JP3086725B2 - Composite members - Google Patents
Composite membersInfo
- Publication number
- JP3086725B2 JP3086725B2 JP03222882A JP22288291A JP3086725B2 JP 3086725 B2 JP3086725 B2 JP 3086725B2 JP 03222882 A JP03222882 A JP 03222882A JP 22288291 A JP22288291 A JP 22288291A JP 3086725 B2 JP3086725 B2 JP 3086725B2
- Authority
- JP
- Japan
- Prior art keywords
- layer
- layers
- heat
- composite member
- exposed
- 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 - Fee Related
Links
Landscapes
- Laminated Bodies (AREA)
Description
【０００１】[0001]
【産業上の利用分野】この発明は、例えば宇宙空間に構
築される構造物等の真空環境における熱制御等の高効率
な熱伝導や、高効率な電気の伝達が要請される各種シス
テムに用いるのに好適する複合部材に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is used for various systems which require high-efficiency heat conduction such as heat control in a vacuum environment such as a structure constructed in outer space, and high-efficiency electricity transmission. And a composite member suitable for:
【０００２】[0002]
【従来の技術】周知のように、宇宙開発の分野において
は、人工衛星に搭載される搭載機器を設置する場合、発
熱体、例えば搭載機器をアルミニウムハニカムサンドイ
ッチパネルで構成される取付板に設置し、この取付板に
埋設したヒートパイプ、冷却管等の熱輸送部材を用いて
放射部に熱輸送を行い、搭載機器の熱制御を行う熱輸送
手段が用いられている。これは、宇宙環境が真空環境で
あることにより、熱伝導を利用した熱制御が有効である
ことによる。2. Description of the Related Art As is well known, in the field of space development, when installing onboard equipment mounted on an artificial satellite, a heating element, for example, onboard equipment is installed on a mounting plate composed of an aluminum honeycomb sandwich panel. In addition, heat transport means for performing heat transport to the radiating portion by using a heat transport member such as a heat pipe or a cooling pipe embedded in the mounting plate and controlling the heat of the mounted equipment is used. This is because the space environment is a vacuum environment, so that heat control using heat conduction is effective.
【０００３】ところが、上記熱輸送手段にあっては、例
えば図１１に示すように熱輸送部材１を取付板２上の搭
載機器３に対向してそれぞれ埋設し、搭載機器３の熱量
をそれぞれに対向配置した熱輸送部材１で図示しない放
射部まで熱輸送することにより、搭載機器３の熱制御が
行われているために、その配置構成に制約を受けるとい
う問題を有する。However, in the above heat transport means, for example, as shown in FIG. 11, a heat transport member 1 is buried opposite to the mounted equipment 3 on the mounting plate 2 so that the heat quantity of the mounted equipment 3 can be reduced. Since the heat is transported to the radiating portion (not shown) by the heat transport member 1 arranged oppositely, the thermal control of the mounted device 3 is performed, so that there is a problem that the arrangement configuration is restricted.
【０００４】これは、特に最近の宇宙開発の分野におけ
る宇宙航行体の大形化の要請にともなって、搭載機器３
の高密度実装化を図る場合に大きな問題が生じる。即
ち、取付板に高密度実装された各搭載機器３は、それぞ
れ熱輸送部材１を介して放射部に熱結合させなければ効
率的な熱制御が困難となるため、上記配置構成の制約
上、大形となるという不具合が生じる。[0004] This is in response to the recent demand for larger space vehicles in the field of space development, and the
A major problem arises when high-density mounting is attempted. That is, since each mounted device 3 densely mounted on the mounting plate is not thermally coupled to the radiating portion via the heat transport member 1, efficient heat control becomes difficult. The problem of large size occurs.
