US3819461A - Unidirectional, high modulus knitted fabrics - Google Patents

Unidirectional, high modulus knitted fabrics Download PDF

Info

Publication number
US3819461A
US3819461A US18767471A US3819461A US 3819461 A US3819461 A US 3819461A US 18767471 A US18767471 A US 18767471A US 3819461 A US3819461 A US 3819461A
Authority
US
Grant status
Grant
Patent type
Prior art keywords
modulus
high
graphite
yarns
strength
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
Inventor
R Saffadi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Stevens & Co Inc J P
Original Assignee
Stevens & Co Inc J 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
Grant date

Links

Images

Classifications

    • DTEXTILES; PAPER
    • D04BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04HMAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
    • D04H3/00Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
    • D04H3/08Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating
    • D04H3/10Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with bonds between yarns or filaments made mechanically
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
    • B29KINDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS
    • B29K2307/00Use of elements other than metals as reinforcement
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S428/00Stock material or miscellaneous articles
    • Y10S428/902High modulus filament or fiber
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24033Structurally defined web or sheet [e.g., overall dimension, etc.] including stitching and discrete fastener[s], coating or bond
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24058Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
    • Y10T428/24074Strand or strand-portions
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24058Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
    • Y10T428/24074Strand or strand-portions
    • Y10T428/24091Strand or strand-portions with additional layer[s]
    • Y10T428/24099On each side of strands or strand-portions
    • Y10T428/24107On each side of strands or strand-portions including mechanically interengaged strands, strand-portions or strand-like strips
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24058Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
    • Y10T428/24074Strand or strand-portions
    • Y10T428/24116Oblique to direction of web
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T442/00Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
    • Y10T442/40Knit fabric [i.e., knit strand or strip material]
    • Y10T442/413Including an elastic strand

Abstract

Unidirectional reinforcing fabric for resin laminates and the laminates including it, in which parallel yarns of fibers of very high modulus of elasticity, in excess of 8 million pounds per square inch, such as high modulus graphite yarn, with or without some glass fiber yarn, are maintained parallel and uncrimped by knitting them together using a fine, flexible knitting yarn. None of the knitting stitches penetrate any of the high modulus yarns. The wales are very widely spaced relative to high modulus yarn cross-section, in excess of two and one-half times with the coarsest material. The stitches are chain stitches, and the very brittle high modulus graphite is not bent or crimped and is maintained parallel by the chain stitches of fine, flexible knitting yarn.

Description

United States Patent [191 Saffadi 1 UNIDIRECTIONAL, HIGH MODULUS KNITTED FABRICS [75] Inventor: Richard R. Saffadi, Ridgefield, NJ.

[73] Assignee: J. P. Stevens & Co., Inc., New York,

[22] Filed: Oct. 8, 1971 [21] Appl. No.: 187,674

Related US. Application Data I [63] Continuation-in-part of Ser. No. 851,408, Aug. 19,

1969, abandoned.

[52] US. Cl 161/58, 8/1162, 66/193, 66/202, 161/89, 161/91, 161/182, 423/447, 423/448 [51] Int. Cl B32b 5/12 [58] Field of Search 161/59, 57, 58, 89, 50, 161/91; 66/193, 202; 423/447, 448; 8/116 R, 1 16.2

[5 6] References Cited UNITED STATES PATENTS 3,105,372 10/1963 Whitehead 66/193 3,235,323 2/1966 Peters 8/116.2 3,283,389 11/1966 Nisbet et a1..... 161/89 3,367,812 2/1968 Watts 423/447 3,462,340 8/1969 Hough 161/59 3,466.219 9/1969 Schwartz 161/57 3,484,183 12/1969 Dickson et a1. 8/116 R 3,527,564 9/1970 Moore et a1. 423/447 June 25, 1974 3,541,582 11/1970 Johnson et a1 423/447 3,556,712 1/1971 Yoneshige et a1. U 423/447 3,637,446 l/1972 Elliott 156/69 OTHER PUBLICATIONS Webber, Modern Textiles Magazine, Vol. 47, 5/66, pp. 72-75.

[57] ABSTRACT Unidirectional reinforcing fabric for resin laminates and the laminates including it, in which parallel yarns of fibers of very high modulus of elasticity, in excess of 8 million pounds per square inch, such as high modulus graphite yarn, with or without some glass fiber yarn, are maintained parallel and uncrimped by knitting them together using a fine, flexible knitting yarn. None of the knitting stitches penetrate any of the high modulus yarns. The wales are very widely spaced relative to high modulus yarn cross-section, in excess of two and one-half times with the coarsest material. The stitches are chain stitches, and the very brittle high modulus graphite is not bent or crimped and is maintained parallel by the chain stitches of fine, flexible knitting yarn.

4 Claims, 6 Drawing Figures PATENTEDJUH25|9Y4 3,819,461

SHEEI 1 OF 3 PR/OR A R T PRIOR ART INVENTOR.

R/CHARD R. SAFFAD/ BY M/W/LM Q ATTORNEY PATENTEU 3, 8 19 .461

sum 2 ur s I INVENTOR. RICHARD R. .SAFFAD/ A TTORNEY PATENTEDJUNZSIEIH SHEET 3 [1F 3 UNIDIRECTIONAL, HIGH MODULUS KNITTED FABRICS RELATED APPLICATION This application is a continuation-in-part of my copending application Ser. No. 851,408, filed Aug. 19, 1969, and now abandoned.

BACKGROUND OF THE INVENTION Resin laminates have been reinforced with fibers and fabrics, especially glass fibers in the form of woven fabric, mats and the like. Glass fiber reinforced laminates have been extensively used as a covering for boats, molding of boat hulls and other articles The glass fibers have a fairly high modulus of elasticity. Throughout the present specification the term modulus of elasticity will be used for Youngs modulus, i.e., the stress required to produce unit strain. This is usually measured in pounds per square inch or dynes per square centimeter. For simplicity Youngs modulus of elasticity will be briefly referred to as modulus throughout the present specification. This property should not be confused with tensile strength. For example, nylon fibers or filaments have an extraordinarily high tensile strength; their modulus, however, is very low, much less than a million pounds, because they stretch under stress. Certain other materials, such as certain elastomers, also have high tensile strength but negligible modulus. The best non-metallic high modulus fibers are those of high modulus graphite, produced by graphitizing highly crystalline stretched cellulosic fibers, such as rayon. Some of these have moduli in excess of 50 million pounds psi. However, they are extremely brittle. They are usually referred to in the art as high modulus graphite. It should be understood that they are a particular form of graphite. Many graphites have very low modulus of elasticity and are quite flexible and pliable.

