US3827129A - Methods of producing a metal and carbon fibre composite - Google Patents

Methods of producing a metal and carbon fibre composite Download PDF

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US3827129A
US3827129A US00215785A US21578572A US3827129A US 3827129 A US3827129 A US 3827129A US 00215785 A US00215785 A US 00215785A US 21578572 A US21578572 A US 21578572A US 3827129 A US3827129 A US 3827129A
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metal
added
fibres
matrix
titanium
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A Denham
B Redfern
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British Railways Board
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/14—Special methods of manufacture; Running-in
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P17/00—Metal-working operations, not covered by a single other subclass or another group in this subclass
    • B23P17/04—Metal-working operations, not covered by a single other subclass or another group in this subclass characterised by the nature of the material involved or the kind of product independently of its shape
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/16—Sliding surface consisting mainly of graphite
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2223/00—Surface treatments; Hardening; Coating
    • F16C2223/30—Coating surfaces
    • F16C2223/60—Coating surfaces by vapour deposition, e.g. PVD, CVD
    • Y—GENERAL 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49801—Shaping fiber or fibered material
    • Y—GENERAL 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49982—Coating
    • Y10T29/49984—Coating and casting

Definitions

  • ABSTRACT A process of producing a metal and carbon fibre composite in which carbon fibres are treated to produce a very thin coating on the surface and the treated fibres are then wetted by metal melts to which a particular alloying metal has been added.
  • the fibres are treated with a metal carbide and the alloying metal is preferably of the same metal as that of the carbide.
  • the carbon fibres are infiltrated into the matrix metal while the latter is in a molten state and the invention is particularly concerned with the production of a wetting interface between the metal alloys and the carbon fibres.
  • the method enables shaped bodies such as shaft bearings to be made in a convenient manner.
  • the composite may have other forms such as continu ous tapes for subsequent assembly into more complex shapes.
  • the purpose of producing metal and carbon fibre composites is essentially to maintain the mechanical properties of the metal and combine them with the anisotropic strengthening influence of carbon fibres.
  • Metal and carbon fibre composites can only be fabricated without the application of large pressures if the metal in the molten state wets the fibres. However, most engineering metals do not wet carbon fibres.
  • a wetting system will display several advantages. Infiltration of the carbon fibres into the matrix of the metal will be complete producing a composite with sustantially no porosity. Conventional molten metal casting techniques can be employed to produce the composites. The manufacturing process will be rapid. Continuous production of metal and carbon fibre composites in the form of tapes for subsequent assembly into complex shapes becomes possible.
  • a method of producing a metal and carbon fibre composite by a molten metal technique includes the use of carbon fibres having a coating of a carbide of titanium vanadium, hafnium, tantalum, zirconium, niobium or of other monocarbide forming metals or of chromium.
  • Such a coating will by itself provide a reasonably satisfactory wetting system for certain matrix metals such as aluminium.
  • matrix metals such as aluminium.
  • a small addition of one of the aforesaid metals is added to the matrix metal.
  • the coating on the carbon fibres and the addition to the matrix metal of one of the aforesaid metals will produce a chemical bond across the carbon fibre-metal interface. Particularly in the case of low melting point metals this will allow high temperature strength to be retained and will prevent dewetting if a subsequent local melting occurs in, for example, a hot pressing treatment.
  • the carbide coating on the fibres is formed by reacting the carbide forming metal with the carbon of the fibres for example using a metal halide vapour deposition method.
  • the added metal will either be present in solid solution in the matrix metal or as an intermetallic compound with the matrix metal.
  • solid solution it is preferable that there is at least 0.05 percent by weight added metal in solid solution.
  • intermetallic compound it is preferable that the melt into which the coated carbon fibres are infiltrated is maintained above 700C.
  • the coating is continuous and does not exceed 500 A thickness.
  • titanium has been found to be the most suitable both for use as the carbide coating on the carbon fibres and as the metal added to the matrix metal.