【０００５】そこで、宇宙開発の分野にあっては、小形
化を確保したうえで、搭載機器等の熱伝導側と放熱部等
の被熱伝導側との効率的な熱結合を実現して、高効率な
熱輸送を可能とする熱輸送手段の開発が要請されてい
る。Therefore, in the field of space development, while ensuring miniaturization, an efficient thermal coupling between the heat conduction side of the mounted equipment and the like and the heat conduction side such as the heat radiating portion is realized. There is a demand for the development of heat transport means that enables highly efficient heat transport.
【０００６】なお、係る事情は、宇宙環境に限ることな
く、例えば地上における各種の真空環境システムにおい
ても、熱制御を実施する場合、熱伝導が利用されること
により、同様である。[0006] Such a situation is not limited to the space environment, and is the same, for example, in various vacuum environment systems on the ground because heat conduction is used when performing heat control.
【０００７】[0007]
【発明が解決しようとする課題】以上述べたように、真
空環境における熱輸送手段では、熱伝導側と被熱伝達側
との熱結合に熱輸送部材を用いているために、小形化の
促進に制約を受けるという問題を有していた。As described above, in the heat transport means in a vacuum environment, the heat transport member is used for the thermal coupling between the heat conduction side and the heat transfer side, so that miniaturization is promoted. Had the problem of being restricted by
【０００８】この発明は上記の事情に鑑みてなされたも
ので、構成簡易にして、高効率な熱的結合と共に、高効
率な電気的結合を実現し得るようにした複合部材を提供
することを目的とする。SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and provides a composite member which has a simple structure and can realize high-efficiency thermal coupling and high-efficiency electrical coupling. Aim.
【０００９】[0009]
【課題を解決するための手段及び作用】この発明は、炭
素繊維が樹脂で固着される複数の層が積層された複合部
材において、前記層の積層方向の少なくとも一方の面に
前記各層の炭素繊維の断面が露出する接合部を設けて構
成した。SUMMARY OF THE INVENTION The present invention relates to a composite member in which a plurality of layers to which carbon fibers are fixed with a resin are laminated, wherein at least one surface of the layers in the laminating direction of the layers has carbon fibers of the respective layers. And a junction where the cross section was exposed was provided.
【００１０】上記構成によれば、各層は、その接合部に
炭素繊維の断面が露出されていることにより、被伝達側
と接合された状態において、炭素繊維の断面が被伝達側
に結合される。従って、各層は、その炭素繊維が被伝導
側と熱的及び電気的に高効率に結合される。[0010] According to the above configuration, the cross section of the carbon fiber is connected to the transmission side in a state where each layer is joined to the transmission side because the cross section of the carbon fiber is exposed at the joint portion. . Therefore, in each layer, the carbon fiber is thermally and electrically coupled with the conductive side with high efficiency.
【００１１】また、この発明は、炭素繊維が樹脂で固着
される複数の層が積層された複合部材において、前記層
の積層方向の少なくとも一方の面に前記各層の炭素繊維
の繊維束の周囲面が露出する接合部を設けて構成した。The present invention also relates to a composite member in which a plurality of layers to which carbon fibers are fixed with a resin are laminated, wherein at least one surface of the layers in the laminating direction is a peripheral surface of a carbon fiber fiber bundle of each layer. Is provided by providing a joint portion where is exposed.
【００１２】上記構成によれば、各層は、その接合部に
炭素繊維の繊維束の周囲面が露出されていることによ
り、被伝達側と接合された状態において、炭素繊維の繊
維束の周囲面が被伝導側に結合される。従って、各層は
その炭素繊維が被伝導側と熱的及び電気的に高効率に結
合される。[0012] According to the above configuration, each layer has a peripheral surface of the fiber bundle of carbon fibers exposed at a joint portion thereof. Are coupled to the driven side. Therefore, in each layer, the carbon fiber is thermally and electrically coupled to the conductive side with high efficiency.