In recent years, starting about a decade ago, a demand arose for reinforcing fabrics for laminates of very high modulus for turbine blades, helicopter rotors and the like where extremely high modulus in a single direction is essential. Even the strongest woven fabrics from glass fiber threads lose modulus because the threads cross over and under each other during weaving and are crimped or bent on a short radius. Even with fine glass fibers strength losses in the laminate of 25 percent and more may result.

An attempt was made to improve the strength of reinforcing fabrics by the weave, described in the Genin US. Pat. No. 2,893,442. This patent describes laying high modulus thread, such as glass fibers, across each other without crimping them as would be the case if the fabric were woven in the ordinary manner. The fabric was held together loosely by weaving with much thinner and more flexible yarn. Crimping of the glass threads was reduced, and the Genin fabric therefore represented an improvement, with less loss of modulus, but crimping was not eliminated as the binding warp and weft threads caused some crimp and so loss in strength still took place. It is impossible to weave even with flexible binding threads without producing some crimp, and the Genin fabric also paid a price for its reduced crimping by the fact that the threads can readily slide out from the binding threads, they are not woven over each other, and raveling at the edges can take place. For some uses this is not a serious objection, for example in reinforcing fabrics for boat hulls and the like. Genin fabrics, of course, are bidirectional and so are the reinforced laminates produced therefrom.

As has been stated, high modulus graphite fibers have been produced with moduli of 50 million to,6() million pounds, whereas the maximum for glass does not exceed 15 million pounds. High modulus graphite threads are extremely brittle and cannot be woven practically as they break.

For certain important uses, such as airplane propellers, blades for jet engine fans or compressors, helicopter rotors and the like, laminates reinforced with unidirectional or substantially unidirectional, extremely high modulus materials are needed. For these purposes reinforcing fabrics with unbroken, substantially parallel, high modulus fibers are needed.

Excellent laminates have been prepared by laying on a flat surface parallel fibers or yarns of high modulus graphite. The surfaces can be quite long, and the exactly parallel bands or stripes of high modulus graphite yarn have to be laid by precisely controlled, very expensive machinery, which lays a stripe, then moves over and lays another stripe, until finally the desired width has been achieved. These parallel strands are yarns treated with a thermosetting resin, which is coated onto the yarn in liquid form. This resin is permitted to set slightly to the beginning of the B stage and is slightly tacky though not stickyor so soft that the yarns can be moved out or parallelism. The tapes of coated yarns are then refrigerated because they have to be keptquite cold to slow down the further setting of the resin, because if it once gets to the C" stage the resulting tapes cannot be practically molded to form strong laminates. Even when kept refrigerated the tapes do not have an indefinite storage life, but can be kept for many months. Transportation of the refrigerated tapes also presents a serious problem because, of course, they must be transported in refrigerated containers or vehicles. This presents a further problem, involving both the expense of the carefully refrigerated transport and, what is much moree important, in case of an accident, if the temperature rises tapes are spoiled, and with the extremely high price of high modulus graphite this can result in a serious monetary loss. Of course the laminater receiving the tapes coated with the B stage resin must keep them refrigerated until they are molded or otherwise formed into the final laminates. Once a laminate, such as a blade for a jet engine fan or airplane propeller or helicopter rotor, has been molded and the resin transformed into the C stage, i.e., cured, the resulting products are of very high quality: the high modulus graphite yarns are not broken and adhesion is excellent. This result in a very high interlaminar shear strength. which is of course essential for finalproducts of maximum strength. In other words, when resin preimpregnated high modulus graphite yarns or tapes are laid, the resulting product is of excellent quality, the only drawback being high cost of machines of extreme precision for laying the yarns parallel and the costs and problems of refrigerated storage and transportation together with the somewhat limited storage life under refrigeration, although this storage life is adequate for most uses.

For certain other forms, such as curved fan or propeller blanks, some problems arise. It is not practical to cut the tapes to exact form and it is difficult to produce blanks, such as those for propellers and certain fan blades, with taper in thickness and particularly if they are curved. Thus it is common to make up blanks of laminates which are somewhat squared off and in general cannot be readily produced in a feathered form to thin edges or ends. These blanks, which have excellent unidirectional strength in the direction of the high modulus graphite fibers, are then machined to the final precise curved form. The final product is of the highest quality, but the machining adds very substantially to the cost of the final product, both from the standpoint of the additional cost of the added machining step and also from the fact that if a blank is made which is thicker in some places than needed, the machining off of course uses up very expensive high modulus graphite. All in all the refrigerated B stage resin impregnated tapes can be used to produce final products of the highest quality, but only at a markedly increased cost. In the trade these tapes of high modulus graphite yarns coated or preimpregnated with thermosetting resin hich is subsequently slightly B staged are usually referred to as prepregged tapes. There thus remains a need for the same high quality material at lower costs and with still longer or substantially indefinite storage life.

The requirement for parallelism and straightness is an important one because sinuous curved yarns do not produce extremely high strength in laminates because under stress in the laminate the curved threads can stretch, and so, even though individual yarns or threads may have fairly high moduli of elasticity, for example glass fibers, the laminate itself is weak. Such fabrics with sinuous threads are described, for example, in the Nisbet et al. US. Pat. No. 3,256,130. Very beautiful fabrics can be produced, but for the special use of extreme high tension and high modulus in a particular direction, such fabrics are not of value as reinforcing fabllCS.

lt should be emphasized that the extremely high modulus material, such as high modulus graphite, is not necessarily of high modulus merely because of its chemical nature. Many graphites, in fact most, are soft, flexible and pliable and have very low modulus. Such fabrics are described in the Peters US. Pat. No. 3,235,323. Fabrics which are made by heat treating nitrogenous salt impregnated rayon have high melting points, are very pliable, and can be used for high temperature filters or, in the case of tapes made therefrom, fireproof tapes, which are useful for many purposes. The material is not a graphite as it contains large amounts of oxygen, the carbon content not exceeding about 61%. It has also been proposed to further carbonize these fabrics or fibers, and when this is done, electrically conductive materials are produced, but, as Peters states, they are not graphitized carbon and they are of low modulus through pliant, strong and very flexible. These products are not practically useful for the specialized reinforcements that require maximum laminate strength in a single direction as has been described above. They bear no relation to the extremely high modulus graphite produced from oriented crystalline fibers and they do not have extreme brittleness, which is, unfortunately, a characteristic of high modulus graphite.

