JPH05508362A - Manufacture of composite materials - Google Patents
Manufacture of composite materialsInfo
- Publication number
- JPH05508362A JPH05508362A JP3510958A JP51095891A JPH05508362A JP H05508362 A JPH05508362 A JP H05508362A JP 3510958 A JP3510958 A JP 3510958A JP 51095891 A JP51095891 A JP 51095891A JP H05508362 A JPH05508362 A JP H05508362A
- Authority
- JP
- Japan
- Prior art keywords
- laminate
- ring
- blade
- sides
- predetermined distance
- 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.)
- Pending
Links
Classifications
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- D—TEXTILES; PAPER
- D05—SEWING; EMBROIDERING; TUFTING
- D05C—EMBROIDERING; TUFTING
- D05C15/00—Making pile fabrics or articles having similar surface features by inserting loops into a base material
- D05C15/04—Tufting
- D05C15/08—Tufting machines
- D05C15/16—Arrangements or devices for manipulating threads
- D05C15/24—Loop cutters; Driving mechanisms therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/14—Making preforms characterised by structure or composition
- B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
Abstract
(57)【要約】本公報は電子出願前の出願データであるため要約のデータは記録されません。 (57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】 本発明は、例えば、航空機の外面材料を形成するのに特に適した複合材料のよう な複合材料を製造するための装置および方法に関する。[Detailed description of the invention] The invention relates to composite materials such as those particularly suitable for forming the exterior material of aircraft, for example. The present invention relates to an apparatus and method for manufacturing composite materials.
用語「材料」は、本発明の応用に応じて、例えば、積層体継手のようないずれの 適当な構成要素または構造体を含む。Depending on the application of the invention, the term "material" may refer to any Contains appropriate components or structures.
従来から提案されている複合材料は高い弾性率を有する高強度の繊維を均一なマ トリックス内に埋め込むことにより製造されていた。このような材料の一例にお いては、繊維は炭素、アラミドまたは硼素製であり、マトリックスはエポキシ、 ビスマレミド（ｂｉｓ＋ｎａｌｅ＋ｎ１ｄｅ ）またはポリイミド樹脂のような 材料で形成することができる。Composite materials that have been proposed so far are made by combining high-strength fibers with high elastic modulus into a uniform matrix. It was manufactured by embedding it within Trix. An example of such a material is In some cases, the fibers are made of carbon, aramid or boron, and the matrix is made of epoxy, such as bismalemide (bis+nale+n1de) or polyimide resin It can be made of any material.
これらの繊維を、わずかに硬化された樹脂を予め含浸した一方向性、織られた、 または繊維状マツ） （ｍａｔ ）形態で供給して中間織物（ｆａｂｒｉｃ）材 を形成する。この中間織物材は可撓性且つ粘着性であり、その中の繊維フィラメ ントの位置は固定されない。これらの中間織物材の層をモールド内で重ねて組み 立て、次いで圧縮し、加熱する。加熱作用により、樹脂の硬化を促進し、加熱と 圧縮との組み合わせにより、中間織物材を互いに接合して複合材料を形成する。These fibers are unidirectional, woven, pre-impregnated with slightly hardened resin, Alternatively, it can be supplied in the form of fibrous pine (mat) to create an intermediate fabric material. form. This intermediate woven material is flexible and sticky, and the fiber filaments therein are The position of the point is not fixed. These layers of intermediate woven materials are assembled one on top of the other in a mold. Stand, then compress and heat. The heating action accelerates the hardening of the resin, and In combination with compression, the intermediate textile materials are joined together to form a composite material.
本出願人の出願中のＧＢ２２３８９７７Ａ号には、複合材料を製造する方法が開 示されており、この方法においては、各層が粘着性の均一な樹脂マ）−ＩＪフッ クス中高い弾性率を有する高強度の繊維を含んでいる中間織物材を複数層、面と 面とを合わせて設け、上記複数層を間隔を隔てた位置で互いに留め、次いで層組 み立て体を圧縮し、加熱して樹脂を硬化する。The applicant's pending application GB2238977A discloses a method for manufacturing composite materials. In this method, each layer consists of a tacky uniform resin matrix) Multiple layers of intermediate fabric material containing high-strength fibers with high modulus of elasticity are used on both surfaces. The plurality of layers are fastened together at spaced positions, and then the layers are assembled. The modeled body is compressed and heated to harden the resin.
