KR100553399B1 - Composite laminate - Google Patents
Composite laminate Download PDFInfo
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- KR100553399B1 KR100553399B1 KR1019980063181A KR19980063181A KR100553399B1 KR 100553399 B1 KR100553399 B1 KR 100553399B1 KR 1019980063181 A KR1019980063181 A KR 1019980063181A KR 19980063181 A KR19980063181 A KR 19980063181A KR 100553399 B1 KR100553399 B1 KR 100553399B1
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- South Korea
- Prior art keywords
- composite laminate
- fibers
- prepreg
- present
- thermoplastic film
- Prior art date
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- 239000002131 composite material Substances 0.000 title claims abstract description 29
- 229920001169 thermoplastic Polymers 0.000 claims abstract description 17
- 239000004416 thermosoftening plastic Substances 0.000 claims abstract description 17
- 229920005989 resin Polymers 0.000 claims abstract description 16
- 239000011347 resin Substances 0.000 claims abstract description 16
- 239000000835 fiber Substances 0.000 claims abstract description 9
- 229920001187 thermosetting polymer Polymers 0.000 claims abstract description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 7
- 239000004917 carbon fiber Substances 0.000 claims abstract description 7
- 239000012783 reinforcing fiber Substances 0.000 claims abstract description 5
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052796 boron Inorganic materials 0.000 claims abstract description 4
- 239000003365 glass fiber Substances 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 12
- 229920005992 thermoplastic resin Polymers 0.000 claims description 4
- 239000004696 Poly ether ether ketone Substances 0.000 claims description 3
- 239000004952 Polyamide Substances 0.000 claims description 3
- 239000004697 Polyetherimide Substances 0.000 claims description 3
- 229920002647 polyamide Polymers 0.000 claims description 3
- 239000004417 polycarbonate Substances 0.000 claims description 3
- 229920000515 polycarbonate Polymers 0.000 claims description 3
- 229920000728 polyester Polymers 0.000 claims description 3
- 229920002530 polyetherether ketone Polymers 0.000 claims description 3
- 229920001601 polyetherimide Polymers 0.000 claims description 3
- 239000004734 Polyphenylene sulfide Substances 0.000 claims description 2
- 229920000069 polyphenylene sulfide Polymers 0.000 claims description 2
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 7
- 239000000853 adhesive Substances 0.000 description 5
- 230000001070 adhesive effect Effects 0.000 description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 5
- 229920006267 polyester film Polymers 0.000 description 5
- 239000011229 interlayer Substances 0.000 description 3
- 238000003475 lamination Methods 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- 239000002904 solvent Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000005191 phase separation Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000012958 reprocessing Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 239000012815 thermoplastic material Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/07—Parts immersed or impregnated in a matrix
- B32B2305/076—Prepregs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2398/00—Unspecified macromolecular compounds
- B32B2398/20—Thermoplastics
Landscapes
- Laminated Bodies (AREA)
Abstract
본 발명은 탄소섬유, 유리섬유 및 보론섬유를 포함하는 군에서 선택되는 1종 이상의 섬유로 이루어진 토우(2b)가 일방향으로 배열된 보강섬유시트가 열경화성 수지(2a)로 함침된 프리프레그(2)들 사이에 다수개의 두께방향 구멍(3a)이 천공된 열가소성 필름(3)이 삽입되어 적층된 콤포지트 라미네이트에 관한 것으로서, 본 콤포지트 라미네이트는 균열 내재시 파괴인성이 향상 되어 콤포지트 라미네이트의 취성 파괴거동을 방지할 수 있어 높은 비강도 및 비탄성도 특성 및 우수한 파괴인성을 동시에 요구하는 용도, 예를 들어 볼트, 리벳 등의 기계적 결합이 요구되는 스포츠-레져 용품, 산업기계 부품 및 항공기 부품 등에 매우 효과적으로 적용할 수 있다.The present invention is a prepreg (2) impregnated with a thermosetting resin (2a) is a reinforcing fiber sheet in which a tow (2b) made of one or more fibers selected from the group consisting of carbon fibers, glass fibers and boron fibers is arranged in one direction. The present invention relates to a composite laminate in which a plurality of thickness holes (3a) perforated thermoplastic films (3) are inserted and laminated between the composite laminates. It can be applied very effectively to applications requiring high specific strength and inelasticity and good fracture toughness, for example, sports-leisure products, industrial machinery parts and aircraft parts requiring mechanical coupling such as bolts and rivets. have.