【００１３】さらに、この発明は、炭素繊維が樹脂で固
着される複数の層が積層された複合部材において、前記
層の積層方向と略直交する少なくとも一方端に該積層方
向に対して所定の傾斜角を有し、前記各層の炭素繊維の
断面が露出する接合部を設けて構成した。Further, according to the present invention, in a composite member in which a plurality of layers to which carbon fibers are fixed with a resin are laminated, at least one end substantially perpendicular to the laminating direction of the layers has a predetermined inclination with respect to the laminating direction. Each layer was provided with a joint having a corner and a cross section of the carbon fiber of each layer exposed.
【００１４】上記構成によれば、各層は、その接合部に
炭素繊維の断面が積層方向に対して所定の傾斜角を有し
て配列されていることにより、被伝達側との接合におい
て、接合部として十分な接合面積が確保されると共に、
その炭素繊維の断面が被伝導側に結合される。従って、
各層はその炭素繊維が被伝導側と熱的及び電気的に高効
率に結合される。According to the above configuration, each layer has a cross section of carbon fibers arranged at a joint portion thereof at a predetermined inclination angle with respect to the laminating direction. While ensuring a sufficient joint area as a part,
The cross section of the carbon fiber is bonded to the conductive side. Therefore,
In each layer, the carbon fibers are thermally and electrically coupled to the conductive side with high efficiency.
【００１５】[0015]
【実施例】以下、この発明の実施例について、図面を参
照して詳細に説明する。Embodiments of the present invention will be described below in detail with reference to the drawings.
【００１６】図１はこの発明の一実施例に係る複合部材
を示すもので、板状の基板１０は複数のプリプレグ１１
を積層した複数層１１ａで形成される。基板１０の各層
１１ａは、その積層方向の一方の面に炭素繊維の断面が
露出されて接合部１２が形成される。この接合部１２に
は被伝導部として、例えば図２に示すように略同様に形
成される基板１０の接合部１２が載置されて接合され
る。これにより、２枚の基板１０は、その各層１１ａの
炭素繊維の断面同士が接続されて熱的及び電気的に結合
され、相互間の熱及び電気的移送が層内の炭素繊維と略
同様に行われる。FIG. 1 shows a composite member according to one embodiment of the present invention, in which a plate-like substrate 10 includes a plurality of prepregs 11.
Are formed in a plurality of layers 11a. In each of the layers 11a of the substrate 10, the cross section of the carbon fiber is exposed on one surface in the laminating direction to form the joint portion 12. For example, as shown in FIG. 2, a bonding portion 12 of the substrate 10 formed substantially in the same manner as shown in FIG. 2 is placed on and bonded to the bonding portion 12. Thereby, the two substrates 10 are thermally and electrically connected by connecting the cross sections of the carbon fibers of the respective layers 11a, and the heat and electric transfer between them is substantially the same as the carbon fibers in the layers. Done.
【００１７】上記基板は、例えば図３に示す手順で製作
される。即ち、長さ寸法の異なる複数のプリプレグ１１
が積層されて一端が階段状の第１のプリプレグ層１３が
形成され、この第１のプリプレグ層１３の一端上には複
数のプリプレグ１１が順に積層されて第２のプリプレグ
層１４が形成される。ここで、第１のプリプレグ層１３
及び第２のプリプレグ層１４はオートクレープ等を用い
て成形され、その後、該第１のプリプレグ層１３及び第
２のプリプレグ層１４の一部が切削あるいは研削等の機
械的に除去されて略板状に形成され（図１中二点鎖線で
示す部分）、第１及び第２のプリプレグ層１３，１４の
境界部に第２のプリプレグ層１４の各層の炭素繊維の断
面が露出される上記接合部１２が形成される。The above substrate is manufactured, for example, by the procedure shown in FIG. That is, a plurality of prepregs 11 having different length dimensions
Are stacked to form a first prepreg layer 13 having a stepped end, and a plurality of prepregs 11 are sequentially stacked on one end of the first prepreg layer 13 to form a second prepreg layer 14. . Here, the first prepreg layer 13
And the second prepreg layer 14 is formed by using an auto crepe or the like, and then a part of the first prepreg layer 13 and a part of the second prepreg layer 14 are mechanically removed by cutting or grinding to form a substantially prepreg layer. (A portion shown by a two-dot chain line in FIG. 1), and the above-described bonding in which the cross section of the carbon fiber of each layer of the second prepreg layer 14 is exposed at the boundary between the first and second prepreg layers 13 and 14 The part 12 is formed.