本発明は、特に、中間織物材の層を間隔を隔てた位置で互いに留めるための装置 および方法に関する。The invention particularly relates to an apparatus for fastening layers of intermediate textile material together at spaced locations. and on methods.
本発明の一局面によれば、積層体中に位置決めされた中間織物材の複数の層を互 いに留める装置において、積層体を貫いて通路を形成する第１手段と、用意した 材料の輪を通路に引き通して積層体の両面から延在させる第２手段と、前記輪を 積層体の一方の面から所定の距離を隔てた位置で切断して用意した材料の２つの 独立片を形成する第３手段と、各月の端部分を積層体の両面上に折り返して他方 の片から離れる方向に延在させる手段とを備えていることを特徴とする装置が提 供される。According to one aspect of the invention, multiple layers of intermediate textile material positioned in a laminate are alternately arranged. a first means for forming a passageway through the laminate; second means for drawing a ring of material through the passageway and extending from both sides of the laminate; Two pieces of material prepared by cutting at a predetermined distance from one side of the laminate. a third means for forming independent pieces; and means for extending away from the piece of the Served.
本発明の他の局面によれば、積層体中に位置決めされた中間織物材の複数の層を 互いに留める方法において、積層体を貫いて通路を形成し、用意した材料の輪を 通路に引き通して積層体の両面から延在させ、前記輪を積層体の一方の面から所 定の距離を隔てた位置で切断して用意した材料の２つの独立片を形成、し、各月 の端部分を積層体の両面上に折り返して他方の片から離れる方向に延在させるこ とを特徴とする方法が提供される。According to another aspect of the invention, a plurality of layers of intermediate textile material are positioned in a laminate. In the method of fastening together, a passage is formed through the laminate and the prepared ring of material is the ring from one side of the laminate; Cut a fixed distance apart to form two independent pieces of the prepared material, and Fold the end portions over both sides of the laminate so that they extend away from the other piece. A method is provided that is characterized by:
次いで、中間織物材の留められた層の積層体を圧縮し、加熱して樹脂を硬化する ことができる。The laminate of pinned layers of intermediate textile material is then compressed and heated to cure the resin. be able to.
本発明の一実施例においては、前方切断刃に隣接して長さ方向（ｌｏｎｇｉｔｕ ｄｉｎａｌ）のスロットを有する可動の平らな幅狭いブレードが本発明の第１お よび第２手段を構成する。操作にあたり、ブレードを前進させて積層体を貫いて 通路を形成する。次いで、ブレードが輪の中間点に位置決めされるように、用意 した材料の輪をブレードの長さ方向のスロットに通し、そして輪の中間部分およ び端部分が積層体の両面から延在した状態で輪が通路に位置決めされるように、 ブレードを積層体から引き抜く。第３の手段は、輪の中間部分が積層体の一方の 面から所定距離を隔てて位置決めされると、用意された材料の２つの独立片を形 成するように輪を切る静止ブレードを有している。輪を構成する材料の長さおよ び静止ブレードの位置は、２つの片が各々積層体の両面から等しい距離突出する ように定められる。In one embodiment of the invention, a longitudinal cutting edge is provided adjacent to the forward cutting blade. A movable flat narrow blade having a slot of and constitutes a second means. In operation, the blade is advanced to penetrate the laminate. form a passage. Next, prepare the blade so that it is positioned at the midpoint of the ring. Thread the hoop of material through the slots along the length of the blade and insert the such that the hoop is positioned in the passageway with the end portions extending from both sides of the laminate. Pull the blade out of the stack. The third means is that the middle part of the ring is located on one side of the laminate. When positioned at a predetermined distance from a surface, it forms two independent pieces of prepared material. It has a stationary blade that cuts a ring to form a ring. The length of the material that makes up the ring and and the position of the stationary blades such that the two pieces each protrude an equal distance from both sides of the stack. It is determined as follows.
