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Publication numberUS3571901 A
Publication typeGrant
Publication dateMar 23, 1971
Filing dateJun 13, 1969
Priority dateJun 13, 1969
Publication numberUS 3571901 A, US 3571901A, US-A-3571901, US3571901 A, US3571901A
InventorsSara Raymond Vincent
Original AssigneeUnion Carbide Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Method of fabricating a carbon-fiber reinforced composite article
US 3571901 A
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Description  (OCR text may contain errors)

United States Patent [72] Inventor Raymond Vincent Sara North Olmsted, Ohio [21 Appl. No. 833,009 [22] Filed June 13, 1969 Division ot S er. No. 727,898, May 9, 1968. [45] Patented Mar. 23, 1971 [73] Assignee Union Carbide Corporation New York, N.Y.

[54] METHOD OF FABRICATING A CARBON-FIBER REINFORCED COMPOSITE ARTICLE 3,491,055 l/1970 Talley Att0rneysPaul A. Rose, Robert C. Cummings, Frederick J.

Mc Carthy, Jr. and John S. Piscitell ABSTRACT: Light weight composite refractory articles com- 5 Claims, 2 Drawing Figs.

prising a plurality of metal or alloy coated carbon fibers [52] US. Cl 29/419, bonded together by an aluminum base matrix are provided,

/8 164/91 The coating metal or alloy can be any material selected from [51] Int. Cl B23p 17/0 the group consisting of silver, silver-aluminum base alloys and [50] Field of Search 164/80, 91, i t th f, Th eferred process for producing such 29/182-2, 1325; 29/419, 527-3, 5275 composites comprises contacting silver coated carbon fibers with an aluminum base material followed by hot pressing the [56] References Cited so-contacted fibers at the solidus temperature of the alu- UNITED STATES PATENTS minum base material to infiltrate aluminum around the silver- 9l0,674 1/1909 Hancock 164/86 coated fibers and then cooling the resultant article to a 2,937,436 5/1960 Butler et a1. 29/419 completely solidified state. Such composite articles are 3,038,248 6/1962 Kremer 29/419 characterized by a high tensile strength coupled with a high 3,187,422 6/1965 Morgan 29/419 modulus of elasticity and are especially suited as materials of 3,256,596 6/ 1966 Fiedler 29/419 construction for aerospace and hydrospace vehicles and 3,476,529 1 1/1969 Dubin et a1. 1 17/71X systems.

A lummum PATENIED m2 3 I9?! Aluminum Carbon Silver-Aluminum INVENTOR. RAYMOND V. SARA A T TORNE V METHOD OF FABRICATING A CARBON-FIBER REINFORCED COMPOSITE ARTICLE This application is a division of copending application Ser. No. 727,898, filed May 9, 1968.

BACKGROUND OF THE INVENTION 1 Field of the Invention The present invention relates to high strength, high modulus composite refractory articles composed of a plurality of carbon fibers which are essentially coated with a thin layer of silver and/or silver base alloys and bonded together by an aluminum base matrix and to the process of producing the same.

2. Description of the Prior Art In the space and missile industries, there has developed a need for refractory materials of construction which exhibit exceptional physical properties, for example, low density coupled with high strength and stiffness. Attempts to produce such refractory materials have centered around the fabrication of composite articles.

One of the most promising materials available today for use in composite form is carbon textiles since they possess excellent refractory properties and are commercially available in all known textile forms. Today, it is well known to form composites of carbon textiles and resins.

Recently, efforts have been directed to forming composites of carbon textiles and metals. The prime object of forming such composites is to increase the strength of the metal matrix by the inclusion therein of high strength carbon fibers.

Aluminum has been suggested as the matrix media for carbon fiber-metal composites which are intended for use in aerospace applications, in the main, due to its low density. However, attempts heretofore to incorporate carbon fibers in an aluminum matrix have met with little or no practical success due to the fact that carbon, especially its graphic form, is not readily wetted by molten aluminum.

The present invention overcomes the foregoing problem by employing an intermediate coating or wetting agent which when applied to the carbon fibers enables them to be readily bonded together by an aluminum base matrix material.