Description
본 발명은 수지함침 일방향 프리프레그가 적층구성되는 콤포지트 라미네이트의 파괴인성의 향상에 관한 것이다. The present invention relates to the improvement of fracture toughness of a composite laminate in which a resin impregnated one-way prepreg is laminated.
일반적으로 탄소섬유, 유리섬유, 보론섬유 등과 같은 보강섬유 토우를 일방향으로 배열한 시트내에 열경화성 수지를 함침시킨 프리프레그는 높은 비강도(단위 무게당 강도) 및 비강성도(단위 무게당 강성도)를 요구하는 각종 스포츠-레져 용품, 산업기계 부품 및 항공기 부품 등에 널리 이용되고 있다.In general, prepregs impregnated with thermosetting resins in sheets arranged in one direction of reinforcing fiber tows such as carbon fiber, glass fiber, and boron fiber require high specific strength (strength per unit weight) and specific rigidity (stiffness per unit weight). It is widely used in various sports-leisure products, industrial machinery parts and aircraft parts.
이러한 열경화성 수지를 기재(matrix material)로 한 프리프레그를 적층하여 열과 압력의 경화싸이클(curing cycle)을 거쳐 성형된 콤포지트 라미네이트내에 균열이 존재하면, 외부에서 하중이 가해질 때 사용된 열경화성 수지의 취성파괴 특성으로 인해 층간분리현상(delamination) 및 취성파괴현상을 동반하면서 급격하게 콤포지트 라미네이트의 구조안정성을 잃게 된다.If a prepreg is laminated using a thermosetting resin as a matrix material and cracks are present in the composite laminate formed through a curing cycle of heat and pressure, the brittle fracture of the thermosetting resin used when a load is applied from the outside. Due to its properties, it is accompanied by delamination and brittle fracture, and suddenly loses the structural stability of the composite laminate.
이러한 콤포지트 라미네이트의 취성파괴거동을 보완하기 위하여 종래에는 열경화성 수지 배합공정중에 고무 혹은 열가소성 수지를 투입하여 프리프레그 기재수지의 파괴인성을 높이는 방법이 시도되었다. 그러나 이러한 방법은 고무 혹은 열가소성 수지를 공정투입에 적합한 상태로 가공하는 과정에 많은 시간이 걸리고, 또한 높은 효율 향상을 위해서는 용제를 사용하기도 하나 사용되는 용제로 인한 유해성이 새로운 문제가 된다. 또한 수지배합시 점도가 상승하여 레진필름 캐스팅(resin flim casting)공정에서 공정 속도가 급격히 떨어지는 단점도 있다. 또한 배합된 수지를 장기 보관시 상분리 현상이 발생하여 공정 투입전에 재가공 필요성이 대두된다.In order to supplement the brittle fracture behavior of the composite laminate, conventionally, a method of increasing the fracture toughness of the prepreg base resin by adding a rubber or a thermoplastic resin during the thermosetting resin mixing process has been attempted. However, this method takes a lot of time to process the rubber or thermoplastic resin in a state suitable for process injection, and also the use of a solvent to improve the high efficiency, but the hazard caused by the solvent used is a new problem. In addition, there is a disadvantage in that the process speed drops sharply in the resin film casting process due to the increase in viscosity during resin blending. In addition, the long-term storage of the blended resin phase separation occurs a necessity of reprocessing before the process input.
다른 종래 방법으로는 프리프레그 적층시 각 층간에 층간 접착력 향상을 위하여 필름상 접착제를 추가로 적층한 후 콤포지트 라미네이트를 성형하는 방법이 제안되었다. 이러한 방법으로 제조된 콤포지트 라미네이트는 무게가 증가하여 비강도 및 비강성도가 떨어질뿐 아니라, 고가의 필름상 접착제가 사용되어 제품의 경제성도 떨어진다.As another conventional method, a method of forming a composite laminate after further laminating a film adhesive for improving interlayer adhesion between layers during prepreg lamination has been proposed. Composite laminates produced in this way not only increase the weight and reduce the specific strength and the specific rigidity, but also use the expensive film adhesive to reduce the economics of the product.