添付の説明に役立つ図面を参照して本発明の一実施例を以下−例として説明する 。An embodiment of the invention will now be described - by way of example - with reference to the accompanying illustrative drawings. .
第１図乃至第７図はここで前述した中間織物材の層を互いに留める際の７つの段 階を示す略図であり、第８ａ図および第８ｂ図は、それぞれ、中間織物材の層を 互いに留めるための用意した材料のトウ（ｔｏｗ ）の１平面図および側面図で あり、 第９図および第１０図は修正された留め方法の図である。Figures 1 to 7 illustrate the seven steps in fastening together the layers of intermediate fabric material described above. Figures 8a and 8b each represent a layer of intermediate fabric material; 1 in plan and side view of prepared tows of material for fastening together; can be, Figures 9 and 10 are illustrations of a modified fastening method.
第１図乃至第７図を参照すれば、中間織物材の積層体２を留め操作の開始前に除 去される剥離フィルム（図示せず）上に供給する。この積層体は室温、真空下で 圧縮または収縮済みである。この圧縮または収縮により、提案した複合材料の組 み立てを助成する程度の構造剛性が積層体に与えられる。積層体は面と面とを重 ね合わせた材料の複数の層よりなる。中間織物材の各層は、エポキシ、ビスマレ ミド（ｂｉｓｍａｌｅｍｉｄｅ ） 、またはポリイミド樹脂である均一なマト リックスに高い弾性率を有する高強度繊維を埋め込むことにより形成される。こ れらの繊維は一方向性でもよいし、織られてもよいし、あるいは繊維マットの形 態でもよく、これらの繊維は炭素、アラミドまたは硼素のような材料で製造され ていてもよい。各中間織物材層には、織物層が粘着性且つ可撓性であるように樹 脂マトリックスがわずかに硬化された状態で供給され、この段階では、繊維はマ トリックスに位置が固定されていない。積層体２は、形状が矩形であり、前方切 断刃６を有する可動のナイフブレード４の下で水平姿勢で位置決めされる。ブレ ードは、図面の平面内ではその小さい寸法を有し、図面の平面と直角な平面では その大きい寸法を有する。また、ブレード４は平らであり、「平ら」とは、ブレ ードが完全に図面の平面と直角な平面内にあることを意味している。ブレード４ には、細長い長さ方向のスロット８がブレード切断刃６に隣接して位置決めされ ている。Referring to Figures 1 to 7, the intermediate laminate 2 of textile material is removed before the start of the fastening operation. onto a release film (not shown) to be removed. This laminate was prepared at room temperature under vacuum. It has been compressed or deflated. This compression or shrinkage causes the proposed composite material to A degree of structural rigidity is imparted to the laminate to assist in erection. The laminate is stacked face to face. Consists of multiple layers of material kneaded together. Each layer of intermediate woven material is made of epoxy, bismale bismalemide, or a homogeneous matte that is polyimide resin It is formed by embedding high strength fibers with high elastic modulus in the lix. child These fibers may be unidirectional, woven, or in the form of a fiber mat. These fibers may be manufactured from materials such as carbon, aramid or boron. You can leave it there. Each intermediate layer of woven material includes a resin such that the woven layer is both sticky and flexible. The fat matrix is supplied in a slightly hardened state, and at this stage the fibers are Trix has no fixed position. The laminate 2 has a rectangular shape and has a front cut. It is positioned in a horizontal position under a movable knife blade 4 having a cutting edge 6 . blur A board has its small dimensions in the plane of the drawing and in a plane perpendicular to the plane of the drawing. With its large dimensions. In addition, the blade 4 is flat, and "flat" does not mean that the blade 4 is flat. This means that the board lies entirely in a plane perpendicular to the plane of the drawing. blade 4 , an elongated longitudinal slot 8 is positioned adjacent the blade cutting edge 6. ing.
