WO2019074502A1 - Feuilles de fibres de carbone composites - Google Patents

Feuilles de fibres de carbone composites Download PDF

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Publication number
WO2019074502A1
WO2019074502A1 PCT/US2017/056158 US2017056158W WO2019074502A1 WO 2019074502 A1 WO2019074502 A1 WO 2019074502A1 US 2017056158 W US2017056158 W US 2017056158W WO 2019074502 A1 WO2019074502 A1 WO 2019074502A1
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WO
WIPO (PCT)
Prior art keywords
carbon fiber
fiber sheet
weave
cut
composite carbon
Prior art date
Application number
PCT/US2017/056158
Other languages
English (en)
Inventor
Yong Yong XU
Hao Ming Chen
Chao-Hung Lin
Feng Gu
Original Assignee
Hewlett-Packard Development Company, L.P.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hewlett-Packard Development Company, L.P. filed Critical Hewlett-Packard Development Company, L.P.
Priority to PCT/US2017/056158 priority Critical patent/WO2019074502A1/fr
Publication of WO2019074502A1 publication Critical patent/WO2019074502A1/fr

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Classifications

    • 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
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/024—Woven fabric
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • 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
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/20—All layers being fibrous or filamentary
    • 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
    • B32B2255/00—Coating on the layer surface
    • B32B2255/02—Coating on the layer surface on 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/732—Dimensional properties
    • 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
    • B32B2457/00—Electrical equipment