따라서 본 발명은 선행기술의 제반 문제점을 감안하여 프리프레그 제조시 별도의 수지배합 추가공정이 불필요하고 콤포지트 라미네이트 성형시 높은 비강도 및 비강성도 특성을 유지하면서 파괴인성이 향상된 경제성이 우수한 콤포지트 라미네이트를 제공하는 것을 목적으로 한다.Accordingly, the present invention provides a composite laminate having excellent economic efficiency with improved fracture toughness while maintaining high specific strength and non-stiffness characteristics when forming a composite laminate without requiring a separate resin blending additional process when preparing prepregs in consideration of various problems of the prior art. It aims to do it.
상기한 목적을 달성하기 위해 제공되는 본 발명에 의하면 탄소섬유, 유리섬유 및 보론섬유를 포함하는 군에서 선택되는 1종 이상의 섬유로 이루어진 토우가 일방향으로 배열된 보강섬유시트가 열경화성 수지로 함침된 프리프레그들 사이에 다수개의 두께방향 구멍이 천공된 열가소성 필음이 삽입되어 적층된 것을 특징으로 하는 콤포지트 라미네이트가 제공된다.According to the present invention provided to achieve the above object, a tow made of at least one fiber selected from the group consisting of carbon fiber, glass fiber and boron fiber is a pre-impregnated reinforcing fiber sheet is arranged in one direction with a thermosetting resin There is provided a composite laminate characterized in that a plurality of thickness holes perforated thermoplastic pens are inserted and stacked between the pregs.
또한 본 발명의 콤포지트 라미네이트는 상기 열가소성 필름이 폴리에스터, 폴리카보네이트, 폴리아미드, 폴리에테르이미드, 폴리에테르에테르케톤 및 폴리페닐렌설파이드를 포함하는 군에서 선택되는 1종 이상의 열가소성 수지로 된 것임을 특징으로 한다.In addition, the composite laminate of the present invention is characterized in that the thermoplastic film is at least one thermoplastic resin selected from the group comprising polyester, polycarbonate, polyamide, polyetherimide, polyetheretherketone and polyphenylene sulfide. do.
또한 본 발명의 콤포지트 라미네이트는 열가소성 필름의 두께가 0.01∼0.1㎜이고, 구멍의 표면적 비율이 전체 프리프레그 접착면적의 10∼50%인 것을 특징으로 한다.The composite laminate of the present invention is characterized in that the thickness of the thermoplastic film is 0.01 to 0.1 mm, and the surface area ratio of the pores is 10 to 50% of the total prepreg adhesion area.
이하 첨부도면을 참조하여 본 발명을 보다 상세하게 설명하기로 한다. Hereinafter, the present invention will be described in more detail with reference to the accompanying drawings.
본 발명의 콤포지트 라미네이트는 파괴인성의 향상을 위하여 토우(2b)가 일방향으로 배열된 보강섬유시트가 열경화성 수지(2a)로 함침된 프리프레그(2)들 사이에 다수개의 두께방향 구멍(3a)이 천공된 열가소성 필름(3)이 삽입되어 적층되는 것에 주된 특징이 있다.In the composite laminate of the present invention, in order to improve fracture toughness, a plurality of thickness holes 3a are formed between the prepregs 2 impregnated with the thermosetting resin 2a in which the reinforcing fiber sheet in which the tow 2b is arranged in one direction is formed. The main feature is that the perforated thermoplastic film 3 is inserted and laminated.
도 1에 도시되는 바와 같이 본 발명의 콤포지트 라미네이트 성형을 위한 프리프레그 적층시 이형지(1)는 박리, 제거된다. As shown in FIG. 1, the release paper 1 is peeled and removed when the prepreg is laminated for the composite laminate molding of the present invention.
도 2에는 콤포지트 라미네이트의 파괴인성 향상을 위하여 프리프레그 적층시 각 층간에 삽입되는 열가소성 필름(3)에 천공되어 있는 구멍(3a)들의 한 배열형태가 예시된다.2 illustrates an arrangement of holes 3a perforated in the thermoplastic film 3 inserted between the layers during prepreg lamination to improve fracture toughness of the composite laminate.