SUMMARY OF THE INVENTION The present invention produces unidirectional high modulus laminate reinforcing fabric of maximum modulus with substantially parallel fibers, for example of high modulus graphite fibers or yarns. It is possible to produce reinforcing fabric, not prepregged tapes, which can be made into laminates of as high quality. The fabrics have indefinite storage life in the unrefrigerated state and without risk or breakage of the high modulus graphite yarn or departure from parallelism, the importance of which has been brought out in the discussion of the background of the invention. Cost can be markedly lower as expensive machines for laying exactly parallel yarns are no longer needed, the cost of refrigeration, refrigerated transport, and the risk of losses if refrigeration breaks down are also eliminated. The present invention, therefore, permits the production of final laminate products of the highest quality at a very substantial saving in operations and in costs.

In the present invention the reinforcing fabric is produced by knitting on a warp knit knitting machine fabrics with insertion of wefts. The wefts are of high modulus graphite yarns which are held in exact parallelism by the knit stitches, which are preferably in the major amount chain stitches. The warps can be of soft textile yarns, such as nylon, polyester, cellulosics and the like, which are preferably of very much finer denier than the inserted high modulus graphite weft. The chain knit stitches surround the high modulus graphite yarn inserted weft without crimping or otherwise bending the yarns to the point where breakage can occasionally occur. The resulting fabric, of course, has an indefinite storage life in a completely unrefrigerated state. Transportation problems are eliminated and the cost of final laminate products is markedly reduced and number of operations from raw material to final product also reduced, without reducing quality of final laminate.

The wales of stitches must be spaced quite widely so that relatively long spaces of unknit fabrics are present so that finally when resin laminates are formed there is a large surface extent of the high modulus graphite in contact with the thermosetting resin and in contact with graphite yarn surfaces of the other fabric layers to form the final laminate. This requires certain minimum spacings which can best be expressed in terms of spacing of wales as compared to high modulus graphite inserted weft yarns cross-section. Even for the coarsest inserted high modulus grahite weft yarn, for example one which may contain as many as 10,000 graphite fibers, the ratio of spacing to cross-section should be at least about 2.5, and in such a case the wales are spaced about four to the inch of weft length. While the absolute spacing lower limit is not critical, it should not be much less than one-quarter inch regardless of the cross section of the inserted high modulus graphite weft yarns. There is no theoretical upper limit on wale spacing as far as resin adhesion and hence interlaminar shear strength of the final laminate is concerned. The upper limit is dictated only by the fact that there must be wales sufficiently near together so that the fabric produced does not permit significant departure of parallelism of the high modulus graphite yarns. This practical upper limit is not at all critical, which is an advantage of the present invention. The minimum relative spacing of wales to cross-section of high modulus graphite inserted wefts occurs with the coarsest wefts. With finer wefts the ratio may be four, eight, or considerably more times the cross-section of the inserted wefts.

At this point a very brief discussion of desirable properties of high unidirectional strength and modulus laminates is appropriate. The principal field of use is in rapidly rotating elements, such as air compressor blades in 6 strength results. A h igh idieflminifshar strength is necessary because the final laminates are made up of a large number of lamina and these lamina should not slide one over the other. Preferably all or substantially reduced and, particularly when final curing of the resin results in decomposition of certain warp yarns, significandy le r q aqhesieeanttbenqe, srheiretsde jet engines, airplane propellers, helicopter rotors and 5 all of the wales should be of chain stitches. However, the like. The stresses to which these final products are an occasional pair of wales may be formed with occaput depend on their density, and so modulus and tensile sional lock stitches without seriously compromising instrength alone are not the ultimate measure. Specific terlaminar shear strength. The vast majority of the tensile strength and specific modulus, i e tensile wales, however, should be chain stitched as significant strength or modulus divided by density, are the impordeterioration in interlaminar strength results if more tant factors. This can be well brought out for as a numthan lock stitch wales are present. As chain stitch ber of materials in the following table, which compares knitting is at least as conomical or more economical two well known types of high modulus and high than lock stitch knitting, there is no economic reason strength graphite with other materials. Type 1 is maxifor departing significantly from the preferred all chain mum modulus with good ultimate tensile strength and I5 stitch form of fabric. As has been pointed Out bo Type 2 maximum ultimate tensile strength with adecompatibility of metals, such as steel, with laminating quate modulus. The comparisons appear in the followresin is so poor that steel reinforced laminates are pracing Table l, in which both tensile strength and Youngs tically useless even though their combination of spee ei. a e expressed in milliqns P i s fismqvlqeaitpe tlatsisflgtensth inptsieat x.