Definitions

  • Electronic devices such as laptops and mobile devices, include various thin parts, such as base covers.
  • Carbon fiber sheets are used for manufacturing such thin parts. Based on the number of filaments per fiber, carbon fiber sheets can be classified as 1K, 3K, 12K sheets and the like, where 1K means there are 1000 filaments per fiber, 3K means there are 3000 filaments per fiber, and 12K means there are 12000 filaments per fiber. Further, based on weave, carbon fiber sheets are classified, for example, as having unidirectional (UD) and multi-directional weave. In UD carbon fiber sheets, fibers run parallel to each other whereas in multi-directional carbon fiber sheets, fibers cross at an angle to each other. Multi-directional carbon fiber sheets may include bidirectional carbon fiber sheets, bidirectional carbon fiber sheets, and the like.
  • Fig. 1 illustrates an example method of preparing a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • FIG. 2 is an example schematic of a method of preparing a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • FIG. 3 illustrates a cross-section of a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • Fig. 4 is an example schematic of a method of preparing a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • UD carbon fiber sheets having unidirectional (UD) weave, hereinafter referred to as UD carbon fiber sheets, are used for manufacturing the thin parts.
  • UD carbon fiber sheets have a lower strength compared to carbon fiber sheets with multi-directional weave. Some regions of the thin parts may require higher strength than that provided by the UD carbon fiber sheets. Multiple layers of UD carbon fiber sheets can be used to fabricate such regions. However, this increases the weight and cost of the manufactured thin part.
  • multi-directional (MD) carbon fiber sheets may be used to manufacture the thin parts.
  • MD carbon fiber sheets are more expensive than UD carbon fiber sheet.
  • UD carbon fiber sheets have better machinability than MD carbon fiber sheets.
  • the present subject matter relates to methods of preparing composite carbon fiber sheets.
  • the composite carbon fiber sheets obtained are cost-effective, machinable, and have a high strength.
  • a cut area is created in a first carbon fiber sheet of a first weave.
  • a cutout is created from a second carbon fiber sheet of a second weave. The cutout is combined with the first carbon fiber sheet in the cut area to obtain the composite carbon fiber sheet.
  • the first weave is a UD weave and the second weave is a multidirectional (MD) weave.
  • the cutout may include a single layer or multiple layers stacked together.
  • the cutout and the first carbon fiber sheet are combined in the cut area by thermally fusing the cutout in the cut area of the first carbon fiber sheet.
  • the composite carbon fiber sheet may also be surface treated to cover the marks and irregularities that may be formed due to the thermal fusion process.
  • the present subject matter provides a composite carbon fiber sheet with localized increase in strength. Therefore, the composite carbon fiber sheet can be used to fabricate thin parts that require higher strength in certain regions without substantially increasing weight, cost, or thickness, while also not affecting machinability. For example, the composite carbon fiber sheet can be used to fabricate laptop base covers with a higher strength in a fan region by placing the multi-dimensional carbon fiber sheet cutout in that region.
  • Example implementations of the present subject matter are described with regard to personal computers (PCs) and laptop computers. Although not described, it will be understood that the implementations of the present subject matter can be used with other types of electronic devices with thin parts as well, such as television, tablet, smartphone device, and the like.
  • Fig. 1 illustrates an example method 100 of preparing a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • the method 100 includes creating a cut area in a first carbon fiber sheet of a first weave at block 102.
  • the first weave is a unidirectional (UD) weave.
  • the cut area may be created in the first carbon fiber sheet, for example, by stamping or punching.
  • the cut area may be created by using a Computer Numeric Control (CNC) punching press. Dimensions, such as size and shape, of the cut area depends on the region in which higher strength is to be provided.
  • CNC Computer Numeric Control
  • the method 100 comprises creating a cutout from a second carbon fiber sheet of a second weave.
  • the second weave is a multi-directional (MD) weave.
  • the second carbon fiber sheet comprises 3K carbon fibers.
  • the second weave may be a 3K bidirectional weave.
  • Creating the cutout can include stamping, punching, cutting, or trimming the second carbon fiber sheet to obtain the cutout.
  • the cutout may be a single layer whose dimensions are substantially similar to the dimensions of the cut area.
  • the cutout comprises multiple layers of the second carbon fiber sheet.
  • the method 100 comprises combining the cutout with the first carbon fiber sheet in the cut area to obtain the composite carbon fiber sheet.
  • the combining comprises thermally fusing the cutout in the cut area to obtain the composite carbon fiber sheet.
  • the cutout and the first carbon fiber sheet may be subjected to high temperature and pressure after placing the cutout in the cut area.
  • the combining is performed at a temperature in a range of about 230 °C - 250 °C and a pressure in a range of about 90 - 110 Ton * (T) for a cycle time of about 240 - 300 seconds.
  • T Ton *
  • a composite carbon fiber sheet having localized higher strength provided by the cutouts in the cut area can be formed.
  • the composite carbon fiber sheet can be surface treated for aesthetic purposes, such as masking any marks or irregularities formed due to thermal fusion.
  • FIG. 2 is an example schematic of a method of preparing a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • Schematic 200(a) depicts a cut area 202 in a first carbon fiber sheet 204 of a first weave.
  • the first weave is a unidirectional weave.
  • schematic 200(a) depicts a square shaped cut area 202, other shapes can also be created as will be understood.
  • schematic 200(a) depicts a single cut area 202, multiple cut areas can be created as will be understood.
  • Schematic 200(b) depicts a cross-sectional view of the first carbon fiber sheet 204 as viewed along line A-A.
  • Schematic 200(c) depicts a cross-section view of a cutout 206 created from a second carbon fiber sheet of a second weave.
  • the second weave is a multi-directional weave.
  • the multi-directional weave can be a 3K bidirectional weave.
  • other multi-directional weaves may be used in other implementations.
  • dimensions of the cutout 206 are substantially similar to that of the cut area 202.
  • the cutout 206 may be suitably cut or trimmed so that the dimensions are substantially similar to that of the cut area 202.
  • dimensions of the cutout 206 can be slightly bigger than the cut area 202 to ensure form fit of the cutout 206 in the cut area 202 after combining.
  • Schematic 200(d) depicts a cross-section view of the cutout 206 placed in the cut area 202 for combining.
  • Combining of the cut area 202 in the cutout 206 includes thermally fusing the cutout 206 in the cut area 202 to obtain a composite carbon fiber sheet 208 as depicted in schematic 200(e).