도 2의 열가소성 필름(3)의 재료로는 폴리에스터, 폴리카보네이트, 폴리아미드, 폴리에테르이미드, 폴리에테르에테르케톤, 폴리에틸렌설파이드 등이 사용될 수 있다. 사용되는 필름의 두께는 열가소성 재료의 특성에 따라 적절하게 조절할 수 있다. 바람직한 열가소성 필름(3) 두께 범위는 0.01∼0.1㎜가 적당하다. 또한 열가소성 필름(3)에 천공된 구멍(3a)의 면적으로 프리프레그 층간 접착면적을 조절할 수 있으며, 바람직한 구멍면적비율은 프리프레그 접착면적의 10∼50% 이다.Polyester, polycarbonate, polyamide, polyetherimide, polyetheretherketone, polyethylenesulfide, or the like may be used as the material of the thermoplastic film 3 of FIG. The thickness of the film used can be appropriately adjusted according to the properties of the thermoplastic material. As for the preferable thermoplastic film 3 thickness range, 0.01-0.1 mm is suitable. In addition, the area of the prepreg interlayer adhesion can be controlled by the area of the holes 3a perforated in the thermoplastic film 3, and the preferred hole area ratio is 10 to 50% of the prepreg adhesion area.
도 3에는 구멍이 있는 열가소성필름(3)이 콤포지트 라미네이트의 각 프리프레그 층간에 삽입된 형태의 예가 도시된다. 삽입된 필름의 구멍부위에서는 라미네이트 성형시 프리프레그에 적용된 수지의 흐름이 원활하여 완벽한 접착이 이루어져 층간접착력이 유지되고 구멍이 천공되지 않은 부위에서는 간접적인 접착이 이루어져 국부적으로 층간 접착강도 조절이 가능하다.3 shows an example of the form in which the porous thermoplastic film 3 is inserted between each prepreg layer of the composite laminate. At the hole of the inserted film, the flow of resin applied to the prepreg is smooth during lamination, so perfect adhesion is achieved, and interlayer adhesion is maintained at the area where the hole is not perforated. .
상술한 바와 같은 본 발명에 의하면 종래에 비하여 간단하면서도 경제적인 방법으로 파괴인성이 향상된 콤포지트 라미네이트를 제조할 수 있다.According to the present invention as described above, a composite laminate having improved fracture toughness can be manufactured in a simple and economical manner as compared with the prior art.
<실시예 1><Example 1>
일방향 탄소섬유 프리프레그(2)인 유에스엔 125에이(USN 125A: 에스케이케미칼사 제품)를 각도 0°, 90°, 0°, 90°, 90°, 0°, 90°, 0°(0/90/0/90/90/0/90/0)의 적층순서로 프리프레그를 적층하고, 구멍(3a)이 천공된 두께 0.015㎜의 폴리에스터 필름(3)을 0/90 프리프레그 층간에 삽입하여 라미네이트를 성형하였다. USN 125A (USN 125A: SK Chemicals Co., Ltd.), a unidirectional carbon fiber prepreg (2), was used at angles of 0 °, 90 °, 0 °, 90 °, 90 °, 0 °, 90 °, 0 ° (0 / Prepreg is laminated in the stacking order of 90/0/90/90/0/90/0, and a polyester film 3 having a thickness of 0.015 mm having holes 3a perforated is inserted between 0/90 prepreg layers. The laminate was molded.
이때 일방향 탄소섬유 프리프레그(2)를 구성하는 일방향 탄소 섬유 토우(2b)는 인장강도가 380kgf/mm2, 인장탄성도가 24Ton/mm2이고 단위 토우당 필라멘트수가 12,000의 일본 토레이사 제품인 T-300 탄소섬유 토우이었으며, 층간에 삽입한 필름(3)의 전체 접착면적에 대한 구멍(3a)의 면적비율은 17%이었다.At this time, the unidirectional carbon fiber tow (2b) constituting the unidirectional carbon fiber prepreg (2b) is T-300 carbon manufactured by Toray Industries Co., Ltd., manufactured by Toray Industries, Ltd., with a tensile strength of 380 kgf / mm2, a tensile elasticity of 24 Ton / mm2, and a filament number of 12,000 per unit tow. It was a fiber tow, and the area ratio of the hole 3a to the total adhesive area of the film 3 inserted between the layers was 17%.
<실시예 2><Example 2>
구멍(3a)의 면적비율이 34%인 폴리에스터 필름(3)을 사용한 것을 제외하고는 실시예 1과 동일한 절차를 반복하였다. The same procedure as in Example 1 was repeated except that the polyester film 3 having an area ratio of the holes 3a was 34%.