TABLE 1 Ultimate Specific Youngs Tensile Specific Tensile Density Modulus Strength Modulus Strength lbs lbs per lbs per Material in X lo in X 10 per in in X l0 in 1O3 Graphite Type I High Modulus 760-900 2.84.l 0.072 55-65 200-300 T 11 Hi Streggth 560-7l0 5.67.l 0.063 3545 350-450 teel 104 1.4 2.1 0.280 400400 (drawn wire) E-Glass 104 2.7 0.092 10 250 S-Glass 104 5.5 0.092 10 500 Boron 530 5.3 0.095 50 7 500 Aluminum 102 0.72 0.097 10 70 Beryllium 470 2.3 0.066 150 Note: 1. Specific modulus is defined as: Young's Modulus/Density 2. Aluminum and beryllium figures are for massive material 3. Gauge length for tests on Morganite Fibre 5cm 7 V 7 if H M W M It will be noted that the higher specific modulus is obinferior to some glasses. tained with the high modulus graphites, the only other Another advantageous property of laminates reinmaterial even approaching them being boron. Specific forced with fabric of the present invention is that for modulus is much higher than either steel, glass or aluequal weight they show superior beam stiffness. In minum; and even in the case of beryllium, which has a 45 other words, it reduces the weight of the final part fairly high specific modulus, the specific tensile when compared to the weight of a part manufactured strength is considerably lower. Most of the metals show from a metal to produce equivalent specific modulus very poor adhesion to the laminating resins, whereas and/or specific strength as that of the high modulus graphite has a high adhesion. Glass can be coated to graphite laminate. This, of course, is a very desirable produce a fair adhesion, but still not as good as graphcharacteristic and can be of great importance in the ite. However, glass when properly coated can be used, case of airplane structures, propeller and helicopter roparticularly in small quantities in admixture with intors, and of course can also reduce vibration in high serted high modulus graphite wefts, and for certain speed rotating compressor blades. MM products g i T i j wggi' z Another advantage of the reinforcing fabrics of the g gequlre fi u l l present invention is that it is possible to cut or stamp er aspecis o fi f are e out desired shapes of the fabric before lamination. This mate Propemes 0 g a requlrje is of importance where curved or compound shapes of t 'f i fi f i g ers s final products, such as an airplane propeller or fan g p Y izi t 6 cos g $5. blade, are desired. The wastage of expensive high mod- 0 f l l mslgm compare to t at 0 ulus graphite is less than if thicker block laminates have f 6 3? d b k h f h to be shaped by machining, and of course the higher 1 a i i l t 6 costs of machining are eliminated. This is another inwales mtlwlt 9 W gi stance where the present invention permits producing tog/a a heslon O e resm m fi ll i high quality products with reduction in required opera- -su ers ecauset e areao contact w1t t e grap 1te 1s 5 tions for producinglhg final product It is an advantage of the present invention that the strength of the reinforcing fabric is for all practical purposes independent of the strength of the relatively fine denier warp yarns and the wide spacing of chain knit wales. Essentially the knitting is only for the purpose of holding the high modulus graphite wefts parallel during lamination. After resin preimpregnation and once the resin has begun to set, the knitted wales could decompose completely without any significant effect on the strength of the final laminate. Thus warps may be of materials which-are destroyed or seriously weakened at the temperature of final lamination.

The important distinction between modulus of elasticity and tensile strength is another facet of the problem of adhesion discussed above. Even if there is good adhesion, if reinforcing fibers, no matter how high their tensile strength, have a low modulus of elasticity, under extreme stress they stretch, but the resins do not and so there is a tendency for the resins to break loose from their reinforcing material. The high modulus material, however, does not stretch and therefore makes for greater overall laminate strength. The difference between tensile strength and modulus can be clearly brought out by considering the Whitehead US. Pat. No. 3,l05,372. This patent deals with body armor, in which nylon threads, or in some cases high tenacity rayon threads, are knitted on a warp knit machine. The nylon threads, although of great tensile strength, have low modulus of elasticity. This is, of course, exactly what Whitehead wanted. The function of a body armor is to absorb the energy of a bullet. This requires that the fabric give, so that the bullet is slowed down over a finite distance. For this purpose nylon is ideal. It is very strong, it stretches, i.e., it is elastic but has a low modulus, and the bullet, therefore, is slowed up and in many cases will not continue its path. High modulus graphite is exactly the opposite. If it were attempted to make a body armor, it is so brittle that it would break and be of little use. It is of interest to note that the Whitehead patent has knitted stitches which go through the nylon and it is also knit with lock stitches. All of these increase the strength for a reasonable stretch when a bullet hits. ln propellers or turbine blades, however, these characteristics result quickly in failure. Any penetration of the high modulus graphite weft by the knitted stitch, and of course the needle forming it, results in breaking the graphite yarn.

While the present invention produces fabrics which have enormous modulus in a single direction, and this is the vital matter for the laminates which have to primarily resist great forces in a single direction, such as high centrifugal forces, it is sometimes desirable to have multiple laminates in which the reinforcing fabrics, while having their high modulus threads parallel in any particular layer, may be at a small angle, for example up to as much as 30% from one reinforcing layer to another. This gives somewhat increased shear strength without significantly reducing the primary strength in the single direction, and such laminates are included in the present invention.

In general the present invention does not change laminating procedure in any significant manner and only a very general and typical lamination will be described in the more specific description which follows. The particular laminating technique used, therefore, is not the distinguishing feature of the present invention, which is an advantage because well known techniques can be used.

The nature of the laminating resin is also not changed by the present invention and any of the well known resins, such as alkyds, epoxies and the like, may be used. Where an all high modulus graphite reinforcing fabric is used, it is often desirable to protect it during shipment and so a suitable backing sheet of polyethylene or the like may be employed. The fabric, of course, should not be wound on packages with too small a radius and care should be taken in laying it up for laminating as the fabric is much more brittle than fabrics made of glass fiber yarns.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a plan view of a typical Genin fabric of the prior art with some of the glass fiber yarns at the edge unraveled;

FIG. 2 is a plan view of a modification not described by Genin in which glass fiber yarns are used in one direction only;

FIG. 3 is a plan view of a fabric according to the present invention made of high modulus graphite and enormously magnified to show the knitted stitching;

FIG. 4 is a plan view, unmagnified, of a mixed high modulus graphite, glass fiber fabric;

FIG. 5 is an isometric of a laminate using a fabric of FIGS. 3 or 4, and

FIG. 6 is an isometric of a laminate using fabrics in which one layer has the inserted wefts at an angle to the other.

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 shows a typical glass fiber fabric according to the Genin patent. The glass fiber threads are shown at (l) and (2) crossing each other but not woven over each other, and thin binding yarn is shown at (3) weaving together the glass fiber yarns. As can be seen at the edge where several yarns are shown raveled off, the edges are quite unstable and tend to ravel easily, which is a serious problem in forming laminates of material for uses such as propellers, rotors, fan blades, and the like where edge stability is of major importance. Also, at the point where the yarns have been raveled off, the glass fiber yarns show areas (4) where they have been crimped to some degree by the binding yarns (3). As has been stated above, the Genin fabric represented an improvement, even though crimping is not entirely eliminated.