【００１８】また、上記基板１０は、例えば基板１０上
に接合部１２を複数箇所設け、図４に示すように複数の
接合部１２（但し、図４中では、図の都合上、図示せ
ず）に対して宇宙航行体に搭載される搭載機器等の発熱
体２０を設置すると共に、熱輸送部材２１をそれぞれ接
合して設置するように構成しても良い。これによると、
発熱体２０及び熱輸送部材２１は基板１０の炭素繊維を
介して熱的に結合され、一つの熱輸送部材２１で効果的
な熱輸送が実現され、宇宙空間における効率的な熱制御
が可能となる。The substrate 10 has, for example, a plurality of joints 12 provided on the substrate 10 and a plurality of joints 12 as shown in FIG. 4 (however, not shown in FIG. ), A heating element 20 such as a device mounted on the spacecraft may be installed, and the heat transport members 21 may be joined and installed. according to this,
The heating element 20 and the heat transport member 21 are thermally coupled via the carbon fiber of the substrate 10, and effective heat transport is realized by one heat transport member 21, enabling efficient heat control in outer space. Become.
【００１９】このように、上記複合部材は、基板１０を
構成する層１１ａの積層方向の一方の面に前記各層１１
ａの炭素繊維の断面が露出する接合部１２を設け、この
接合部１２の炭素繊維の断面が被伝導側に結合されるよ
うに構成した。これによれば、基板１０は、その各層１
１ａの炭素繊維の熱的及び電気的結合特性の優れた断面
が被伝導部に接合されることにより、基板１０自体が熱
輸送部材と同様の機能を果して、被伝導部に対して熱的
及び電気的結合が高効率に行われるため、熱輸送部材の
削減化が図れ、小形化の促進が容易に図れる。As described above, the composite member is provided on one surface of the layer 11a constituting the substrate 10 in the laminating direction.
The joint portion 12 is provided such that the cross section of the carbon fiber is exposed, and the cross section of the carbon fiber of the joint portion 12 is connected to the conductive side. According to this, the substrate 10 has its respective layers 1
The cross section of the carbon fiber having excellent thermal and electrical coupling characteristics of the carbon fiber 1a is joined to the conductive portion, so that the substrate 10 itself performs the same function as the heat transport member, and is thermally and electrically conductive to the conductive portion. Since the electrical coupling is performed with high efficiency, the number of heat transport members can be reduced, and the miniaturization can be easily promoted.
【００２０】なお、上記実施例では、第１のプリプレグ
層１３の一方を階段状に形成して、この第１のプリプレ
グ層１３の一端部に第２のプリプレグ層１４の炭素繊維
の断面が露出する接合部１２を形成したが、これに限る
ことなく、図５に示すように第１のプリプレグ層１３ａ
を略三角形状に形成して（同図（ａ）参照）、この第１
のプリプレグ層１３ａ上に第２のプリプレグ層１４ａを
形成し（同図（ｂ）参照）、第２のプリプレグ層１４ａ
の一部を同図（ｃ）に示すように除去して第１のプリプ
レグ層１３ａを挟んで炭素繊維の断面が露出する接合部
１２ａを形成するようにしても良い。また、この発明は
上記実施例に限ることなく、図６及び図７に示すように
接合部を形成しても良い。In the above embodiment, one of the first prepreg layers 13 is formed in a step-like manner, and the cross section of the carbon fiber of the second prepreg layer 14 is exposed at one end of the first prepreg layer 13. The joining portion 12 is formed, but is not limited to this, and as shown in FIG. 5, the first prepreg layer 13a
Is formed in a substantially triangular shape (see FIG. 3A), and the first
A second prepreg layer 14a is formed on the prepreg layer 13a (see FIG. 2B), and the second prepreg layer 14a is formed.
