｉ、ｋ、
ｌ、ｎ）のフアスナ継手部（図中Ａで示される部
分）の材料として、他の部分（外側の部分）の材
料よりも伸びが大きく剛性が低い材料が用いられ
る。たとえば、外側の部分には炭素繊維複合材
（CFRP）を、フアスナ継手部Ａにはガラス繊維
複合材（GFRP）、アラミド繊維複合材（AFRP）
等を用いる。Ａ部分の幅はフアスナ孔径の５〜６
倍が望ましい。
本実施例においては、フアスナ継手部の剛性が
低くなつているので、一様荷重とフアスナにより
伝達される面圧荷重の分担する領域を分離するこ
とができる。すなわち、面圧荷重は剛性の高い領
域に剪断で移つていき、フアスナ孔部は一様荷重
を分担することなく面圧荷重のみ分担すればよい
ことになつて、応力集中の高い孔部の強度が向上
する。
次に本発明の第２実施例を第３図および第４図
により説明する。第３図は平面図、第４図は第３
図の−断面図である。
これらの図においても、１は繊維強化プラスチ
クスをａ、ｂ、ｃ……と積層した複合材より成る
母材、４はフアスナ孔である。
本実施例ではフアスナ孔端部（図中Ｂで示され
る部分）の材料として、他の部分の材料よりも伸
びが大きく剛性が低い材料が用いられる。
本実施例においては、フアスナ孔端部の剛性が
低いので、孔端の応力集中が緩和され、破壊時の
クラツクの方向が変わるため、強度が向上する。
次に本発明の第３の実施例を第５図および第６
図により説明する。第５図は平面図、第６図は第
５図の−断面図である。これらの図において
も、１は繊維強化プラスチクスをａ、ｂ、ｃ……
と積層した複合材より成る母材、４はフアスナ孔
である。
本実施例では一部の積層のフアスナ継手部（図
中Ａで示される部分）の繊維の方向が他の部分
（外側の部分）の繊維の方向と異なつている。
たとえば、外側の部分の繊維の方向
〔45／０／−45／02／90／０／−45／０／45／
02／90／０〕sに対して、フアスナ継手部Ａの繊維
の方向を
〔45／−452／452／90／−452／452／−452／90／
45〕sとする。すなわちこの例では、外側の部分の
0°層（ｂ、ｄ、ｅ、ｇ、ｉ、ｋ、ｌ、ｎ）をフア
スナ継手部では＋45°または−45°とする。
本実施例においても、前記第１の実施例と同
様、フアスナ継手部の剛性が低くなるので、応力
集中の高い孔部の強度が向上する。
次に本発明の第４の実施例を第７図および第８
図により説明する。第７図は平面図、第８図は第
７図の−断面図である。これらの図において
も、１は繊維強化プラスチクスをａ、ｂ、ｃ……
と積層した複合材より成る母材、４はフアスナ孔
である。
本実施例では一部の積層のフアスナ孔端部（図
中Ｂで示される部分）の繊維の方向が他の部分の
繊維の方向と異なつている。たとえば、前記第３
の実施例と同様に、フアスナ孔端部以外の部分の
0°層をフアスナ孔端部では＋45°または−45°とす
る。
本実施例においても、前記第２の実施例と同
様、フアスナ孔端部の剛性が低くなるので、孔端
の応力集中が緩和され、強度が向上する。
更に他の実施例として、フアスナ継手部または
フアスナ孔端部の積層数を他の部分の積層数より
も多くしたものについて説明する。上記他の部分
の層構成
〔45／０／−45／02／90／０／−45／０／45／
02／90／０〕s
に対し、フアスナ継手部またはフアスナ孔端部の
層構成を、たとえば〔45／−452／452／90／−
452／452／−452／90／45〕ｓ、〔45／−45／０／
45／−45／45／０／−452 ／０／45／90／45／
０／−45／−45／−45／０／45／45／45／０／−
452／０／45／90／45／０／−45〕s、〔45／02 ／−
45／04 ／90／02 ／−45／02 ／45／04 ／90／02 〕s、
または〔45／０／０／０／−45／０／０／02 ／
０／０／90／０／０／０／−45／０／０／０／
45／０／０／02 ／０／０／90／０／０／０／〕sと
するのである。また材料としては、上記他の部分
には炭素繊維複合材を用いる一方、フアスナ継手
部またはフアスナ孔端部では、上記層構成中下線
を引いた層にはガラス繊維複合材を、その他の層
には炭素繊維複合材を、それぞれ用いる。
このような実施例においても、フアスナ継手部
またはフアスナ孔端部の剛性が低いので、この部
分の強度が向上する。
〔発明の効果〕
この発明によれば、フアスナ継手部またはフア
スナ孔端部に局部的に、他の部位と異なる積層構
成または剛性の高くなる伸びの強い材料を用い、
継手部強度を画期的に向上させることができる。
したがつて、複合材部品構造の重量を大幅に軽減
できる。 DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a fastener joint structure for composite parts made of laminated fiber-reinforced plastics. [Prior Art] As shown in Fig. 9, the conventional fastener joint structure for composite parts is made by mechanically drilling holes in a base material 1 such as a plate made by laminating and hardening prepreg, and then forming a joint metal fitting. The structure was such that the second class was fastened with three fasteners.