If it is attempted to make a woven fabric which is unidirectional, as is shown in FIG. 2 with the glass fiber yarns (1) and the binding yarns (3), the glass fiber yarns are not held rigidly in parallel alignment as they can slide along the woven binding threads. This is shown in somewhat exaggerated form in the case of the glass fiber yarn (5). Unless extraordinary care is taken, some of these yarns will depart from parallelism, with loss of strength in the final laminate because under tension the distorted yarn straightens out, as has been described above. Of course even with a unidirectional woven fabric the problems of edge raveling remain and so does the small amount of crimping from the binding yarns which have been described above in connection with FIG. 1.

FIG. 3 shows in a greatly magnifiedform a fabric according to the present invention with high modulus graphite yarns (6) held together with chain stitches knit of a yarn (7) on a warp knitting machine. It will be seen that the high modulus graphite yarns are held in exact parallelism firmly but gently since the stitches of much lighter, soft thread surround them and do not crimp them at all. Such a fabric, and of course a laminate made from it as a reinforcing fabric, utilizes the maximum modulus and tensile strength of the high modulus graphite yarns. It will also be apparent that since the stitches hold the yarns together, there can be no raveling at an edge, and this problem, which is a serious one with a woven fabric if it is to be used for propeller blade laminates or the like, does not occur. In other words, the great advantage of elimination of crimping is obtained without any offsetting disadvantages and, in fact, with a greatly improved edge effect which does not ravel.

FIG. 3 represents the preferred modification with no lock stitched wales at all and shows very thick threads of high modulus graphite, for example up to about 10,000 individual graphite filaments. It therefore repre-. sents one extreme, but even here the wales are spaced, slightly over three times the cross-section of the high modulus graphite threads.

Because of the markedly higher cost of the high modulus graphite as compared to glass fibers, it is often desirable, where the absolute maximum of laminate tensile strength is not needed, to use a mixture of high modulus graphite and glass fiber, and this is shown in FIG. 4, the glass fiber yarns being shown at (9) whereas the high modulus graphite yarns bear the same number,

some strength in a direction at an angle to the high modulus yarns of the first layer. This improves the resistance to shear in propeller or fan blades.

FIG. 5 is a sample of laminate and not a portion of a propeller or compressor fan blade. The reinforcing fabric is shown'in one direction only, whereas, as has been pointed out above, often in the case of a propeller or a fan blade there may be more than one layer of reinforcing fabric at an angle, such as 20 to In FIG. 5 this would only confuse the drawing and so an additional layer at an angle is not shown.

While the present invention does not change the procedure of lamination, the following brief description of a typical process is given:

Twelve layers of the resin preimpregnated fabric of the present invention, (resin used was a dispersion of high performance cycloaliphatic epoxy resin), were placed into a press and cured, using a standard curing cycle, until the resin had completely set. Two samples were made, one with the epoxy resin sold by Union Carbide Company under their designation ERLA-46 l 7 and another with a similar resin sold by the Shell Company under their designation EPON-826. The fabrics were knit with fine soft nylon with chain stitched wales four to the inch, the high modulus graphite in both cases having 780 filaments. The resulting laminates were then tested and compared to the same high modulus grahite yarn in a laminate form produced by a filament winding of the prepregged graphite yarn, pre- (6), as in FIG. 3. FIG. 4illustrates very much finer laidpregged th th sam resin, the u r of laminae in wefts and hence the ratio of the spacing of the wale is considerably greater, approximatingeight times the being the same. Results of these tests are shown in Table 2:

T TAB'IQE '2 PREPREGGED PREPREGGED PREPREGGED YARN FILAMENT FABRIC OF FABRIC OF WOUND ON TWO MECHANICAL INYENIION. INVENTION SIDED MOLD PROFE'E E RESIN EPON-826 RESIN ERLA-46l7 RESIN ERLA-46-l7N No. No. 0. Range Ave. 0 Tests Range Ave. Tests Range Ave. Tests Flexural Modulus 24.7- 27.2- 27. l0 psi 28.0 26.4 5 30.2 28.9 8 31.8 29.6 l2

Interlaminar Shear Strength 9.3- 7.4- 6.5- X I000 psi 9.9 9.6 5 9.7 8.8 I6 10.7 9.1 12

Volume Fractions Not Determined 57-62 60 4 50-63 57 I2 cross-section of the high modulus yarn. This is not the limit for with even finer high modulus yarns and somewhat greater wale spacing. usable fabrics may have a ratio of wale spacing to cross-section of high modulus fibers as high as 80 or 100 times. i

FIG. 5 illustrates, in isometric form, laminates of a fabric such as that of FIG. 3 or FIG. 4, the resin,'such as epoxides, alkyds, etc., being shown at (8). The isometric view permits showing one edge of the laminate substantially in section. illustrating the ends of the high modulus yarns. FIG. 5 illustrates a laminate in which all of the high modulus yarns are in the same direction. FIG. 6 shows a two-layer laminate and is partly broken away at an edge. the bottom layer (10) shows the high modulus yarns (6) in one direction and the second layer (11) shows the high modulus yarns (6) at a slight angle, about 30, which produces a laminate which has It will be noted that the interlaminar shear strength is comparable in each case but with a somewhat closer range for the laminates produced with fabrics of the present invention. This is a small but not insignificant advantage as it shows a greate uniformity of properties. In other words, products with as good flexural modulus and interlaminar shear strength are obtained with all of the advantages, economic and operational, of the present invention which have been set out above.

In the tests for interlaminar shear strength set out above the graphite yarns were all in the same direction. When products according to FIG. 6 are produced the layers, of course, are not parallel, although the fibers in each layer are.

Another method of lamination which is usable with the reinforcing fabrics of the present invention is to place a resin film in a mold, then a layer of fabric, then one or more layers of resin film, another layer of fabric, and so on. This method produces final laminates of the same excellent physical properties as when layers of prepregged fabric are used as is described above. As an example, the Bloomingdale Epoxy Resin film B.P. 907 has been used successfully to manufacture laminates described in this paragraph.