  • Thermally fusing the cutout 206 in the cut area 202 is achieved by subjecting the cutout 206 and the first carbon fiber sheet 204 to high temperature and pressure. The high temperature causes the cutout 206 and the first carbon fiber sheet 204 to form molten portions. The molten portions fuse to form the composite carbon fiber sheet 208 under high pressure.
  • Schematic 200(e) depicts the composite carbon fiber sheet 208 which comprises the first carbon fiber sheet 204 of the first weave and the cutout 206 of the second carbon fiber sheet of the second weave.
  • Schematic 200(f) depicts a cross-sectional view of the composite carbon fiber sheet 208 along line B-B of schematic 200(e). Combining the cutout 206 within the cut area 202 provides localized strength, without increasing the thickness of the first carbon fiber sheet 204. Further, the obtained composite carbon fiber sheet 208 can have differential strength as compared to the first carbon fiber sheet 204 without affecting properties of the first carbon fiber sheet 204. In addition, since the composite carbon fiber sheet 208 substantially comprises the first carbon fiber sheet 204, overall machinability remains unaffected. The obtained composite carbon fiber 208 can also be surface treated to improve its aesthetic appearance.
  • Fig. 2 has been explained with respect to the first weave being a unidirectional weave and the second weave being a multi-directional weave, other weaves and combinations are possible as will be understood.
  • the first carbon fiber sheet can be of lower strength than the second carbon fiber sheet.
  • different cutouts 206 of different weaves may be thermally fused with different cut areas 202 depending on the strength to be provided in that region.
  • Fig. 3 illustrates a cross-section of a composite carbon fiber sheet 300, according to one example of the principles described herein.
  • the composite carbon fiber sheet 300 comprises a first part 302 made of the first carbon fiber sheet 204 of a first weave and a second part 304 made of the second carbon fiber sheet 202 of a second weave.
  • the first part 302 and the second part 304 are thermally fused to each other.
  • the composite carbon fiber sheet 300 also comprises a surface treatment layer 306 over at least a portion of the first part 302 and the second part 304 on at least one side of the composite carbon fiber sheet 300.
  • the surface treatment layer 306 can be formed from one of painting, dyeing, printing, and combinations thereof.
  • the surface treatment layer 306 is provided over an entire surface area of the fused first part 302 and second part 304.
  • the surface treatment layer 306 may be provided on thermally fused portions 310.
  • the surface treatment layer 306 helps in masking marks or scars or other irregularities formed due to thermal fusing on the composite carbon fiber sheet 300.
  • the surface treatment layer 306 can be provided as a pattern formed on the composite carbon fiber sheet 300.
  • Fig. 3 depicts the surface treatment layer 306 as a single layer, a plurality of layers can be provided in different portions of the composite carbon fiber sheet 300 as will be understood.
  • Fig. 4 illustrates an example schematic of a method 400 of preparing a composite carbon fiber sheet, according to an example implementation of the present subject matter.
  • the method 400 comprises creating a cut area in a first carbon fiber sheet of a first weave.
  • Schematic 400(a) depicts cut areas 404a and 404b created in a first carbon fiber sheet 402 of a first weave.
  • schematic 400(a) depicts two cut areas 404a and 404b, more than two cut areas can also be created.
  • schematic 400(a) depicts square-shaped cut areas 404a and 404b, other shapes are possible as will be understood.
  • Schematic 400(b) depicts a cross-sectional view of the first carbon fiber sheet 402 as viewed along line C-C of schematic 400(a).
  • the method 400 comprises creating a plurality of cut portions from a second carbon fiber sheet of a second weave.
  • Schematic 400(c) depicts the plurality of cut portions 406.
  • the plurality of cut portions 406 comprises a first set 406a of cut portions 406 and a second set 406b of cut portions 406.
  • an area of a cut portion 406 of the second set 406b is less than an area of a cut portion 406 of the first set 406a.
  • the first set 406a may comprise cut portions 406 of different weaves.
  • the cut portions 406 in the first set 406a and the second set 406b may be of different weaves.
  • the method 400 comprises stacking the plurality of cut portions 406 in the cut area.
  • Schematic 400(d) depicts the plurality of cut portions 406 stacked in the cut areas 404a and 404b.
  • stacking comprises placing the cut portions 406 of the second set 406b between the cut portions 406 of the first set 406a.
  • a gap 407 is formed between the cut portions of the second set 406b and the cut area 404. The gap 407 allows more uniform thermal fusion by providing space for melting and settling of the cut portions 406 in the cut area 404.
  • the number of cut portions 406 to be stacked in the cut area 404 depends on a thickness of the first carbon fiber sheet 402 and a thickness of each of the plurality of the cut portions 406.
  • the first carbon fiber sheet 402 has a thickness in a range of about 0.6 - 0.8 millimeter (mm) and the second carbon fiber sheet has a thickness in a range of about 0.2 - 0.3 mm.
  • the first carbon fiber sheet 402 has a thickness of 0.6 mm and the second carbon fiber sheet has a thickness of 0.2mm
  • three layers of cut portions 406 can be stacked in the cut area 404.
  • the plurality of cut portions 406 are stacked such that a thickness of a stack obtained is substantially equal to the thickness of the cut area 404.
  • the method 400 comprises combining the plurality of cut portions 406 with the first carbon fiber sheet 402 in the cut area 404 to obtain the composite carbon fiber sheet 408 as shown in schematic 400(e).
  • combining the plurality of cut portions 406 with the first carbon fiber sheet 402 is done by thermally fusing them.
  • thermally fusing comprises subjecting the plurality of cut portions 406 and the first carbon fiber sheet to high temperature and high pressure which causes fusion of the plurality of cut portions 406 and the first carbon fiber sheet 402.
  • the method 400 further comprises surface treating the composite carbon fiber sheet.
  • Schematic 400(f) depicts a cross-sectional view of the composite carbon fiber sheet 408 comprising a surface treatment layer 410.
  • the surface treating is performed over the entire surface area of the composite carbon fiber sheet 408.
  • the surface treating may be performed on thermally fused portions 412.
  • Surface treating helps in covering marks or scars formed on the composite carbon fiber sheet 208 due to the thermal fusing.
  • Surface treating can be performed by one of painting, dyeing, printing, and combinations thereof.
  • the composite carbon fiber sheet obtained using the method of the present subject has localized increase in strength in the cut area comprising the cutout. Further, cost of the composite carbon fiber sheet does not substantially increase in comparison to the first carbon fiber sheet as only certain regions have been replaced by the cutouts or cut portions of the second carbon fiber sheet.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Reinforced Plastic Materials (AREA)
  • Woven Fabrics (AREA)
  • Laminated Bodies (AREA)