This joint part simultaneously receives a surface pressure load shared by the fastener 3 and a tensile or compressive load applied as a whole, and due to stress concentration in the hole, the strength is significantly reduced compared to general parts other than the joint part. . Therefore, in the past, in order to satisfy the joint strength requirements, weight was expended by either providing a strength margin for the entire joint or by reinforcing parts of the joint. [Problems to be Solved by the Invention] In the conventional fastener joint structure in which a hole is mechanically drilled in a structure made of a composite material and fastened with a fastener, the following problems were to be solved. (a) Simultaneously receives a surface pressure load shared by the fastener and a tensile or compressive load applied as a whole. (b) There is stress concentration in the fastener hole. (c) Due to (a) and (b) above, the strength of the fastener joint is greater than that of general parts other than the joint. The purpose of this invention is to propose a structural style that minimizes the above-mentioned drawbacks of the conventional fastener joint and dramatically improves the strength of the fastener joint. [Means for Solving the Problems] In order to achieve the above object, the present invention uses the following means. (1) A composite material fastener joint made of laminated fiber-reinforced plastics, in which the material at the fastener joint part or the end of the fastener hole has greater elongation and lower rigidity than the material in other parts. . (2) A fastener joint of a composite material made of laminated fiber-reinforced plastics, characterized in that the direction of the fibers at the fastener joint part or the end of the fastener hole is different from the direction of the fibers in other parts. (3) A composite fastener joint made of laminated fiber-reinforced plastics, characterized in that the number of laminated layers at the fastener joint part or the end of the fastener hole is greater than the number of laminated layers at other parts. [Function] A. By locally lowering the rigidity of the fastener joint, most of the entire tensile or compressive load will flow to the area where there is no fastener hole, which has high rigidity, and the fastener hole will be transferred to the surface where the fastener shares the load. Pressure load is applied. In this way, the surface pressure load and the overall tensile or compressive load are separated at the fastener hole, eliminating the mutual influence of these loads and strength reduction due to stress concentration, and achieving a significant improvement in the strength of the fastener joint. . By locally reducing the rigidity of the fastener hole end and increasing the elongation at failure, the stress concentration at the hole end is alleviated and the strength of the fastener joint can be improved. [Example] An example of the present invention will be described with reference to FIGS. 1 and 2. FIG. 1 is a plan view, and FIG. 2 is a cross-sectional view taken from FIG. 1. In these figures, 1 is a base material made of a composite material in which fiber-reinforced plastics are laminated in the manner of a, b, c, . . . , and 4 is a fastener hole. The direction of the fibers in the laminated layers a, b, c... of the base material 1 is, for example,
[45/0/-45/0 2 /90/0/-45/0/45/
0 2 /90/0] s . However, the subscript s indicates that the sheets are stacked in mirror symmetry, and the subscript 2 indicates that two sheets are stacked (the same applies hereafter). In this example, the 0° layers (b, d, e, g, i, k,
As the material of the fastener joint portion (portion indicated by A in the figure) of (l, n), a material with greater elongation and lower rigidity than the material of the other portions (outer portions) is used. For example, the outer part is made of carbon fiber composite material (CFRP), the fastener joint part A is made of glass fiber composite material (GFRP), and aramid fiber composite material (AFRP).
etc. are used. The width of part A is 5 to 6 times the diameter of the fastener hole.