  • Matrix metals to which the invention may be applied include, for example tin-lead alloy, which brings the application of the invention into the field of plain bearings as will be described, and also include copper, aluminium and magnesium which bring the application of the invention into the field of structural artifacts.
  • titanium is used as the carbide forming metal on the carbon fibres and is also used as the metal added to the matrix metal.
  • a carbide coating is formed on the carbon fibres by a reaction of titanium with the carbon of the fibres using a titanium iodide vapour deposition method.
  • the reaction can be expressed as:
  • reaction formation 'Ii! formation TiC lormation In the temperature range 700C 1,000C, A Gdmmp m: is positive but Gmwm" is negative so the titanium is deposited specifically onto the carbon, forming titanium carbide.
  • the coating is adherent to the carbon fibre and evenly distributed.
  • the particle size is A 500A and the thickness can be controlled to the same order.
  • the coating is brittle and weaker than the carbon fibre but provided the thickness is kept below 500A degradation in strength is acceptable.
  • the carbon fibres. are coated by passing them through a reaction furnace one or two tows at a time in an atmosphere of argon, the tows each consisting of for example 10,000 fibres.
  • the reaction chamber is isolated by using liquid traps either side, these keep the reactants, namely titanium and iodine, in and oxygen out.
  • the fibres pass through constructions on the inlet and outlet passages of the furnace to prevent seepage of iodide from the furnace.
  • titanium iodide is formed and reacts with the carbon as described above and the coating rate and hence the speed at which the tows are pulled through the reaction chamber is 25 feet per hour.
  • the titanium carbide coated fibres thus formed are infiltrated into a matrix metal using conventional molten metal casting techniques, a small addition of titanium having been added to the matrix metal.
  • the presence of the titanium carbide coating and the added titanium metal ensure a satisfactory wetting interface between the carbon fibres and the matrix metal.
  • titanium is present in the melt of a particular matrix metal, which may itself be an alloy. It may be in solid solution and will therefore be released at the melting point of the alloy. Cu alloys offer such a system when the titanium is present at least by 0.5 percent by weight. Alternatively titanium may have restricted solid solution in a metal alloy and the chemical thermodynamics may favour the formation of an intermetallic coma conventional white metal alloy bearing and gave the following result on a standard Amsler test machine.
  • the solubility of the intermetallic compound in the liquid metal may be very low and consequently temperatures in excess of the alloy matrix melting point may be reached before wetting occurs.
  • the alloy system which is the basis of white metal bearing alloys, tin-lead, when combined with 0.5 percent titanium by weight forms a tintitanium intermetallic compound, which does not have appreciable solubility in the melt until about 800C.
  • the melt is superheated to this temperature before casting into it the coated carbon fibres.
  • FIG. 1 is a perspective view of the bearing
  • FIG. 2 is a cross-sectional view of the bearing
  • FlG. 3 is a longitudinal sectional view.
  • the bearing has a body 1 and incorporates a bearing insert 2.
  • the insert 2 comprises a tin-lead alloy and carbon fibre composite bonded to a tin-lead alloy block.
  • coated carbon fibres represented at 3 coated with titanium carbide by the method described above are placed in a silica mould in the neck of which is contained the matrix metal alloy having a nominal composition by weight of 8 percent tin 0.5 percent titanium and the remainder lead.
  • the alloy is melted in the neck by radio frequency (RF) heating until it has all flowed into the cylindrical mould containing the coated carbon fibres and forms a composite, i.e., a strip of matrix metal into which the fibres have been infiltrated.
  • RF radio frequency
  • the cast composite thus formed containing 10 percent by volume of carbon fibres is then placed in a mould and bonded by melting to the tinlead alloy block to form a test specimen, so that the carbon fibres are concentrated near the bearing surface 4 and extend parallel to the bearing surface.
  • Method of forming a metal and carbon fibre composite which comprises coating the carbon fibres with a carbide of a member selected from the group consisting of titanium, vanadium, hafnium, tantalum, zirconium, niobium, other monocarbide forming metals, and chromium; then employing a molten technique to cause infiltration of the coated carbon fibres into a matrix metal while the matrix metal is in a molten state, and obtaining said metal and carbon fibre composite.
  • a method as claimed in claim 1, wherein the coating is formed as a preliminary step by reacting the metal with the carbon of the fibres.
  • a method as claimed in claim 3 wherein the coating is produced by a metal halide vapour deposition method.