SUMMARY Broadly stated, the carbon fiber-aluminum composite article of the invention comprises a plurality of carbon fibers each of which is coated with either a thin layer of silver, a silver-aluminum base alloy or mixtures thereof and bonded together, preferably in a side-by-side or parallel manner, with an aluminum binder or matrix material. Generally, this composite article may be provided by a process which comprises coating carbon fibers with a thin but essentially continuous film of silver, contacting the so-coated fibers with a solidified aluminum base material, hot pressing the so-produced assembly at the solidus temperature of the aluminum base material to infiltrate it around the coated fibers and cooling the resultant aluminum bonded carbon fibers to produce a composite article. This article can then be formed into any desired shape by known techniques which will readily suggest themselves to those skilled in the art.

DESCRIPTION OF THE DRAWINGS FIG. 1 is a diagrammatical illustration of a portion of a carbon fiber-aluminum composite article produced according to the preferred teachings of the invention; and

FIG. 2 is a greatly magnified diagrammatical illustration of a single fiber found in the composite of FIG. 1.

Referring now to the drawings in detail, FIG. 1 shows a portion of a rectangular composite article 10 consisting of aligned graphite fibers 12 (the silver coating and aluminum-silver zone thereon are not shown) bonded together by an aluminum matrix 18. The graphite fibers 12 are disposed in the aluminum matrix in a parallel manner with their length dimension being perpendicular to the surface of the drawing. FIG. 2 shows a single graphite fiber 12 taken from the composite l of FIG. 1 having on its surface a coating of silver 14 and an aluminum-silver interface zone 16 between the silver coating and the aluminum matrix 18.

DESCRIPTION OF THE PREFERRED EMBODIMENT OF THE INVENTION Carbon textiles in any form can be employed in the practice of the instant invention. However, it is preferred to employ carbon fibers in yarn or multifilament form. Carbon textiles are available commercially and are generally produced by the techniques described in U.S. Pat. Nos. 3,107,152 and 3,1 16,975, among others.

Silver can be deposited on the carbon fibers by a variety of methods. The techniques available for accomplishing this in clude electrodeposition from a conductive bath, reduction of salts to the metal or sputtering. The exact deposition technique to be employed is dictated by a number of factors. Sputtering can be used on relatively complex shapes and results in a tenacious bond between the thin silver coating and the carbon fiber substrate. Such a bond is a highly desirable feature in carbon fiber-metal matrix composites. Dipping of the carbon fibers into a silver containing solution and chemically reducing the salt to the metal can also be employed, however, with this technique it is difficult to accurately control the thickness of the silver coating. Electrodeposition of silver from a conductive bath is an ideal way of coating carbon fibers with a thin film of silver and is the preferred method since it results in a uniform, tenaciously bonded metallic coating.

The following example illustrates in detail the preferred practice of the instant invention.

A single ply graphite yarn composed of 720 monofilaments, each characterized by an average modulus of elasticity of 3 3.5 X 10 lb./in. and an average tensile strength of 20 X 10 lb./in. was cut into a plurality of 4inch lengths. These lengths of yarn were heated at 560 C. for 30 seconds in a tube furnace which was open to the atmosphere. The slightly oxidized fibers were immediately plated electrolytically with silver by placing them in a strike solution for about 5 to 10 seconds and then into a conventional plating solution for about 5 to 10 seconds. The plating current employed was about 400 milliamps for the strike solution and between about 600 to 800 milliamps for the conventional plating solution. The make up of the strike and conventional plating solution was as follows:

Strike Solution Silver Cyanide (Ag CN) 6.5 g./ 1. Potassium Cyanide (KCN) 68.0 g./ 1.

Regular Solution Silver Cyanide (Ag CN) 41 g./1. Potassium Cyanide (KCN) 4O g./1. Potassium Hydroxide (K011) 11 g./1. Potassium Carbonate (K CO 62 g./l.

The so-coated graphite fibers were cut into one inch lengthsand then positioned in a parallel manner between alternate layers of aluminum alloy foils measuring'0.003 inch X 0.125

inch X 1.00 inch each. The aluminum alloy employed con sisted of 4.5 weight percent copper, 0.6 weight manganese, 1.5 weight percent magnesium with the remainder being essentially aluminum. Two single plies of silver-coated yarn were used for each layer. The complete array consisted of 22 layers of foil and 42, one-inch lengths of silver-coated single ply yarn. This assembly was placed in a graphite mold and hot pressed at 2,250 lb./in. in vacuum at approximately 550 C. for one hour. The composite was subsequently cooled in the mold to room temperature and then formed into a 1/16" XVs" X 1" specimen for physical property measurements. This specimen evidenced an average tensile strength of 44,10 lb./in. and a Youngs modulus of 13.0 X 10 lb./in.