<비교예 1>Comparative Example 1
구멍이 천공된 폴리에스터 필름(3)을 사용하지 않은 것을 제외하고는 실시예 1과 동일한 절차를 반복하였다. The same procedure as in Example 1 was repeated except that the perforated polyester film 3 was not used.
상기 실시예 1 내지 2 및 비교예 1에 의해 제조된 콤포지트 라미네이트에 대하여 인장강도, 인장탄성도, 파괴시편폭(fracture specimen width, W)에 대한 균열길이(crack length, a) 비율(a/W) 0.35에서 한쪽 균열 노치강도(notch strength) 및 한쪽 균열 인장파괴 인성(single edge notched tensile fracture toughness)을 측정하였다. 그 결과는 하기 표 1에 제시된다.The crack length (a) ratio (a / W) of the tensile strength, the tensile elasticity, and the fracture specimen width (W) of the composite laminates prepared according to Examples 1 to 2 and Comparative Example 1. At 0.35, single notch strength and single edge notched tensile fracture toughness were measured. The results are shown in Table 1 below.
상기 표 1로부터, 본 발명에 따른 실시예 1의 경우는 콤포지트 라미네이트 적층시 층간에 전체 접착면적에 대한 구멍의 비율이 17%인 폴리에스터 필름을 삽입함으로서 인장강도 및 인장탄성도는 각각 5%, 9% 감소하지만, 전체폭에 대한 균열길이 비율(a/W)이 0.35일 경우의 노치강도 및 파괴인성은 각각 14%, 59% 향상하는 효과를 얻었다. 또한 실시예 2의 경우에도 전체 접착면적에 대한 구멍의 비율이 34%인 폴리에스터 필름을 삽입함으로서 인장강도 및 인장탄성도는 각각 3.5%, 9% 감소하지만, 전체폭에 대한 균열길이 비율(a/W)이 0.35일 경우의 노치강도 및 파괴인성은 각각 8.5%, 43% 향상하는 효과를 얻었다.From Table 1, in the case of Example 1 according to the present invention, by inserting a polyester film having a ratio of 17% of the hole to the total adhesive area between layers when the composite laminate is laminated, tensile strength and tensile elasticity are 5%, Although 9% decreased, the notch strength and fracture toughness were improved by 14% and 59%, respectively, when the crack length ratio (a / W) was 0.35. In addition, in the case of Example 2, the tensile strength and the tensile elasticity are reduced by 3.5% and 9%, respectively, by inserting a polyester film having a ratio of 34% to the total adhesive area, but the crack length ratio to the total width (a / W) is 0.35, notch strength and fracture toughness are improved 8.5% and 43%, respectively.
이와 같이 본 발명에 따라 구멍이 있는 얇은 열가소성 필름을 프리프레그 층간에 삽입한 콤포지트 라미네이트는 균열 내재시 파괴인성이 향상 되어 콤포지트 라미네이트의 취성 파괴거동을 방지할 수 있어 높은 비강도 및 비탄성도 특성 및 우수한 파괴인성을 동시에 요구하는 용도, 예를 들어 볼트, 리벳 등의 기계적 결합이 요구되는 스포츠-레져 용품, 산업기계 부품 및 항공기 부품 등에 매우 효과적으로 적용할 수 있다.As described above, the composite laminate in which the thin thermoplastic film having a hole is inserted between the prepreg layers has improved fracture toughness when cracking is embedded, thereby preventing brittle fracture behavior of the composite laminate. It can be very effectively applied to applications requiring fracture toughness at the same time, for example, sports-leisure articles, industrial machine parts and aircraft parts requiring mechanical coupling such as bolts and rivets.
도 1은 본 발명의 콤포지트 라미네이트에 구성되는 일방향 프리프레그의 구조를 개략적으로 나타낸 단면도.1 is a cross-sectional view schematically showing the structure of a one-way prepreg composed of the composite laminate of the present invention.
도 2는 본 발명의 콤포지트 라미네이트에 구성되는 천공된 열가소성 필름의 구멍 형상 및 배열을 개략적으로 나타낸 평면도.FIG. 2 is a plan view schematically showing the hole shape and arrangement of the perforated thermoplastic film composed of the composite laminate of the present invention. FIG.