I claim:

1. A reinforcing fabric suitable for laminates formed of parallel, continuous filaments yarns of high modulus graphite, the modulus of elasticity thereof, of more than 8,000,000 lbs. per square inch, the graphite being extremely brittle, the yarns being bound together with chain stitch knit wales which surround the outside of the continuous filament parallel yarns, the parallel yarns being held firmly by the knit stitches and maintained thereby in strict parallelism, wale spacing being at least about three times parallel filament yarns crosssectional diameter in same units and the majority of the wales being chain stitch.

2. A fabric-reinforced resin laminate, the resin having bonding affinity for high modulus graphite, and the laminate being for articles requiring high tensile strength primarily in one direction only in which the reinforcement is a fabric according to claim 1.

3. A multi-layer resin laminate according to claim 2 in which at least one layer has its yarns of high modulus graphite at a small angle to those of another layer.

4. A resin laminate according to claim 2 in which the

Claims (3)

  1. 2. A fabric-reinforced resin laminate, the resin having bonding affinity for high modulus graphite, and the laminate being for articles requiring high tensile strength primarily in one direction only in which the reinforcement is a fabric according to claim 1.
  2. 3. A multi-layer resin laminate according to claim 2 in which at least one layer has its yarns of high modulus graphite at a small angle to those of another layer.
  3. 4. A resin laminate according to claim 2 in which the small angle is from 20* to 30*.
US3819461A 1969-08-19 1971-10-08 Unidirectional, high modulus knitted fabrics Expired - Lifetime US3819461A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US85140869 true 1969-08-19 1969-08-19
US3819461A US3819461A (en) 1969-08-19 1971-10-08 Unidirectional, high modulus knitted fabrics

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3819461A US3819461A (en) 1969-08-19 1971-10-08 Unidirectional, high modulus knitted fabrics

Publications (1)

Publication Number Publication Date
US3819461A true US3819461A (en) 1974-06-25

Family

ID=26883274

Family Applications (1)

Application Number Title Priority Date Filing Date
US3819461A Expired - Lifetime US3819461A (en) 1969-08-19 1971-10-08 Unidirectional, high modulus knitted fabrics

Country Status (1)

Country Link
US (1) US3819461A (en)

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3914494A (en) * 1973-04-03 1975-10-21 Celanese Corp Pervious low density carbon fiber reinforced composite articles
US3953641A (en) * 1972-04-19 1976-04-27 Societe Civile D'etudes Et De Recherches Pour L'obtention De Fibres Minerales (S.E.R.O.F.I.M.) Ply of parallel filaments
US3993829A (en) * 1973-04-03 1976-11-23 Celanese Corporation Production of pervious low density carbon fiber reinforced composite articles
US3997697A (en) * 1973-05-10 1976-12-14 J. Brochier & Fils Fabric with boron filaments
US4063684A (en) * 1975-11-25 1977-12-20 The United States Of America As Represented By The Secretary Of The Air Force Composite rocket nozzle structure
US4103055A (en) * 1975-05-26 1978-07-25 Avions Marcel Dassault-Breguet Aviation Porous structure
US4153750A (en) * 1978-04-26 1979-05-08 Sommer Exploitation Floor and/or wall covering
US4183993A (en) * 1978-01-30 1980-01-15 Gulf States Paper Corporation Reinforced fabric and laminate made therewith
US4260441A (en) * 1978-05-10 1981-04-07 United Technologies Corporation Quick bond composite and process
US4320160A (en) * 1979-08-21 1982-03-16 Toray Industries, Inc. Fabric structure for fiber reinforced plastics
WO1982004227A1 (en) * 1981-06-03 1982-12-09 Fluidics Corp Bowles Improvements in oscillating reed and method
US4416929A (en) * 1981-07-02 1983-11-22 Proform, Inc. Multilayer stitched knitted fiberglass composite
US4460633A (en) * 1981-12-16 1984-07-17 Kurashiki Boseki Kabushiki Kaisha Non-woven reinforcement for composite
US4622254A (en) * 1981-08-31 1986-11-11 Toray Industries, Inc. Fiber material for reinforcing plastics
US4748996A (en) * 1987-02-06 1988-06-07 J. B. Martin Company Woven multilayered textile fabrics and attendant method of making
US4786541A (en) * 1981-08-31 1988-11-22 Toray Industries, Inc. Fiber material for reinforcing plastics
US4854352A (en) * 1987-02-06 1989-08-08 J. B. Martin Company Textile fabrics having a plurality of warp and filling layers and attendant method of making
US4867760A (en) * 1980-07-31 1989-09-19 Norton Company Coated abrasive
US5014755A (en) * 1987-08-11 1991-05-14 Brochier S.A. Textile structure with binding weave for multiple layers of non-interlaced fit filaments
US5149583A (en) * 1988-02-09 1992-09-22 Jukka Saarikettu Oriented thread structure and a method for manufacturing same
US5166480A (en) * 1988-04-23 1992-11-24 Vorwerk & Co. Interholding Gmbh Knitted fabric panel structure and process of manufacture
US5200018A (en) * 1990-12-19 1993-04-06 Hercules Incorporated Ribbonizing apparatus for individually heating a plurality of laterally adjacent tows in a fiber placement device
US5273602A (en) * 1990-12-19 1993-12-28 Hercules Incorporated Ribbonizing method for selectively heating a respective one of a plurality of fiber tows
US5290389A (en) * 1990-12-19 1994-03-01 Hercules Incorporated Fiber placement delivery system with modular cut/add actuators
US5520984A (en) * 1993-12-24 1996-05-28 Vetrotex France Glass-strand mesh and composite material reinforced thereby
US5543212A (en) * 1993-12-02 1996-08-06 Toray Industries, Inc. Prepregs comprising a reinforcing fiber layer, a knitted fabric of thermoplastic fibers and a matrix resin
US5698066A (en) * 1990-12-19 1997-12-16 Alliant Techsystems Inc. Band fiber forming and placement delivery head
US5878645A (en) * 1997-09-12 1999-03-09 Streit; Carl Accordion fold curtains and method of manufacture
US6096164A (en) * 1990-12-19 2000-08-01 Alliant Techsystems Inc. Multiple axes fiber placement machine
US20020164911A1 (en) * 2001-05-03 2002-11-07 Cunningham David Verlin Quasi-unidirectional fabric for ballistic applications
US6752190B1 (en) 1991-07-31 2004-06-22 Alliant Techsystems Inc. Cure-on-the-fly system
FR2864972A1 (en) * 2004-01-14 2005-07-15 Chomarat Composites Reinforcing material for resin-based composition components comprises filaments or fibres in one or more parallel planes connected by stitching or knitting
US20050186069A1 (en) * 2004-02-23 2005-08-25 General Electric Company Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
US20070080481A1 (en) * 2005-10-12 2007-04-12 The Boeing Company Apparatus and methods for fabrication of composite components
US20070099526A1 (en) * 2001-05-03 2007-05-03 Heerden Jason V Densely woven quasi-unidirectional fabric for ballistic applications
US20090214815A1 (en) * 2008-02-22 2009-08-27 Ryo Okada Quasi-unidirectional fabrics for structural applications, and structural members having same
US8850612B1 (en) 2011-09-01 2014-10-07 Armorworks Enterprises LLC Ballistic helmet and fabrication method