The table below shows the improvement obtained by incorporating silver coated graphite fibers in an aluminum base matrix material by the technique of the instant invention.

TABLE PROPERTIES OF GRAPHITE-FIBER, ALUMINUM COMPOSITE Composites produced by the technique of the instant invention are extremely useful as materials of construction for subsonic and supersonic aircraft, space system components and various propulsion devices.

It will be appreciated by those skilled in the art that while the preferred technique of the invention results in a composite article which comprises silver-coated carbon fibers bonded together by an aluminum base matrix, the silver coating on the carbon fibers may be converted to a silver-aluminum base alloy by annealing the composite during its fabrication or after it has been formed. The only requirement being that the silveraluminum base alloy not be formed at a temperature in excess of the melting point of the applied silver coating. Accordingly, it is clear that the instant invention results in a unique type of composite comprising carbon fiber which are coated with.

either silver, a silver-aluminum base alloy or mixture thereof and bonded together by an aluminum base matrix.

While the foregoing example concerns a composite having the fibers positioned in a side-by-side relationship, it is readily apparent to those skilled in the art that the carbon fibers may be randomly orientated in the aluminum matrix if more isotropic physical properties are desired without losing the benefits of the instant invention. In addition, it is obvious that the thickness of the silver can be varied as desired. All that is required is that it be thick enough to prevent the aluminum matrix metal from coming into contact with the reinforcing carbon fibers to such an extent that there is essentially no bonding between the fibers and the matrix metal. Likewise, it

will be appreciated by those versed in the art that although graphite fibers and fabrics are preferred in the practice of the instant invention, nongraphitic carbon fibers and fabrics may also be employed.

It should be noted here that while the invention can be beneficially practiced by using pure aluminum as the matrix metal, it is preferred to employ an aluminum base alloy which has an incongruent melting temperature. Such alloys are well known in the art and will not be discussed herein in detail.

In addition it should be noted that while it may be possible to infiltrate the molten aluminum metal around the silver clad carbon fibers without removing the silver therefrom, the preferred practice of the invention involves infiltrating the matrix metal around the filaments by heating the metal to a temperature at which it begins to melt but below that at which 7 it becomes completely liquid, i.e., at its solidus temperature,

and then forcing the so-softened matrix metal around the individual filaments by the means of an applied pressure. The amount of pressure to be applied is not particularly critical and need only be sufficient to compact the fibers and matrix material into an essentially nonporous article. 4

The term carbon as used herein and in the appended claims vis meant to include both the nongraphitic and graphitic forms of carbon.

The foregoing example is presented for illustrative purposes only and is not intended to unduly limit the reasonable scope of the instant invention. The limitations of applicants invention are defined by the following claims.

I claim:

1. A method of producing a metal coated carbon fiber aluminum-bonded composite article comprising:

a. contacting a plurality of silver coated carbon fibers with a solidified aluminum base material;

b. heating the so-formed mass to the solidus temperature of magnesium with the remainder being essentially aluminum.

3. A method of producing an aluminum-bonded silvercoated carbon fiber composite article comprising:

a. forming an assembly comprising alternate layers of silver coated carbon fibers and aluminum base foil, said fibers being positioned thereon in a parallel manner;

b. placing the so-formed assembly in mold and heating it in an inert atmosphere to a temperature approximately equal to the solidus temperature of said aluminum base foil while exerting a sufficient pressure on said assembly to cause said aluminum base foil material to be infiltrated around said silver-coated carbon fibers; and

c. cooling the resultant assembly to produce an aluminumbonded silver-coated carbon fiber composite.

4. The method of claim 3 wherein:

a. said aluminum base foil material consists essentially of 4.5 weight percent copper, 0.6 weight percent manganese, 1.5 weight percent magnesium with the remainder being essentially aluminum; and

b. said heating in step (b) is accomplished in a vacuum at a temperature of about 550 C.

5. The method of claim 1 wherein said aluminum-bonded silver-coated carbon fiber composite article is heated to a temperature sufficient to cause at least some said silver to alloy with at least some of said aluminum to form at least a partial coating of a silver-aluminum base alloy on said fibers.