도 3은 본 발명의 바람직한 일 실시태양에 따라 도 1의 프리프레그들 사이에 도 2의 천공된 열가소성 필름이 적층구성된 콤포지트 라미네이트를 개략적으로 나타낸 단면도.3 is a schematic cross-sectional view of a composite laminate in which the perforated thermoplastic film of FIG. 2 is laminated between the prepregs of FIG. 1 in accordance with a preferred embodiment of the present invention.
※도면중 주요부분에 대한 부호의 설명※※ Explanation of symbols for main parts in drawing ※
1. 이형지1. Release paper
2. 일방향 프리프레그 2. One-way prepreg
2a. 열경화성 수지 2a. Thermosetting resin
2b. 섬유 토우 2b. Fiber tow
3. 열가소성 필름3. Thermoplastic film
3a. 구멍 3a. hole
Claims (3)
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| Application Number | Priority Date | Filing Date | Title |
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| KR1019980063181A KR100553399B1 (en) | 1998-12-31 | 1998-12-31 | Composite laminate |
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| Application Number | Priority Date | Filing Date | Title |
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| KR1019980063181A KR100553399B1 (en) | 1998-12-31 | 1998-12-31 | Composite laminate |
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| KR100553399B1 true KR100553399B1 (en) | 2006-06-07 |
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| KR20020086784A (en) * | 2001-05-11 | 2002-11-20 | 린통샨 | Method for forming carbon fiber layer |
| US20070202314A1 (en) * | 2004-04-30 | 2007-08-30 | Sambark Co., Ltd | Thermoplastic Compound Plate-Shaped Material, Method For Manufacturing And Articles Manufactured Using The Same |
| US11872773B2 (en) * | 2017-02-02 | 2024-01-16 | Toray Industries, Inc. | Method for producing fiber-reinforced plastic |
| CN112848545A (en) * | 2021-01-25 | 2021-05-28 | 北京理工大学 | Impact-resistant design and preparation method of composite laminated plate with embedded thermoplastic film |
Citations (7)
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|---|---|---|---|---|
| KR850006718A (en) * | 1984-03-30 | 1985-10-16 | 존 제이 헤이간 | Preparation of Fiber Resin Matrix Prepreg Fabric |
| KR900012988A (en) * | 1989-02-28 | 1990-09-03 | 미쓰비시레이온 가부시끼가이샤 | Prepreg (prepreg) and its manufacturing method |
| JPH03161331A (en) * | 1989-11-03 | 1991-07-11 | Phillips Petroleum Co | Thermoplastic complex reinforced with fiber in predetermined direction and its manufacture |
| JPH08127662A (en) * | 1994-10-28 | 1996-05-21 | Tonen Corp | Composite hybrid prepreg, composite resin pipe and molding method therefor |
| KR19980053417A (en) * | 1996-12-26 | 1998-09-25 | 김준웅 | Nonwoven Mat Prepreg and Manufacturing Method |
| KR19980053415A (en) * | 1996-12-26 | 1998-09-25 | 김준웅 | Non-woven mat scrim prepreg and its manufacturing method |
| KR19990066235A (en) * | 1998-01-23 | 1999-08-16 | 조민호 | Hybrid prepreg and its manufacturing method |
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1998
- 1998-12-31 KR KR1019980063181A patent/KR100553399B1/en not_active IP Right Cessation
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR850006718A (en) * | 1984-03-30 | 1985-10-16 | 존 제이 헤이간 | Preparation of Fiber Resin Matrix Prepreg Fabric |
| KR900012988A (en) * | 1989-02-28 | 1990-09-03 | 미쓰비시레이온 가부시끼가이샤 | Prepreg (prepreg) and its manufacturing method |
| JPH03161331A (en) * | 1989-11-03 | 1991-07-11 | Phillips Petroleum Co | Thermoplastic complex reinforced with fiber in predetermined direction and its manufacture |
| JPH08127662A (en) * | 1994-10-28 | 1996-05-21 | Tonen Corp | Composite hybrid prepreg, composite resin pipe and molding method therefor |
| KR19980053417A (en) * | 1996-12-26 | 1998-09-25 | 김준웅 | Nonwoven Mat Prepreg and Manufacturing Method |
| KR19980053415A (en) * | 1996-12-26 | 1998-09-25 | 김준웅 | Non-woven mat scrim prepreg and its manufacturing method |
| KR19990066235A (en) * | 1998-01-23 | 1999-08-16 | 조민호 | Hybrid prepreg and its manufacturing method |
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