Abstract

A process of producing a metal and carbon fibre composite in which carbon fibres are treated to produce a very thin coating on the surface and the treated fibres are then wetted by metal melts to which a particular alloying metal has been added. The fibres are treated with a metal carbide and the alloying metal is preferably of the same metal as that of the carbide. The carbon fibres are infiltrated into the matrix metal while the latter is in a molten state and the invention is particularly concerned with the production of a wetting interface between the metal alloys and the carbon fibres. The method enables shaped bodies such as shaft bearings to be made in a convenient manner. The composite may have other forms such as continuous tapes for subsequent assembly into more complex shapes.

Description

Dnited States Patent [1 1 Denham et a1.
[ 1 Aug. 6, 1974 [75] Inventors: Albert W. Denham; Brian A. W. Redfern, both of Derby, England [73] Assignee: British Railways Board, London,
England [22] Filed: Jan. 6, 1972 [21] Appl. No.: 215,785
[52] 11.5. C1 29/419, 29/1912, 29/527.3, 164/97 [51] Int. Cl 1323p 17/04 [58] Field 01 Search 164/97; 29/419, 527.1, 29/5273, 527.5, 191.2
[56] References Cited UNITED STATES PATENTS 3,348,967 10/1967 Hucke 29/1912 X 3,460,920 8/1969 Long et al .1 29/1912 X 3,550,247 12/1970 Evans et al. 29/419 3,553,820 1/1971 Sara I 29/419 3,583,471 6/1971 Kemming 164/97 3,600,163 8/1971 Badia et a1 164/97 X 3,668,748 6/1972 Divecha et al 29/419 FOREIGN PATENTS OR APPLICATIONS 2,016,734 7/1971 Germany 29/1912 Primary Examiner-Charles W. Lanham Assistant Examiner-D. C. Reiley, lll
Attorney, Agent, or Firm-Pollock, Philpitt & Vande Sande [57] ABSTRACT A process of producing a metal and carbon fibre composite in which carbon fibres are treated to produce a very thin coating on the surface and the treated fibres are then wetted by metal melts to which a particular alloying metal has been added. The fibres are treated with a metal carbide and the alloying metal is preferably of the same metal as that of the carbide. The carbon fibres are infiltrated into the matrix metal while the latter is in a molten state and the invention is particularly concerned with the production of a wetting interface between the metal alloys and the carbon fibres. The method enables shaped bodies such as shaft bearings to be made in a convenient manner. The composite may have other forms such as continu ous tapes for subsequent assembly into more complex shapes.
12 Claims, 3 Drawing Figures METHODS OF PRODUCING A TAL AND (I 1t" FIBRE COSITE This invention is concerned with the production of metal and carbon fibre composites using molten metal techniques in which the carbon fibres are infiltrated into a matrix metal while the latter is in a molten state.
The purpose of producing metal and carbon fibre composites is essentially to maintain the mechanical properties of the metal and combine them with the anisotropic strengthening influence of carbon fibres.
Metal and carbon fibre composites can only be fabricated without the application of large pressures if the metal in the molten state wets the fibres. However, most engineering metals do not wet carbon fibres.
It is the object of this invention to provide a statisfactory wetting system. Such a wetting system will display several advantages. Infiltration of the carbon fibres into the matrix of the metal will be complete producing a composite with sustantially no porosity. Conventional molten metal casting techniques can be employed to produce the composites. The manufacturing process will be rapid. Continuous production of metal and carbon fibre composites in the form of tapes for subsequent assembly into complex shapes becomes possible.
According to the invention a method of producing a metal and carbon fibre composite by a molten metal technique includes the use of carbon fibres having a coating of a carbide of titanium vanadium, hafnium, tantalum, zirconium, niobium or of other monocarbide forming metals or of chromium.
Such a coating will by itself provide a reasonably satisfactory wetting system for certain matrix metals such as aluminium. However in further advantageous development of the invention a small addition of one of the aforesaid metals is added to the matrix metal.