形態が第１ブレード４と同様な第２の平らな幅狭いブレード１０が第１ブレード ４と摺動接触して位置決めされている。このブレード１０は静止しており、その 前方切断刃１２は積層体２の上面１３の上方に所定の距離ｒｌＩＪを隔てて位置 決めされている。A second flat narrow blade 10 similar in form to the first blade 4 is the first blade. It is positioned in sliding contact with 4. This blade 10 is stationary and its The front cutting blade 12 is located above the upper surface 13 of the laminate 2 at a predetermined distance rlIJ. It's decided.
操作においては、ブレード４を第１図に示すその休止位置から前進させて積層体 ２を切り込んでいき、それにより積層体２を貫いてスリット状通路１４を形成す る。スロット８が積層体２の下面１６を通り越すまで、ブレード４を前進させる 。用意した材料の予め切られた所定長さのトウ１８をブレード４の各側から等し い距離延在するようにスロット８に通す。第８ａ図および第８ｂ図を参照すると 、トウ１８は実質的に矩形の断面のものであることがわかるであろう。トウ１８ は予め含浸された（プレプレグ： ｐｒｅｐｒｅｇ ）または乾燥（樹脂無し） 状態である織られたおよび／または無方向性（ｕｎｄｉｒｅｃｔｉｏｎａｌ ） 材料の複数の層から形成されている。各層はケブラー（Ｋｅｖｌａｒ） 、炭素 または硼素製の補強材を含む熱硬化性および／または熱可塑性材料で作られてい る。用語「プレプレグ」とは、Ｂ段階樹脂系が含浸された補強材を指して言う。In operation, the blade 4 is advanced from its rest position shown in FIG. 2, thereby forming a slit-like passage 14 through the laminate 2. Ru. Advance the blade 4 until the slot 8 passes the underside 16 of the stack 2 . A pre-cut length of tow 18 of the prepared material is equally distributed from each side of the blade 4. through the slot 8 so that it extends a long distance. With reference to Figures 8a and 8b , it will be seen that the tow 18 is of substantially rectangular cross-section. Tow 18 pre-impregnated (prepreg) or dried (without resin) woven and/or undirectional Formed from multiple layers of material. Each layer is Kevlar, carbon or made of thermosetting and/or thermoplastic materials containing boron reinforcements. Ru. The term "prepreg" refers to reinforcement material impregnated with a B-stage resin system.
用語「Ｂ段階」とは、プレプレグ織物の取り扱い性を向上させるように粘度およ び粘着性を増大させるために限られた硬化を受けた樹脂を指して言う。The term "B stage" refers to the viscosity and refers to a resin that has undergone limited curing to increase its adhesive properties and tack.
これは、熱硬化プレプレグが、織られたものであっても無方向性（ｕｎｄｉｒｅ ｃｔｉｏｎａｌ ）であっても、加工業者により供給される状態であるが、この 特定の発明にとっては何ら独特ではない。This means that the thermoset prepreg, even if woven, is non-directional. ctional) is supplied by the processor, but this There is nothing unique about any particular invention.
トウ材料の層（積層体）は圧縮状態にあり、この圧縮状態とは、室温のみで真空 下で固定された材料の積層体を指して言う。The layers of tow material (laminates) are in a compressed state, and this compressed state is defined as a vacuum at room temperature only. Refers to the laminate of material fixed underneath.
次いで、第４図および第５図に示すようにブレード４を引き抜き、スロット８の 下縁部を積層体２の上面１３の上に距離ｒＪまで引き抜くと、静止ブレード１０ の切断刃１２がトウ１８の輪を切って第５図に示すようにトウの２つの独立片２ ０．２２を形成する。静止ブレード１０の位置およびトウ片２０．２２の長さは 、片２０．２２が互いに等しい長さのものであり、各々が積層体２の上面および 下面１３．１６から等しい距離延在するように定められている。Next, as shown in FIGS. 4 and 5, pull out the blade 4 and insert it into the slot 8. When the lower edge is pulled out to a distance rJ above the upper surface 13 of the stack 2, the stationary blade 10 The cutting blade 12 cuts the ring of the tow 18 to form two independent pieces 2 of the tow as shown in FIG. Form 0.22. The position of the stationary blade 10 and the length of the tow piece 20.22 are , the pieces 20, 22 are of equal length, each covering the top surface of the stack 2 and It is defined to extend an equal distance from the lower surface 13.16.