May be removed as shown in FIG. 3C to form a joint 12a where the cross section of the carbon fiber is exposed with the first prepreg layer 13a interposed therebetween. Further, the present invention is not limited to the above-described embodiment, and a joint may be formed as shown in FIGS.
【００２１】図６の複合部材は、基板１０を形成する層
１１ａの積層方向の一方の面に該各層１１ａの炭素繊維
の繊維束の周囲面が露出する接合部１２ｂを形成したも
ので、例えば図８に示すように、長さ寸法の異なるプリ
プレグ１１を一端を揃えて順に積層した第１のプリプレ
グ層１３ｂが形成される。次に、第１のプリプレグ層１
３ｂの他端の一方の面に長さ寸法の異なるプリプレグ１
１を順に積層した第２のプリプレグ層１４ｂを形成して
成形後、、第１のプリプレグ層１３ｂの各層１１ａの炭
素繊維の繊維束の周囲部をサンディング等の機械的手段
により露出させた接合部１２ｂを基板１０の一方の面に
形成したものである。また、図９に示すようにプリプレ
グ１１の中間部に長さの異なるプリプレグ１１を階段状
に積層した第１のプリプレグ層１３ｃを形成して、この
第１のプリプレグ層１３ｃの階段状部と逆側の面に長さ
寸法の異なるプリプレグ１１を積層した第２のプリプレ
グ層１４ｃを形成し、この第２のプリプレグ層１４ｃの
両端部に対応する第１のプリプレグ層１３ｃの階段状部
側の炭素繊維の繊維束の周囲部を同様にして露出させた
接合部１２ｃを形成するように構成しても良い。The composite member shown in FIG. 6 has a bonding portion 12b formed on one surface of the layer 11a forming the substrate 10 in the laminating direction so that the peripheral surface of the fiber bundle of the carbon fibers of each layer 11a is exposed. As shown in FIG. 8, a first prepreg layer 13b is formed by sequentially stacking prepregs 11 having different lengths with their ends aligned. Next, the first prepreg layer 1
Prepreg 1 having a different length dimension on one surface of the other end of 3b
After forming and forming a second prepreg layer 14b in which the first prepreg layers 1a and 1b are laminated, a bonding portion in which the periphery of the carbon fiber fiber bundle of each layer 11a of the first prepreg layer 13b is exposed by mechanical means such as sanding. 12b is formed on one surface of the substrate 10. Further, as shown in FIG. 9, a first prepreg layer 13c in which prepregs 11 having different lengths are laminated in a step-like manner is formed in an intermediate portion of the prepreg 11, and the first prepreg layer 13c is formed in a reverse direction to the step-like portion of the first prepreg layer 13c. A second prepreg layer 14c formed by laminating prepregs 11 having different lengths on the side surface is formed, and carbon on the step-like side of the first prepreg layer 13c corresponding to both ends of the second prepreg layer 14c is formed. You may comprise so that the joint part 12c which exposed the periphery part of the fiber bundle of fibers similarly may be formed.
【００２２】図７の複合部材は、基板１０を形成する層
１１ａの積層方向と略直交する一方端に該積層方向に対
して所定の傾斜角を有した各層１１ａの炭素繊維の断面
を露出させた接合部１２ｄを形成したものである。この
場合は、例えばプリプレグ１１を積層して形成した基板
１０の端部を所定の傾斜角を有して切削することにより
形成される。また、基板１０に形成する所定の傾斜角を
有する接合部１２ｄとしては、図７に限ることなく、例
えば図１０に示すように基板１０の一端に繊維方向に対
応して略Ｖ字状に突出した接合部１２ｅを形成しても良
い。In the composite member shown in FIG. 7, the cross section of the carbon fibers of each layer 11a having a predetermined inclination angle with respect to the laminating direction is exposed at one end substantially perpendicular to the laminating direction of the layers 11a forming the substrate 10. In this case, the joining portion 12d is formed. In this case, for example, it is formed by cutting an end portion of the substrate 10 formed by laminating the prepregs 11 at a predetermined inclination angle. The bonding portion 12d having a predetermined inclination angle formed on the substrate 10 is not limited to that shown in FIG. 7, and for example, as shown in FIG. The joined portion 12e may be formed.