Patent Citations
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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3679324 *Dec 4, 1970Jul 25, 1972United Aircraft CorpFilament reinforced gas turbine blade
US3695335 *Sep 8, 1970Oct 3, 1972John Corjeag CannellProcess for making composite materials from refractory fibers and metal
US3717419 *Jul 9, 1971Feb 20, 1973Susquehanna CorpTurbine blade
US3807996 *Jul 10, 1972Apr 30, 1974Union Carbide CorpCarbon fiber reinforced nickel matrix composite having an intermediate layer of metal carbide
US3818588 *Mar 29, 1973Jun 25, 1974Nat Res DevElectrical brushes
US3862657 *Jul 20, 1973Jan 28, 1975Concast AgMethod and apparatus for continuous casting of metal with a considerably lower specific gravity of the strand in relation to the cast metal
US3900150 *Aug 22, 1974Aug 19, 1975United Aircraft CorpDuplex composite tape
US3938579 *Sep 10, 1971Feb 17, 1976United Kingdom Atomic Energy AuthorityMethod of producing composite bearing materials
US3981616 *Oct 22, 1974Sep 21, 1976The United States Of America As Represented By The Secretary Of The Air ForceHollow composite compressor blade
US4261099 *Jul 27, 1979Apr 14, 1981Westinghouse Electric Corp.Method for making multi-element brushes
US4341823 *Jan 14, 1981Jul 27, 1982Material Concepts, Inc.Graphite or ceramics coated with nickel, copper, and noble metal, then immersed in molten lead, aluminum, tin or alloys thereof
US4347083 *Aug 29, 1980Aug 31, 1982Union Carbide CorporationTantalum, titanium, hafnium carbides
US4402744 *Aug 29, 1980Sep 6, 1983Union Carbide CorporationChemically bonded aluminum coating for carbon via monocarbides
US4609449 *Feb 28, 1984Sep 2, 1986American Cyanamid CompanyElectrodeposition, electroconductivity stabilizzation
US4661403 *Sep 12, 1984Apr 28, 1987American Cyanamid CompanyHigh strength; composite fiber core comprises carbon, boron or silicon carbide and metal coating
US4831707 *Jan 13, 1984May 23, 1989Fiber Materials, Inc.Method of preparing metal matrix composite materials using metallo-organic solutions for fiber pre-treatment
US4909910 *Jul 7, 1988Mar 20, 1990American CyanamidElectrodepositing a metal on electroconductive graphite core
US4919594 *Mar 8, 1989Apr 24, 1990Allied-Signal Inc.Composite member, unitary rotor member including same, and method of making
US4929513 *Jun 17, 1988May 29, 1990Agency Of Industrial Science And TechnologyPreform wire for a carbon fiber reinforced aluminum composite material and a method for manufacturing the same
US6112410 *Oct 21, 1998Sep 5, 2000The Research Corporation Of State University Of New YorkMethods for fabricating a structural beam
US6355340Aug 20, 1999Mar 12, 2002M Cubed Technologies, Inc.Low expansion metal matrix composites
US6568061 *Sep 21, 2001May 27, 2003Atlantic Research CorporationSpirally winding a retaining wire of a predetermined heat resistant metal over assembly under tension to retain said assembly in position on said mandrel
US7846506 *Sep 18, 2007Dec 7, 2010The United States Of America As Represented By The Secretary Of The Air Forceproviding the carbon composite substrate, depositing a layer of carbon on the substrate, applying a layer of aluminum on the layer of carbon, annealing the substrate at a temperature greater than a melting temperature of aluminum, and applying a layer of silver by electrodeposition
US8458886 *Dec 24, 2008Jun 11, 2013Messier-Bugatti-DowtyProcess for manufacturing a metal part reinforced with ceramic fibres
US20110005061 *Dec 24, 2008Jan 13, 2011Messier-Dowty SaProcess for manufacturing a metal part reinforced with ceramic fibres
U.S. Classification29/419.1, 29/527.3, 164/80, 416/241.00R, 428/614, 164/91, 416/230, 29/527.5
International ClassificationC22C49/14, C22C49/00, B64G1/22
Cooperative ClassificationB64G1/22, C22C49/14
European ClassificationC22C49/14
Legal Events
Sep 19, 1986ASAssignment
Effective date: 19860620