第６図を参照すると、トウ片２０．２２を、各々、それらの端部分が互いに離れ る方向に延在するように、積層体２の上面および下面１３．１６に折り返す。Referring to FIG. 6, the tow pieces 20, 22 are each separated from each other at their end portions It is folded back on the upper and lower surfaces 13, 16 of the laminate 2 so as to extend in the direction shown in FIG.
複数の留めトウ１８を積層体２に互いに所望の間隔を隔てた位置に位置決めする ように上記の操作を繰り返し、次いで積層体２および位置決めされたトウ留め具 を硬化する。A plurality of fastening tows 18 are positioned on the laminate 2 at desired distances from each other. Repeat the above operations as shown, then remove the laminate 2 and the positioned toe fasteners. harden.
第９図を参照すると、望むなら、折り返されたトウ片２０．２２を覆って追加の 中間織物材層を設置してもよい。これらの追加層はトウ片２０．２２のみ、ある いは積層体２の上面および下面１３．１６の全体を覆うように寸法法めされる。Referring to FIG. 9, if desired, an additional An intermediate layer of textile material may also be provided. These additional layers are only on the toe pieces 20.22. Alternatively, it is dimensioned to cover the entire top and bottom surfaces 13, 16 of the laminate 2.
第１０図を参照すると、次いで、積層体およびトウ留め具を硬化してトウ留め具 を封入する。Referring to FIG. 10, the laminate and tow fastener are then cured to form a tow fastener. Enclose.
積層体２およびトウ留め具を硬化する１つの適当な装置および方法は本出願人の 出願中の特許出願公報ＧＢ２２３８９７７Ａ号に記載されている。One suitable apparatus and method for curing laminate 2 and tow fasteners is described by Applicants. It is described in the pending patent application publication number GB2238977A.
この実施例の変更例においては、単一の積層体２０代わりに、本出願人の出願中 の特許出願公報ＧＢ２２３８９７７Ａ号に開示されているように重ね合わせ関係 に置かれた２つの中間織物材の積層体を使用することができる。In a variation of this embodiment, instead of a single laminate 20, the The superposition relationship as disclosed in patent application publication No. GB2238977A A laminate of two intermediate textile materials placed in a laminate can be used.
本発明の上記の図示実施例は下記の有利な特徴を有している。The above illustrated embodiment of the invention has the following advantageous features.
（ａ）亀裂伝播に対する増加した弾性とともに、向上した耐衝撃性、引張強度、 剥離強度および剪断強度。(a) improved impact resistance, tensile strength, along with increased resiliency against crack propagation; Peel strength and shear strength.
（ｂ）先に知られていた機械的留め具の場合よりも、トウの構造要素を、留めら れた材料に付与される荷重と、より正確に整合するように位置決めすることがで きる。(b) make the structural elements of the tow more secure than previously known mechanical fasteners; The material can be positioned to more accurately align with the load applied to the material. Wear.
（ｃ）公知の機械的継手と関連した下記の主な問題を解消することができる。(c) The following main problems associated with known mechanical joints can be overcome:
（１）積層耐の厚さの増大が公知の機械的留め具により生じる増大より少ない。(1) The increase in laminate thickness is less than that produced by known mechanical fasteners.
これは、切断ブレードが積層体の材料のきれいな切断を行い、次の硬化工程中に 積層体の厚さのいずれの増大も少なくとも部分的に除去されるからである。This allows the cutting blade to make a clean cut through the laminate material during the subsequent curing process. This is because any increase in the thickness of the laminate is at least partially removed.
（２）機械的留め操作の技術で使用される穴あけ、ジグ工作、皿座ぐり、および リベット留めと関連した代表的な問題が回避される。(2) drilling, jig-working, countersinking, and Typical problems associated with riveting are avoided.