The coating on the carbon fibres and the addition to the matrix metal of one of the aforesaid metals will produce a chemical bond across the carbon fibre-metal interface. Particularly in the case of low melting point metals this will allow high temperature strength to be retained and will prevent dewetting if a subsequent local melting occurs in, for example, a hot pressing treatment.
Preferably the carbide coating on the fibres is formed by reacting the carbide forming metal with the carbon of the fibres for example using a metal halide vapour deposition method.
Depending upon the matrix metal and the added metal used, the added metal will either be present in solid solution in the matrix metal or as an intermetallic compound with the matrix metal. When in solid solution, it is preferable that there is at least 0.05 percent by weight added metal in solid solution. When forming an intermetallic compound, it is preferable that the melt into which the coated carbon fibres are infiltrated is maintained above 700C.
It is advantageous if the coating is continuous and does not exceed 500 A thickness.
In experiments so far conducted, titanium has been found to be the most suitable both for use as the carbide coating on the carbon fibres and as the metal added to the matrix metal.
Matrix metals to which the invention may be applied include, for example tin-lead alloy, which brings the application of the invention into the field of plain bearings as will be described, and also include copper, aluminium and magnesium which bring the application of the invention into the field of structural artifacts.
The invention will now be further explained by way of example in which titanium is used as the carbide forming metal on the carbon fibres and is also used as the metal added to the matrix metal.
A carbide coating is formed on the carbon fibres by a reaction of titanium with the carbon of the fibres using a titanium iodide vapour deposition method. The reaction can be expressed as:
Til; C Til Ti C.
For this process to occur (where G denotes Gibbs Free Energy change) AG reaction formation 'Ii! formation TiC lormation In the temperature range 700C 1,000C, A Gdmmp m: is positive but Gmwm" is negative so the titanium is deposited specifically onto the carbon, forming titanium carbide.
The coating is adherent to the carbon fibre and evenly distributed. The particle size is A 500A and the thickness can be controlled to the same order.
The coating is brittle and weaker than the carbon fibre but provided the thickness is kept below 500A degradation in strength is acceptable.
The carbon fibres. are coated by passing them through a reaction furnace one or two tows at a time in an atmosphere of argon, the tows each consisting of for example 10,000 fibres.
The reaction chamber is isolated by using liquid traps either side, these keep the reactants, namely titanium and iodine, in and oxygen out. The fibres pass through constructions on the inlet and outlet passages of the furnace to prevent seepage of iodide from the furnace.
At an operating temperature of 950C, with a titanium to iodine ratio of 5 l, titanium iodide is formed and reacts with the carbon as described above and the coating rate and hence the speed at which the tows are pulled through the reaction chamber is 25 feet per hour.
Similar considerations of thermodynamic data show that the process could be adopted for other carbide forming metals notably chromium, niobium, zirconium, molybdenum using the iodides and other halides. Titanium, however, produces the most adherent and continuous carbide coating and the iodide process allows a greater measure of control over coating thickness.
The titanium carbide coated fibres thus formed are infiltrated into a matrix metal using conventional molten metal casting techniques, a small addition of titanium having been added to the matrix metal. The presence of the titanium carbide coating and the added titanium metal ensure a satisfactory wetting interface between the carbon fibres and the matrix metal.
Two main possibilities exists for ensuring that the titanium is present in the melt of a particular matrix metal, which may itself be an alloy. It may be in solid solution and will therefore be released at the melting point of the alloy. Cu alloys offer such a system when the titanium is present at least by 0.5 percent by weight. Alternatively titanium may have restricted solid solution in a metal alloy and the chemical thermodynamics may favour the formation of an intermetallic coma conventional white metal alloy bearing and gave the following result on a standard Amsler test machine.