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3105372A (en) * 1958-04-10 1963-10-01 Celanese Corp Resistant fabric
US3235323A (en) * 1960-04-14 1966-02-15 Minnesota Mining & Mfg Heat-resistant black fibers and fabrics derived from rayon
US3283389A (en) * 1966-11-08 Method op making multi-break fabric
US3367812A (en) * 1962-11-14 1968-02-06 Union Carbide Corp Process of producing carbonized articles
US3462340A (en) * 1965-07-28 1969-08-19 Us Air Force Fiber-containing pyrolytic composite material
US3466219A (en) * 1965-08-09 1969-09-09 Us Air Force Fiber reinforced plastic composite material
US3484183A (en) * 1965-06-04 1969-12-16 Minnesota Mining & Mfg Heat-resistant black fibers and fabrics derived from rayon
US3527564A (en) * 1968-04-15 1970-09-08 Stevens & Co Inc J P Process for carbonizing fibrous materials
US3541582A (en) * 1966-07-08 1970-11-17 Nat Res Dev Manufacture of carbon cloth from polymeric fibre material
US3556712A (en) * 1967-06-03 1971-01-19 Nippon Carbon Co Ltd Method of making flame-proof fibers
US3637446A (en) * 1966-01-24 1972-01-25 Uniroyal Inc Manufacture of radial-filament spheres

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3283389A (en) * 1966-11-08 Method op making multi-break fabric
US3105372A (en) * 1958-04-10 1963-10-01 Celanese Corp Resistant fabric
US3235323A (en) * 1960-04-14 1966-02-15 Minnesota Mining & Mfg Heat-resistant black fibers and fabrics derived from rayon
US3367812A (en) * 1962-11-14 1968-02-06 Union Carbide Corp Process of producing carbonized articles
US3484183A (en) * 1965-06-04 1969-12-16 Minnesota Mining & Mfg Heat-resistant black fibers and fabrics derived from rayon
US3462340A (en) * 1965-07-28 1969-08-19 Us Air Force Fiber-containing pyrolytic composite material
US3466219A (en) * 1965-08-09 1969-09-09 Us Air Force Fiber reinforced plastic composite material
US3637446A (en) * 1966-01-24 1972-01-25 Uniroyal Inc Manufacture of radial-filament spheres
US3541582A (en) * 1966-07-08 1970-11-17 Nat Res Dev Manufacture of carbon cloth from polymeric fibre material
US3556712A (en) * 1967-06-03 1971-01-19 Nippon Carbon Co Ltd Method of making flame-proof fibers
US3527564A (en) * 1968-04-15 1970-09-08 Stevens & Co Inc J P Process for carbonizing fibrous materials

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Webber, Modern Textiles Magazine, Vol. 47, 5/66, pp. 72 75. *