（３）継手は自己シール性であり、従って、不利な環境で使用するのに理想的で ある。かかる用途の一例はあらゆる天候状態で使用される航空機の翼に燃料を収 容するための使用である。(3) The fitting is self-sealing and is therefore ideal for use in hostile environments. be. An example of such an application is the collection of fuel on aircraft wings used in all weather conditions. It is used to accommodate people.
（４）これらの留め具は機械的留め具より軽い。(4) These fasteners are lighter than mechanical fasteners.
（５）完成された継手は積層体の外面上において空気力学的に滑らかであり、そ の結果、充填、フェザリング、平滑化または皿座ぐり操作のいずれも行うことが 必要でない。(5) The completed joint is aerodynamically smooth on the outer surface of the laminate; As a result, any filling, feathering, smoothing or countersinking operations can be performed. Not necessary.
（ｄ）（１）中間織物層を剥離しないようにするための剥離防止留め具として作 用するように、 （２）硬化操作前および硬化操作中に積層体の中間織物層を適所に正確に固着す るように、 継手を使用して、例えば積層体の端部に、積層体の局部的補強を行うことができ る。(d) (1) Serves as an anti-peel fastener to prevent the intermediate fabric layer from peeling. to use, (2) Accurately securing the intermediate fabric layer of the laminate in place before and during the curing operation; As if Joints can be used to provide local reinforcement of the laminate, for example at the ends of the laminate. Ru.
（ｅ）留め操作は、−回の自動化操作で完了することができるので、機械的留め 具の場合の操作より労力が効率的である。(e) Mechanical fastening, since the fastening operation can be completed in - times of automated operation. It is more labor efficient than the operation with tools.
（ｆ）留め具が非金属であるので、安全率がより高い。例えば、留め具を燃料容 器環境中で使用する場合、アーク発生の危険が回避される。(f) The safety factor is higher because the fasteners are non-metallic. For example, if the fastener is When used in a heated environment, the risk of arcing is avoided.
（ｇ）例えば、刃および補剛材ウェッブ（ｗｅｂ ）の場合のように、追加の留 めを必要とする領域、および留め具が通常使用されない領域に留め具を位置決め することができる。(g) Additional fastenings, e.g. in the case of blades and stiffener webs. Positioning fasteners in areas where fasteners are required and where fasteners are not normally used can do.
（ｈ）進歩した複合材料の構造強度を増大させるために、すなわち、層の離層を 防ぐためにトウ留め具を使用することができる。(h) To increase the structural strength of advanced composite materials, i.e. delamination of layers. Tow fasteners can be used to prevent this.
（ｉ）本発明の留め具では、金属留め具と関連した電蝕（ｇａｌｖａｎｉｃ ｃ ｏｒｒｏｓｉｏｎ）問題が生じない。(i) The fasteners of the present invention prevent galvanic corrosion associated with metal fasteners. (orrosion) problem does not occur.
（ｊ＞留められる材料の荷重付与要件に対処するために、トウ用に高強度または 高弾性率の材料を選択することができる。(j> high strength or High modulus materials can be selected.
要約 積層体（２）を形成すべく中間織物材の複数の水平層を互いに留めるための装置 は第１ナイフブレード（４）を有する。このブレード（４）は前方切断刃（６） を有しており、ブレード（４）には、長さ方向のスロット（８）が位置決めされ ている。summary Apparatus for fastening together horizontal layers of intermediate textile material to form a laminate (2) has a first knife blade (4). This blade (4) is the front cutting blade (6) The blade (4) has a longitudinal slot (8) positioned therein. ing.
第２の平らなナイフブレード（１０）がブレード（４）と摺動接触している。こ のブレード（１０）は不動であり、その前方切断刃（１２）は積層体（２）の上 面（１３）の上方に所定の距離を隔てて位置決めされている。ブレード（４）を 前進させて、スロット（８）が積層体の下面（１６）を通り越すまで、積層体（ ２）を切っていく。所定長さのトウ（１８）をブレード（４）の各側で等しい距 離延在するようにスロット（８）に通す。次いで、ブレード（１０）の切断刃（ １２）がトウ輪を切って２つの独立片（２０，２２）を形成するまで、ブレード （４）を引き抜く。これらの片（２０，２２）を積層体（２）の上面および下面 （１３，１６）に折り返し、次いで積層体を硬化する。A second flat knife blade (10) is in sliding contact with blade (4). child The blade (10) is stationary and its front cutting edge (12) rests on the stack (2). It is positioned above the surface (13) at a predetermined distance. Blade (4) Advance the laminate ( 2) Cut. A tow (18) of a predetermined length is placed at an equal distance on each side of the blade (4). through the slots (8) so as to extend apart. Next, the cutting blade ( 12) cuts the toe ring to form two independent pieces (20, 22). Pull out (4). These pieces (20, 22) are attached to the upper and lower surfaces of the laminate (2). (13, 16) and then harden the laminate.