pound. When such an alloy melts, the solubility of the intermetallic compound in the liquid metal (and therefore the availability of the titanium) may be very low and consequently temperatures in excess of the alloy matrix melting point may be reached before wetting occurs. For example the alloy system which is the basis of white metal bearing alloys, tin-lead, when combined with 0.5 percent titanium by weight forms a tintitanium intermetallic compound, which does not have appreciable solubility in the melt until about 800C. To produce a composite in this alloy, the melt is superheated to this temperature before casting into it the coated carbon fibres.
The tensile properties of composites produced in the manner described above compare favourably with those produced by alternative methods. The characteristics of the fracture surfaces in copper, tin-lead and aluminium alloy composites show no pull out of fibres which would infer that a good bond exists between the carbon fibres and the metal matrices.
One application of a composite produced as described above in a plain bearing will now be described by way of example with reference to the accompanying drawing in which:
FIG. 1 is a perspective view of the bearing,
FIG. 2 is a cross-sectional view of the bearing, and
FlG. 3 is a longitudinal sectional view.
The bearing has a body 1 and incorporates a bearing insert 2. The insert 2 comprises a tin-lead alloy and carbon fibre composite bonded to a tin-lead alloy block.
To form the insert 2, coated carbon fibres represented at 3 coated with titanium carbide by the method described above are placed in a silica mould in the neck of which is contained the matrix metal alloy having a nominal composition by weight of 8 percent tin 0.5 percent titanium and the remainder lead. The alloy is melted in the neck by radio frequency (RF) heating until it has all flowed into the cylindrical mould containing the coated carbon fibres and forms a composite, i.e., a strip of matrix metal into which the fibres have been infiltrated. To ensure optimum distribution, the mould is vibrated. The cast composite thus formed containing 10 percent by volume of carbon fibres is then placed in a mould and bonded by melting to the tinlead alloy block to form a test specimen, so that the carbon fibres are concentrated near the bearing surface 4 and extend parallel to the bearing surface.
A bearing incorporating an insert 2 was tested against We claim:
1. Method of forming a metal and carbon fibre composite which comprises coating the carbon fibres with a carbide of a member selected from the group consisting of titanium, vanadium, hafnium, tantalum, zirconium, niobium, other monocarbide forming metals, and chromium; then employing a molten technique to cause infiltration of the coated carbon fibres into a matrix metal while the matrix metal is in a molten state, and obtaining said metal and carbon fibre composite.
2. A method as claimed in claim 1, wherein the coating is continuous and does not exceed 500 A thickness.
3. A method as claimed in claim 1, wherein the coating is formed as a preliminary step by reacting the metal with the carbon of the fibres.
4. A method as claimed in claim 3 wherein the coating is produced by a metal halide vapour deposition method.
5. A method as claimed in claim 1, wherein an amount of at least one of the metals specified is added to the matrix metal.
6. A method as claimed in claim 5, wherein the metal added to the matrix is the same as that forming the carbide coating on the carbon fibres.
7. A method as claimed in claim 5 in which the added metal is insolid solution in the matrix metal in an amount of at least 0.05 percent by weight of the whole.
8. A method as claimed in claim 5, wherein the matrix metal is copper or a copper alloy and the added metal is titanium.
9. A method as claimed in claim 5, wherein the added metal forms an intermetallic compound with the matrix metal and the melt into which the carbon fibres are infiltrated is maintained at a temperature high enough to release the added metal from the intermetallic compound.
10. A method as claimed in claim 5, wherein the matrix metal is a tin lead alloy and the added metal is titamum.
11. A method as claimed in claim 5, wherein the matrix metal is aluminium and the added metal is titanium.
12. A method as claimed in claim 5, wherein the matrix metal is magnesium and the added metal is tita-