【００２３】さらに、上記図１及び図６においては、接
合部１２，１２ｂを積層方向に対して略直交する面の一
方面に形成するように構成したが、これに限ることな
く、両面に形成するように構成しても良い。Further, in FIGS. 1 and 6, the joints 12 and 12b are formed on one of the surfaces substantially perpendicular to the laminating direction. However, the present invention is not limited to this. May be configured.
【００２４】また、図７及び図１０においては、所定の
傾斜角を有した接合部１２ｄ，１２ｅを基板１０の繊維
方向の一端に形成した場合で説明したが、これに限るこ
となく、例えば基板１０の両端に形成するようにしても
良い。さらに、また、この発明に用いられる基板として
は、上述したような板状に限ることなく、円筒等の筒状
のもの適用可能である。Although FIGS. 7 and 10 show the case where the joints 12d and 12e having a predetermined inclination angle are formed at one end of the substrate 10 in the fiber direction, the present invention is not limited to this. 10 may be formed at both ends. Further, the substrate used in the present invention is not limited to the above-mentioned plate shape, but may be a cylindrical one such as a cylinder.
【００２５】また、さらに、上記実施例では、宇宙空間
で使用する熱制御のための熱輸送手段として、適用した
場合で説明したが、この発明は、これに限ることなく、
その他、地上における真空環境を含む各種の熱輸送手
段、熱遮蔽手段、電気導通手段としての適用が可能であ
る。よって、この発明は上記実施例に限ることなく、そ
の他、この発明の要旨を逸脱しない範囲で種々の変形を
実施し得ることは勿論のことである。Further, in the above embodiment, the case where the present invention is applied as a heat transport means for controlling heat used in outer space is described. However, the present invention is not limited to this.
In addition, it can be applied as various heat transporting means including a vacuum environment on the ground, a heat shielding means, and an electric conduction means. Therefore, it is needless to say that the present invention is not limited to the above-described embodiment, and that various modifications can be made without departing from the scope of the present invention.
【００２６】[0026]
【発明の効果】以上詳述したように、この発明によれ
ば、構成簡易にして、高効率な熱的結合と共に、高効率
な電気的結合を実現し得るようにした複合部材を提供す
ることができる。As described above in detail, according to the present invention, there is provided a composite member which has a simplified structure and can realize high-efficiency thermal coupling and high-efficiency electrical coupling. Can be.
【図１】この発明の一実施例に係る複合部材を示した
図。FIG. 1 is a view showing a composite member according to one embodiment of the present invention.
【図２】図１の接合状態を示した図。FIG. 2 is a view showing a bonding state of FIG. 1;
【図３】図１の製造工程を説明するために示した図。FIG. 3 is a view shown for explaining the manufacturing process of FIG. 1;
【図４】図１の使用例を示した図。FIG. 4 is a diagram showing a usage example of FIG. 1;
【図５】この発明の他の実施例を示した図。FIG. 5 is a diagram showing another embodiment of the present invention.
【図６】この発明の他の実施例を示した図。FIG. 6 is a diagram showing another embodiment of the present invention.
【図７】この発明の他の実施例を示した図。FIG. 7 is a diagram showing another embodiment of the present invention.
【図８】図７の製造工程を示した図。FIG. 8 is a view showing the manufacturing process of FIG. 7;
【図９】この発明の他の実施例を示した図。FIG. 9 is a diagram showing another embodiment of the present invention.