国際調査報告international search report
Claims (1)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9014770.3 | 1990-07-03 | ||
| GB909014770A GB9014770D0 (en) | 1990-07-03 | 1990-07-03 | Manufacture of a composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05508362A true JPH05508362A (en) | 1993-11-25 |
Family
ID=10678613
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3510958A Pending JPH05508362A (en) | 1990-07-03 | 1991-06-26 | Manufacture of composite materials |
Country Status (9)
| Country | Link |
|---|---|
| EP (1) | EP0648159A1 (en) |
| JP (1) | JPH05508362A (en) |
| AU (1) | AU8006791A (en) |
| BR (1) | BR9106615A (en) |
| CA (1) | CA2085253A1 (en) |
| FI (1) | FI925805A (en) |
| GB (2) | GB9014770D0 (en) |
| IL (1) | IL98585A0 (en) |
| WO (1) | WO1992000845A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004536726A (en) * | 2001-08-02 | 2004-12-09 | エバート コンポジッツ コーポレイション | Method of clamping top and bottom ends of Z-axis fiber to top and bottom surfaces of composite laminate, respectively |
| JP2007511391A (en) * | 2003-11-10 | 2007-05-10 | エバート コンポジッツ コーポレイション | Method for inserting Z-axis reinforcing fiber into composite laminate |
| US8915201B2 (en) | 2007-11-21 | 2014-12-23 | Airbus Operations Gmbh | Device and method for producing a reinforced foam material |
| US9289927B2 (en) | 2005-05-27 | 2016-03-22 | Airbus Operations Gmbh | Reinforcement of cellular materials |
| JP2020537059A (en) * | 2017-10-10 | 2020-12-17 | グロツ・ベッケルト コマンディートゲゼルシャフト | Equipment and Methods for Manufacturing Carrier Members with Multiple Fiber Bundles |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19628388A1 (en) * | 1996-07-13 | 1998-01-15 | Inst Polymerforschung Dresden | Multi-axial, multi-layer, fiber preform with adequate force flow with at least partial Z-axis reinforcement and a process for its production |
| US7785693B2 (en) | 2001-04-06 | 2010-08-31 | Ebert Composites Corporation | Composite laminate structure |
| US6676785B2 (en) | 2001-04-06 | 2004-01-13 | Ebert Composites Corporation | Method of clinching the top and bottom ends of Z-axis fibers into the respective top and bottom surfaces of a composite laminate |
| US6645333B2 (en) * | 2001-04-06 | 2003-11-11 | Ebert Composites Corporation | Method of inserting z-axis reinforcing fibers into a composite laminate |
| US7731046B2 (en) | 2001-04-06 | 2010-06-08 | Ebert Composites Corporation | Composite sandwich panel and method of making same |
| DE102005035681A1 (en) * | 2005-07-27 | 2007-02-08 | Röhm Gmbh | Manufacturing process for reinforcing core materials for core composites and core composite structures |
| DE102007033869A1 (en) * | 2007-07-20 | 2009-01-29 | Eads Deutschland Gmbh | Apparatus and method for providing cut-to-length rovings and machine for reinforcing a textile semifinished product |
| DE102009010292A1 (en) * | 2009-02-24 | 2010-08-26 | Bayerische Motoren Werke Aktiengesellschaft | Process for producing a fiber-reinforced plastic component |
| WO2016180420A1 (en) * | 2015-05-12 | 2016-11-17 | Vestas Wind Systems A/S | Improvements relating to the production of wind turbine components |
