US3473900A - Aluminum-carbon fiber composites - Google Patents

Aluminum-carbon fiber composites Download PDF

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Publication number
US3473900A
US3473900A US617662A US3473900DA US3473900A US 3473900 A US3473900 A US 3473900A US 617662 A US617662 A US 617662A US 3473900D A US3473900D A US 3473900DA US 3473900 A US3473900 A US 3473900A
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United States
Prior art keywords
fibres
aluminum
tantalum
carbon
fibers
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
US617662A
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English (en)
Inventor
Raymond V Sara
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BP Corp North America Inc
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Union Carbide Corp
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Assigned to AMOCO CORPORATION, A CORP. OF INDIANA reassignment AMOCO CORPORATION, A CORP. OF INDIANA ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: UNION CARBIDE CORPORATION
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/02—Pretreatment of the fibres or filaments
    • C22C47/04—Pretreatment of the fibres or filaments by coating, e.g. with a protective or activated covering
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S428/00—Stock material or miscellaneous articles
    • Y10S428/922—Static electricity metal bleed-off metallic stock
    • Y10S428/923—Physical dimension
    • Y10S428/924—Composite
    • Y10S428/926—Thickness of individual layer specified
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12444—Embodying fibers interengaged or between layers [e.g., paper, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12625—Free carbon containing component
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y10T428/12743—Next to refractory [Group IVB, VB, or VIB] metal-base component
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component
    • Y10T428/12819—Group VB metal-base component
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/29—Coated or structually defined flake, particle, cell, strand, strand portion, rod, filament, macroscopic fiber or mass thereof
    • Y10T428/2913—Rod, strand, filament or fiber
    • Y10T428/2918—Rod, strand, filament or fiber including free carbon or carbide or therewith [not as steel]

Definitions

  • the present invention relates to a composite refractory article which is made up of a plurality of high modulus, high strength carbon fibers which are completely coated with a thin layer of tantalum and bonded together by an aluminum matrix.
  • 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.
  • aluminum does not wet pure graphite for all practical purposes unless aluminum carbide is formed at the interface. Such an aluminum carbide phase cannot be tolerated due to its thermochemical instability.
  • the carbon fiber-aluminum composite article of the invention comprises a plurality of carbon iibers each of which is coated with a thin layer ofi tantalum and bonded together, preferably in a side-by-side or parallel manner, with an aluminum binder or matrix.
  • this composite article may be provided by a process which comprises coating carbon fibers with a thin but continuous film of tantalum, compacting the socalled fibers into the desired form, infiltrating the voids between the compacted fibers with molten aluminum and cooling the resultant aluminum infiltrated tantalum coated 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.
  • a rectangular composite article 1 consisting of aligned graphite fibers 2 having disposed on their surface a continuous one to two micron thick coating of tantalum 3. These so-coated fibers are bonded together by an aluminum matrix 4.
  • the graphite fibers 2 are approximately two inches in length and disposed in the aluminum matrix 4 in a parallel or side-by-side manner. The length dimension of the fibers 2 is perpendicular to surface of the drawing.
  • 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 mono-filament form. Carbon textiles are available commercially and are generally produced by the techniques described in U.S. Patents 3,107,152 and 3,116,975, among others.
  • Tantalum can be deposited on the carbon fibers by a variety of methods.
  • the techniques available for accomplishing this include electrodeposition from a fused salt bath, thermal decomposition of the appropriate metal halide 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 tantalum coating and the carbon fiber substrate. Such a bond is a highly desirable feature in carbon fiber-metal matrix composites.
  • Thermal decomposition of the appropriate halide requires a heating of the carbon fiber substrate and, accordingly, somewhat limits the type of shapes which can be coated with tantalum in this manner.
  • Electrodeposition of tantalum from a fused salt bath is an ideal way of coating carbon fibers with a thin film of tantalum but this technique is limited to rather simple carbon fiber configurations.
  • a carbon yarn material which had been heated to graphitizing temperatures was cut into 2 inch lengths.
  • a tantalum coating averaging from 0.2 to 2.0 microns was electrodeposited on these fibers by a technique similar to that described in co-pending US. patent application Ser. No. 609,683 which has been assigned to the same assignee as the instant application.
  • These tantalum clad fibers were then placed in an aligned position (all parallel) in a cylindrical capillary tube which was provided with a top and bottom closure.
  • the surface of the cylinder was provided with randomly placed holes or openings to facilitate the ingress of aluminum into the cylinder and hence into the voids between the aligned carbon fibers.
  • the cylinder containing the carbon fibers in a preselected form was placed into an air tight chamber which also contained a vessel of aluminum.
  • The. chamber was then evacuated to a pressure of approximately 2X10" mm. of mercury to out gas the carbon fibers.
  • the aluminum was heated to a temperature of approximately 700 C.
  • the cylinder containing the aligned fibers was submerged below the surface of the molten aluminum.
  • the chamber was then filled with argon gas to a pressure of about one atmosphere to insure that molten aluminum filled essentially all the voids between the aligned carbon fibers. After about thirty seconds of pressurizing the specimen, the capsule was withdrawn from the molten aluminum, cooled and removed from the chamber.
  • a metallographic examination of the resultant composite showed that aluminum readily wet the tantalum clad fibers and incorporated them into the matrix without disturbing the tantalum coating and, more importantly, without the formation of a reaction zone at the aluminum-tantalum interface.
  • Composite so-produced are extremely useful as materials of construction for subsonic and supersonic aricraft, space system components and various propulsion devices.
  • 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.
  • the thickness of the tantalum 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.
  • graphite fibers and fabrics are preferred in the practice of the instant invention, nongraphitic carbon fibers and fabrics may also be employed.
  • other methods of infiltrating the tantalum clad carbon fibers with aluminum will readily suggest themselves to the skilled artisan.
  • carbon as used herein and in the appended claims is meant to include both the non-graphitic and graphitic forms of carbon.
  • a refractory composite article comprising a plurality of carbon fibers bonded together by an essentially aluminum matrix, said carbon fibers having a continuous coating consisting essentially of tantalum on their outer surface so as to prevent said aluminum matrix from being in direct contact with said carbon fibers.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Chemical Or Physical Treatment Of Fibers (AREA)
US617662A 1967-02-21 1967-02-21 Aluminum-carbon fiber composites Expired - Lifetime US3473900A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US61766267A 1967-02-21 1967-02-21