【図１０】この発明の他の実施例を示した図。FIG. 10 is a diagram showing another embodiment of the present invention.
【図１１】従来の問題点を説明するために示した図。FIG. 11 is a view for explaining a conventional problem.
１０…基板、１１…プリプレグ、１１ａ…層、１２，１
２ａ，１２ｂ，１２ｃ，１２ｄ，１２ｅ…接合部、１
３，１３ａ，１３ｂ，１３ｃ…第１のプリプレグ層、１
４ａ，１４ｂ，１４ｃ…第２のプリプレグ層、２０…発
熱体、２１…熱輸送部材。10: substrate, 11: prepreg, 11a: layer, 12, 1
2a, 12b, 12c, 12d, 12e ... joint, 1
3, 13a, 13b, 13c: first prepreg layer, 1
4a, 14b, 14c: second prepreg layer, 20: heating element, 21: heat transport member.
───────────────────────────────────────────────────── フロントページの続き (58)調査した分野(Int.Cl.7，ＤＢ名) B32B 1/00 - 35/00 B29B 11/16 B29B 15/08 - 15/14 C08J 5/04 - 5/10 C08J 5/24 ──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int. Cl. 7 , DB name) B32B 1/00-35/00 B29B 11/16 B29B 15/08-15/14 C08J 5/04-5 / 10 C08J 5/24
Claims (3)
積層された複合部材において、 前記層の積層方向の少なくとも一方の面に前記各層の炭
素繊維の断面が露出する接合部を設けたことを特徴とす
る複合部材。1. A composite member in which a plurality of layers to which carbon fibers are fixed with a resin are laminated, wherein at least one surface of the layers in the laminating direction is provided with a joint portion in which a cross section of the carbon fibers of each layer is exposed. A composite member characterized by the above-mentioned.
積層された複合部材において、 前記層の積層方向の少なくとも一方の面に前記各層の炭
素繊維の繊維束の周囲面が露出する接合部を設けたこと
を特徴とする複合部材。2. A composite member in which a plurality of layers to which carbon fibers are fixed with a resin are laminated, wherein a peripheral surface of a fiber bundle of carbon fibers of each layer is exposed on at least one surface in a laminating direction of the layers. A composite member comprising a part.
積層された複合部材において、 前記層の積層方向と略直交する少なくとも一方端に該積
層方向に対して所定の傾斜角を有し、前記各層の炭素繊
維の断面が露出する接合部を設けたことを特徴とする複
合部材。3. A composite member in which a plurality of layers to which carbon fibers are fixed with a resin are laminated, wherein at least one end of the layer substantially perpendicular to the laminating direction has a predetermined inclination angle with respect to the laminating direction. A composite member provided with a joint portion in which a cross section of the carbon fiber of each layer is exposed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP03222882A JP3086725B2 (en) | 1991-09-03 | 1991-09-03 | Composite members |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP03222882A JP3086725B2 (en) | 1991-09-03 | 1991-09-03 | Composite members |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0557829A JPH0557829A (en) | 1993-03-09 |
| JP3086725B2 true JP3086725B2 (en) | 2000-09-11 |
Family
ID=16789366
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP03222882A Expired - Fee Related JP3086725B2 (en) | 1991-09-03 | 1991-09-03 | Composite members |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3086725B2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DK200401225A (en) | 2004-08-13 | 2006-02-14 | Lm Glasfiber As | Method for cutting laminate layers, for example a fiberglass or carbon fiber laminate layer in a wind turbine blade |
| JP5675673B2 (en) * | 2012-02-29 | 2015-02-25 | 三菱重工業株式会社 | Fiber reinforced plastic heating element and wind power generator equipped with the heating element |
| JP6484378B1 (en) * | 2018-09-21 | 2019-03-13 | 太平洋工業株式会社 | Resin molded product and method for producing resin molded product |
-
1991
- 1991-09-03 JP JP03222882A patent/JP3086725B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0557829A (en) | 1993-03-09 |
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