| US10800114B2 (en) | 2016-08-09 | 2020-10-13 | Nissan Motor Co., Ltd. | Molding method for composite material and intermediate member for composite material |
| FR3098444B1 (en) * | 2019-07-08 | 2021-10-01 | Soc Internationale Pour Le Commerce Et Lindustrie | A method of reinforcing a panel and a method of manufacturing a composite panel implementing such a method |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB600177A (en) * | 1945-09-29 | 1948-04-01 | Francis Colin Curtis | A tufting needle embodying a cutter, wool-feeding action, and length of stitch adjuster |
| US3142276A (en) * | 1962-06-25 | 1964-07-28 | Roger H Mullen Inc | Device for forming cut pile fabrics and the like |
| AU3984772A (en) * | 1971-05-05 | 1973-09-13 | Rheem Australia Limited | Reinforced plastic mechanical fasteners and method and means for forming them |
| DE3246803A1 (en) * | 1982-12-17 | 1984-06-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | METHOD FOR PRODUCING COMPONENTS FROM LAYERS OF FIBER REINFORCED PLASTIC |
| FR2565262B1 (en) * | 1984-05-29 | 1986-09-26 | Europ Propulsion | METHOD FOR MANUFACTURING A MULTI-DIRECTIONAL FIBROUS TEXTURE AND DEVICE FOR CARRYING OUT THIS METHOD |
-
1990
- 1990-07-03 GB GB909014770A patent/GB9014770D0/en active Pending
-
1991
- 1991-06-23 IL IL98585A patent/IL98585A0/en unknown
- 1991-06-26 WO PCT/GB1991/001033 patent/WO1992000845A1/en not_active Application Discontinuation
- 1991-06-26 CA CA002085253A patent/CA2085253A1/en not_active Abandoned
- 1991-06-26 BR BR919106615A patent/BR9106615A/en not_active Application Discontinuation
- 1991-06-26 AU AU80067/91A patent/AU8006791A/en not_active Abandoned
- 1991-06-26 GB GB9113766A patent/GB2245862B/en not_active Expired - Fee Related
- 1991-06-26 EP EP91911858A patent/EP0648159A1/en not_active Withdrawn
- 1991-06-26 JP JP3510958A patent/JPH05508362A/en active Pending
-
1992
- 1992-12-21 FI FI925805A patent/FI925805A/en not_active Application Discontinuation
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004536726A (en) * | 2001-08-02 | 2004-12-09 | エバート コンポジッツ コーポレイション | Method of clamping top and bottom ends of Z-axis fiber to top and bottom surfaces of composite laminate, respectively |
| JP2007511391A (en) * | 2003-11-10 | 2007-05-10 | エバート コンポジッツ コーポレイション | Method for inserting Z-axis reinforcing fiber into composite laminate |
| US9289927B2 (en) | 2005-05-27 | 2016-03-22 | Airbus Operations Gmbh | Reinforcement of cellular materials |
| US8915201B2 (en) | 2007-11-21 | 2014-12-23 | Airbus Operations Gmbh | Device and method for producing a reinforced foam material |
| JP2020537059A (en) * | 2017-10-10 | 2020-12-17 | グロツ・ベッケルト コマンディートゲゼルシャフト | Equipment and Methods for Manufacturing Carrier Members with Multiple Fiber Bundles |
Also Published As
| Publication number | Publication date |
|---|---|
| IL98585A0 (en) | 1992-07-15 |
| EP0648159A1 (en) | 1995-04-19 |
| AU8006791A (en) | 1992-02-04 |
| CA2085253A1 (en) | 1992-01-04 |
| GB9113766D0 (en) | 1991-08-14 |
| GB2245862A (en) | 1992-01-15 |
| GB9014770D0 (en) | 1990-08-22 |
| GB2245862B (en) | 1994-01-26 |
| FI925805A0 (en) | 1992-12-21 |
| WO1992000845A1 (en) | 1992-01-23 |
| BR9106615A (en) | 1993-06-01 |
| FI925805A (en) | 1992-12-21 |
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