Abstract

La présente invention concerne des feuilles de fibres de carbone composites et leurs procédés de préparation. La feuille de fibres de carbone composite contient une première feuille de fibres de carbone d'une première armure et une seconde feuille de fibres de carbone d'une seconde armure. Une zone de coupe est créée dans une première feuille de fibres de carbone d'une première armure. Une découpe est créée à partir d'une seconde feuille de fibres de carbone d'une seconde armure. La découpe est combinée à la première feuille de fibres de carbone dans la zone de coupe de façon à obtenir la feuille de fibres de carbone composite.
PCT/US2017/056158 2017-10-11 2017-10-11 Feuilles de fibres de carbone composites WO2019074502A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2017/056158 WO2019074502A1 (fr) 2017-10-11 2017-10-11 Feuilles de fibres de carbone composites

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2017/056158 WO2019074502A1 (fr) 2017-10-11 2017-10-11 Feuilles de fibres de carbone composites

Publications (1)

Publication Number Publication Date
WO2019074502A1 true WO2019074502A1 (fr) 2019-04-18

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5279892A (en) * 1992-06-26 1994-01-18 General Electric Company Composite airfoil with woven insert
EA200802202A1 (ru) * 2006-04-26 2009-02-27 ДСМ АйПи АССЕТС Б. В. Лист многослойного материала и способ его получения
RU2372423C2 (ru) * 2008-01-14 2009-11-10 Общество С Ограниченной Ответственностью "Завод Углеродных И Композиционных Материалов" Способ получения высокомодульного углеродного волокна

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5279892A (en) * 1992-06-26 1994-01-18 General Electric Company Composite airfoil with woven insert
EA200802202A1 (ru) * 2006-04-26 2009-02-27 ДСМ АйПи АССЕТС Б. В. Лист многослойного материала и способ его получения
RU2372423C2 (ru) * 2008-01-14 2009-11-10 Общество С Ограниченной Ответственностью "Завод Углеродных И Композиционных Материалов" Способ получения высокомодульного углеродного волокна

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
VASHUKOV YU. A, TECHNOLOGY OF ROCKET AND AEROSPACE STRUCTURES FROM COMPOSITE MATERIALS, 2012, pages 51 *

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