Double is desirable. In this embodiment, since the rigidity of the fastener joint portion is low, the areas to which the uniform load and the surface pressure load transmitted by the fastener are shared can be separated. In other words, the surface pressure load is transferred to a region with high rigidity by shearing, and the fastener hole only has to share the surface pressure load without sharing a uniform load.This means that the strength of the hole where stress concentration is high increases. will improve. Next, a second embodiment of the present invention will be described with reference to FIGS. 3 and 4. Figure 3 is a plan view, Figure 4 is a 3rd floor view.
FIG. Also in these figures, 1 is a base material made of a composite material in which fiber-reinforced plastics are laminated in layers a, b, c, . . . , and 4 is a fastener hole. In this embodiment, a material having greater elongation and lower rigidity than the material for other portions is used as the material for the end portion of the fastener hole (portion indicated by B in the figure). In this embodiment, since the rigidity of the end of the fastener hole is low, the stress concentration at the end of the hole is alleviated, and the direction of the crack at the time of failure changes, so that the strength is improved. Next, a third embodiment of the present invention is shown in FIGS. 5 and 6.
This will be explained using figures. FIG. 5 is a plan view, and FIG. 6 is a cross-sectional view taken from FIG. In these figures, 1 indicates fiber-reinforced plastics a, b, c...
4 is a fastener hole. In this embodiment, the direction of the fibers in the fastener joint part (the part indicated by A in the figure) of some of the laminated layers is different from the direction of the fibers in the other part (the outer part). For example, the direction of the fibers in the outer part [45/0/-45/0 2 /90/0/-45/0/45/
0 2 / 90 / 0 ] With respect to
45〕 s . That is, in this example, the outer part
The 0° layers (b, d, e, g, i, k, l, n) are set at +45° or -45° at the fastener joint. In this embodiment as well, as in the first embodiment, the rigidity of the fastener joint is reduced, so the strength of the hole where stress concentration is high is improved. Next, a fourth embodiment of the present invention is shown in FIGS. 7 and 8.
This will be explained using figures. FIG. 7 is a plan view, and FIG. 8 is a cross-sectional view taken from FIG. 7. In these figures, 1 indicates fiber-reinforced plastics a, b, c...
4 is a fastener hole. In this embodiment, the direction of the fibers at the ends of the fastener holes in some of the laminated layers (the part indicated by B in the figure) is different from the direction of the fibers in other parts. For example, the third
Similar to the example, the parts other than the fastener hole end
The 0° layer is +45° or -45° at the end of the fastener hole. In this embodiment as well, as in the second embodiment, the rigidity of the end of the fastener hole is reduced, so stress concentration at the end of the hole is alleviated and the strength is improved. As yet another embodiment, a case will be described in which the number of laminated layers at the fastener joint portion or the end portion of the fastener hole is greater than the number of laminated layers at the other portions. Layer structure of other parts above [45/0/-45/0 2 /90/0/-45/0/45/
0 2 /90/0] s , the layer structure of the fastener joint or the end of the fastener hole, for example, [45/-45 2 /45 2 /90/-
45 2 /45 2 /-45 2 /90/45〕 s , [45/ -45 /0/
45/-45/ 45 /0/- 45 2 /0/ 45 /90/ 45 /
0/ -45 /- 45 /- 45 /0/ 45 /45/ 45 /0/-
45 2 /0/ 45 /90/ 45 /0/- 45 〕 s , [45/0 2 /-
45／ 04 ／90／ 02 ／−45／ 02 ／45／ 04 ／90／ 02 〕 s ,
or [45/ 0 /0/ 0 /-45/ 0 /0/ 0 2 /
0/ 0 /90/ 0 /0/ 0 /-45/ 0 /0/ 0 /
45／ 0 ／ 0／ 02 ／0／ 0 ／90／ 0 ／0／ 0 ／ s . As for the material, carbon fiber composite is used for the other parts mentioned above, while at the fastener joint part or the end of the fastener hole, glass fiber composite is used for the underlined layer in the above layer structure, and glass fiber composite is used for the other layers. uses carbon fiber composite materials, respectively. Even in such an embodiment, since the rigidity of the fastener joint portion or the end portion of the fastener hole is low, the strength of this portion is improved. [Effects of the Invention] According to the present invention, a laminated structure different from other parts or a highly elongated material with high rigidity is used locally at the fastener joint or the end of the fastener hole,
The joint strength can be dramatically improved.