Cited By (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3953641A (en) * 1972-04-19 1976-04-27 Societe Civile D'etudes Et De Recherches Pour L'obtention De Fibres Minerales (S.E.R.O.F.I.M.) Ply of parallel filaments
US3914494A (en) * 1973-04-03 1975-10-21 Celanese Corp Pervious low density carbon fiber reinforced composite articles
US3993829A (en) * 1973-04-03 1976-11-23 Celanese Corporation Production of pervious low density carbon fiber reinforced composite articles
US3997697A (en) * 1973-05-10 1976-12-14 J. Brochier & Fils Fabric with boron filaments
US4103055A (en) * 1975-05-26 1978-07-25 Avions Marcel Dassault-Breguet Aviation Porous structure
US4063684A (en) * 1975-11-25 1977-12-20 The United States Of America As Represented By The Secretary Of The Air Force Composite rocket nozzle structure
US4183993A (en) * 1978-01-30 1980-01-15 Gulf States Paper Corporation Reinforced fabric and laminate made therewith
US4153750A (en) * 1978-04-26 1979-05-08 Sommer Exploitation Floor and/or wall covering
US4260441A (en) * 1978-05-10 1981-04-07 United Technologies Corporation Quick bond composite and process
US4320160A (en) * 1979-08-21 1982-03-16 Toray Industries, Inc. Fabric structure for fiber reinforced plastics
US4867760A (en) * 1980-07-31 1989-09-19 Norton Company Coated abrasive
WO1982004227A1 (en) * 1981-06-03 1982-12-09 Fluidics Corp Bowles Improvements in oscillating reed and method
US4941398A (en) * 1981-06-03 1990-07-17 Bowles Fluidics Corporation Oscillating reed and method
US4416929A (en) * 1981-07-02 1983-11-22 Proform, Inc. Multilayer stitched knitted fiberglass composite
US4786541A (en) * 1981-08-31 1988-11-22 Toray Industries, Inc. Fiber material for reinforcing plastics
US4622254A (en) * 1981-08-31 1986-11-11 Toray Industries, Inc. Fiber material for reinforcing plastics
US4460633A (en) * 1981-12-16 1984-07-17 Kurashiki Boseki Kabushiki Kaisha Non-woven reinforcement for composite
US4748996A (en) * 1987-02-06 1988-06-07 J. B. Martin Company Woven multilayered textile fabrics and attendant method of making
US4854352A (en) * 1987-02-06 1989-08-08 J. B. Martin Company Textile fabrics having a plurality of warp and filling layers and attendant method of making
US5014755A (en) * 1987-08-11 1991-05-14 Brochier S.A. Textile structure with binding weave for multiple layers of non-interlaced fit filaments
US5149583A (en) * 1988-02-09 1992-09-22 Jukka Saarikettu Oriented thread structure and a method for manufacturing same
US5166480A (en) * 1988-04-23 1992-11-24 Vorwerk & Co. Interholding Gmbh Knitted fabric panel structure and process of manufacture
US5698066A (en) * 1990-12-19 1997-12-16 Alliant Techsystems Inc. Band fiber forming and placement delivery head
US5273602A (en) * 1990-12-19 1993-12-28 Hercules Incorporated Ribbonizing method for selectively heating a respective one of a plurality of fiber tows
US5200018A (en) * 1990-12-19 1993-04-06 Hercules Incorporated Ribbonizing apparatus for individually heating a plurality of laterally adjacent tows in a fiber placement device
US6096164A (en) * 1990-12-19 2000-08-01 Alliant Techsystems Inc. Multiple axes fiber placement machine
US5290389A (en) * 1990-12-19 1994-03-01 Hercules Incorporated Fiber placement delivery system with modular cut/add actuators
US6752190B1 (en) 1991-07-31 2004-06-22 Alliant Techsystems Inc. Cure-on-the-fly system
US5543212A (en) * 1993-12-02 1996-08-06 Toray Industries, Inc. Prepregs comprising a reinforcing fiber layer, a knitted fabric of thermoplastic fibers and a matrix resin
US5520984A (en) * 1993-12-24 1996-05-28 Vetrotex France Glass-strand mesh and composite material reinforced thereby
US5878645A (en) * 1997-09-12 1999-03-09 Streit; Carl Accordion fold curtains and method of manufacture
US20070099526A1 (en) * 2001-05-03 2007-05-03 Heerden Jason V Densely woven quasi-unidirectional fabric for ballistic applications
WO2002090866A1 (en) 2001-05-03 2002-11-14 Barrday, Inc. Quasi-unidirectional fabric for ballistic applications
US20040224592A1 (en) * 2001-05-03 2004-11-11 Cuningham David Verlin Quasi-unidirectional fabric for ballistic applications
US6861378B2 (en) 2001-05-03 2005-03-01 Barrday, Inc. Quasi-unidirectional fabric for ballistic applications
US7820565B2 (en) 2001-05-03 2010-10-26 Barrday Inc. Densely woven quasi-unidirectional fabric for ballistic applications
US20020164911A1 (en) * 2001-05-03 2002-11-07 Cunningham David Verlin Quasi-unidirectional fabric for ballistic applications
WO2005072940A1 (en) * 2004-01-14 2005-08-11 Chomarat Composites Novel reinforcing stiffening wire complex
FR2864972A1 (en) * 2004-01-14 2005-07-15 Chomarat Composites Reinforcing material for resin-based composition components comprises filaments or fibres in one or more parallel planes connected by stitching or knitting
US20070082201A1 (en) * 2004-02-23 2007-04-12 General Electric Company USE OF BIASED FABRIC TO IMPROVE PROPERTIES OF SiC/SiC CERAMIC COMPOSITES FOR TURBINE ENGINE COMPONENTS
US7579094B2 (en) 2004-02-23 2009-08-25 General Electric Company Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
US20050186069A1 (en) * 2004-02-23 2005-08-25 General Electric Company Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
US7306826B2 (en) 2004-02-23 2007-12-11 General Electric Company Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
US20070080481A1 (en) * 2005-10-12 2007-04-12 The Boeing Company Apparatus and methods for fabrication of composite components
EP1908864A1 (en) 2006-10-05 2008-04-09 Barrday, Inc. Densely woven quasi-unidirectional fabric for ballistic applications
US20090214815A1 (en) * 2008-02-22 2009-08-27 Ryo Okada Quasi-unidirectional fabrics for structural applications, and structural members having same
US8017532B2 (en) 2008-02-22 2011-09-13 Barrday Inc. Quasi-unidirectional fabrics for structural applications, and structural members having same
US8850612B1 (en) 2011-09-01 2014-10-07 Armorworks Enterprises LLC Ballistic helmet and fabrication method

Similar Documents

Publication Publication Date Title
US3526306A (en) Clutch facing
US3719212A (en) Circular weaving apparatus product and process
US3749138A (en) Thick fabrics
US4282011A (en) Woven fabrics containing glass fibers and abrasive belts made from same
Campbell Structural composite materials
US4403012A (en) Ballistic-resistant article
US6187411B1 (en) Stitch-reinforced sandwich panel and method of making same
US5130193A (en) Fiber-reinforced composite cable
US4892780A (en) Fiber reinforcement for resin composites
US2594693A (en) Hollow circular article and method of making same
US4868038A (en) Carbonaceous fiber reinforced composites
EP0361796A2 (en) Method of producing a formable composite material
US4725485A (en) Textile structure for reinforced composite material
US6183834B1 (en) Balistic-resistant moulded article and a process for the manufacture of the moulded article
US5688594A (en) Hybrid yarn
US5597649A (en) Composite yarns having high cut resistance for severe service
US4621980A (en) Fiber reinforced composite spar for a rotary wing aircraft
US6893704B1 (en) Ballistic-resistant moulded article and a process for the manufacture of the moulded article
US5672417A (en) Turbomachine blade made of composite material
US4407885A (en) Composite article
US20040241415A1 (en) Reinforcing fiber substrate, composite material and method for producing the same
US2862283A (en) Anti-friction fabric
US5565264A (en) Protective fabric having high penetration resistance
Dransfield et al. Improving the delamination resistance of CFRP by stitching—a review
US5888609A (en) Planar porous composite structure and method for its manufacture

Legal Events

Date Code Title Description
AS Assignment

Owner name: BANKERS TRUST COMPANY, A NY BANKING CORP., NEW YO

Free format text: SECURITY INTEREST;ASSIGNOR:J.P. STEVENS & CO.;REEL/FRAME:005271/0777

Effective date: 19891020

AS Assignment

Owner name: J.P. STEVENS & CO., INC., GEORGIA

Free format text: RELEASE SECURITY INTEREST & ASSIGNMENT.;ASSIGNOR:BANKERS TRUST COMPANY;REEL/FRAME:007074/0390

Effective date: 19931210