Claims (11)

  1. 2. A method as claimed in claim 1, wherein the coating is continuous and does not exceed 500 A thickness.
  2. 3. A method as claimed in claim 1, wherein the coating is formed as a preliminary step by reacting the metal with the carbon of the fibres.
  3. 4. A method as claimed in claim 3 wherein the coating is produced by a metal halide vapour deposition method.
  4. 5. A methOd as claimed in claim 1, wherein an amount of at least one of the metals specified is added to the matrix metal.
  5. 6. A method as claimed in claim 5, wherein the metal added to the matrix is the same as that forming the carbide coating on the carbon fibres.
  6. 7. A method as claimed in claim 5 in which the added metal is insolid solution in the matrix metal in an amount of at least 0.05 percent by weight of the whole.
  7. 8. A method as claimed in claim 5, wherein the matrix metal is copper or a copper alloy and the added metal is titanium.
  8. 9. A method as claimed in claim 5, wherein the added metal forms an intermetallic compound with the matrix metal and the melt into which the carbon fibres are infiltrated is maintained at a temperature high enough to release the added metal from the intermetallic compound.
  9. 10. A method as claimed in claim 5, wherein the matrix metal is a tin lead alloy and the added metal is titanium.
  10. 11. A method as claimed in claim 5, wherein the matrix metal is aluminium and the added metal is titanium.
  11. 12. A method as claimed in claim 5, wherein the matrix metal is magnesium and the added metal is titanium.
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US3907514A (en) * 1972-10-19 1975-09-23 Pure Carbon Company Inc Aluminum carbon composite seal material
US3929427A (en) * 1972-07-10 1975-12-30 Union Carbide Corp Wear-resistant surface composite materials and method for producing same
US4056874A (en) * 1976-05-13 1977-11-08 Celanese Corporation Process for the production of carbon fiber reinforced magnesium composite articles
US4083719A (en) * 1975-10-29 1978-04-11 Hitachi, Ltd. Copper-carbon fiber composites and process for preparation thereof
US4134759A (en) * 1976-09-01 1979-01-16 The Research Institute For Iron, Steel And Other Metals Of The Tohoku University Light metal matrix composite materials reinforced with silicon carbide fibers
US4180399A (en) * 1976-09-28 1979-12-25 The Foundation: The Research Institute For Special Inorganic Materials Molybdenum base composite materials reinforced with continuous silicon carbide fibers and a method for producing the same
US4609449A (en) * 1982-03-16 1986-09-02 American Cyanamid Company Apparatus for the production of continuous yarns or tows comprising high strength metal coated fibers
US4747873A (en) * 1986-06-13 1988-05-31 Akebono Brake Industry Co., Ltd. Frictional material
US4831707A (en) * 1980-11-14 1989-05-23 Fiber Materials, Inc. Method of preparing metal matrix composite materials using metallo-organic solutions for fiber pre-treatment
US5244748A (en) * 1989-01-27 1993-09-14 Technical Research Associates, Inc. Metal matrix coated fiber composites and the methods of manufacturing such composites
EP0567284A2 (en) * 1992-04-21 1993-10-27 Inco Limited Aluminium-base metal matrix composite
US5410796A (en) * 1993-10-06 1995-05-02 Technical Research Associates, Inc. Copper/copper alloy and graphite fiber composite and method
US6735842B1 (en) * 1999-03-08 2004-05-18 Man Technologie Ag Movable structural component for a thermomechanically stressed assembly as well as a process for producing the structural component
US20170307454A1 (en) * 2014-10-20 2017-10-26 Bae Systems Plc Strain sensing in composite materials
CN107675108A (en) * 2017-09-05 2018-02-09 巩义市泛锐熠辉复合材料有限公司 A kind of preparation method of composite carbon-copper material
USD1009509S1 (en) * 2021-10-29 2024-01-02 Bernard H. Cohen Soap holder

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