Therefore, the weight of the composite component structure can be significantly reduced.
第１図は本発明の第１の実施例の平面図、第２
図は第１図の−断面図、第３図は本発明の第
２の実施例の平面図、第４図は第３図の−断
面図、第５図は本発明の第３の実施例の平面図、
第６図は第５図の−断面図、第７図は本発明
の第４の実施例の平面図、第８図は第７図の−
断面図、第９図は複合材製部品のフアスナ継手
構造を示す図である。
１……母材、２……継手金具、３……フアス
ナ、４……フアスナ孔。
FIG. 1 is a plan view of the first embodiment of the present invention;
The figures are a cross-sectional view of FIG. 1, FIG. 3 is a plan view of a second embodiment of the present invention, FIG. 4 is a cross-sectional view of FIG. 3, and FIG. 5 is a third embodiment of the present invention. plan view of
6 is a sectional view of FIG. 5, FIG. 7 is a plan view of the fourth embodiment of the present invention, and FIG. 8 is a sectional view of FIG. 7.
The sectional view, FIG. 9, is a diagram showing a fastener joint structure of a composite material component. 1...Base metal, 2...Joint fittings, 3...Fusner, 4...Fusner hole.
Claims (1)
アスナ継手において、フアスナ継手部またはフア
スナ孔端部の材料が他の部分の材料よりも伸びが
大きく剛性が低いことを特徴とする複合材のフア
スナ継手。 ２ 繊維強化プラスチクスを積層した複合材のフ
アスナ継手において、フアスナ継手部またはフア
スナ孔端部の繊維の方向が他の部分の繊維の方向
と異なることを特徴とする複合材のフアスナ継
手。 ３ 繊維強化プラスチクスを積層した複合材のフ
アスナ継手において、フアスナ継手部またはフア
スナ孔端部の積層数が他の部分の積層数よりも多
いことを特徴とする複合材のフアスナ継手。[Scope of Claims] 1. A fastener joint made of a composite material made of laminated fiber-reinforced plastics, characterized in that the material of the fastener joint part or the end of the fastener hole has greater elongation and lower rigidity than the material of other parts. Fastener joints for materials. 2. A fastener joint of a composite material in which fiber-reinforced plastics are laminated, wherein the direction of the fibers at the fastener joint part or the end of the fastener hole is different from the direction of the fibers in other parts. 3. A fastener joint of a composite material in which fiber-reinforced plastics are laminated, characterized in that the number of laminated layers at the fastener joint part or the end of the fastener hole is greater than the number of laminated layers at other parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9170488A JPH01263030A (en) | 1988-04-15 | 1988-04-15 | Fastener joint for composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9170488A JPH01263030A (en) | 1988-04-15 | 1988-04-15 | Fastener joint for composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01263030A JPH01263030A (en) | 1989-10-19 |
| JPH0455859B2 true JPH0455859B2 (en) | 1992-09-04 |
Family
ID=14033902
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9170488A Granted JPH01263030A (en) | 1988-04-15 | 1988-04-15 | Fastener joint for composite material |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01263030A (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7087296B2 (en) | 2001-11-29 | 2006-08-08 | Saint-Gobain Technical Fabrics Canada, Ltd. | Energy absorbent laminate |
| BR112012001714B1 (en) * | 2009-10-08 | 2020-04-07 | Mitsubishi Heavy Ind Ltd | main aircraft wing and aircraft fuselage |
| BR112013010337A2 (en) * | 2011-02-04 | 2016-08-02 | Mitsubishi Heavy Ind Ltd | composite material structure, and aircraft wing and fuselage provided |
| JP6004669B2 (en) * | 2012-02-29 | 2016-10-12 | 三菱重工業株式会社 | Composite structure, aircraft wing and aircraft fuselage provided with the same, and method for manufacturing composite structure |
| JP6309324B2 (en) | 2014-03-28 | 2018-04-11 | 三菱重工業株式会社 | Composite structure, aircraft wing and aircraft fuselage provided with the same, and method for manufacturing composite structure |
-
1988
- 1988-04-15 JP JP9170488A patent/JPH01263030A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPH01263030A (en) | 1989-10-19 |
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