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Country Status (4)

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US (1) US3473900A (de)
DE (1) DE1621379B2 (de)
FR (1) FR1559658A (de)
GB (1) GB1185349A (de)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3623981A (en) * 1967-05-04 1971-11-30 Nat Res Dev Composite bearing materials
US3674689A (en) * 1969-06-25 1972-07-04 Nat Res Dev Carbon fiber filled composite materials
US3720257A (en) * 1970-01-07 1973-03-13 Bbc Brown Boveri & Cie Method of producing carbon fiber-reinforced metal
US3871834A (en) * 1970-12-25 1975-03-18 Hitachi Ltd Carbon-fiber-reinforced aluminum composite material
US3894677A (en) * 1971-03-24 1975-07-15 Nasa Method of preparing graphite reinforced aluminum composite
US3936277A (en) * 1970-04-09 1976-02-03 Mcdonnell Douglas Corporation Aluminum alloy-boron fiber composite
US3949804A (en) * 1973-03-26 1976-04-13 Toyota Jidosha Kogyo Kabushiki Kaisha Method of manufacturing a metal-impregnated body
JPS5138643B1 (de) * 1970-09-30 1976-10-22
US4058052A (en) * 1971-08-30 1977-11-15 Hart Mark M Cooking grill and briquettes therefor
US4364300A (en) * 1978-06-26 1982-12-21 The United States Of America As Represented By The Secretary Of The Army Composite cored combat vehicle armor
US4534400A (en) * 1981-09-16 1985-08-13 Honda Giken Kogyo Kabushiki Kaisha Method for making a reinforced article for an internal combustion engine
US4578287A (en) * 1984-10-09 1986-03-25 The United States Of America As Represented By The Secretary Of The Navy Process for producing graphite fiber/aluminum-magnesium matrix composites
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
US4661403A (en) * 1982-03-16 1987-04-28 American Cyanamid Company Yarns and tows comprising high strength metal coated fibers, process for their production, and articles made therefrom
US4892130A (en) * 1981-09-16 1990-01-09 Honda Giken Kogyo Kabushiki Kaisha Method for making a reinforced article for an internal combustion engine
US4909910A (en) * 1982-03-16 1990-03-20 American Cyanamid Yarns and tows comprising high strength metal coated fibers, process for their production, and articles made therefrom
US6466414B1 (en) * 2000-08-29 2002-10-15 International Business Machines Corporation Continuously wound fiber-reinforced disk drive actuator assembly
EP2208706A1 (de) * 2007-09-18 2010-07-21 Shimane Prefectural Government Metallbeschichtetes kohlenstoffmaterial und kohlenstoff-metall-verbundwerkstoff mit dem metallbeschichteten kohlenstoffmaterial

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5260222A (en) * 1975-09-30 1977-05-18 Honda Motor Co Ltd Method of manufacturing fibre reinforced composite
JPS5292827A (en) * 1976-01-16 1977-08-04 Honda Motor Co Ltd Method of manufacturing structures with fiber reinforced composite parts
DE3100950C2 (de) * 1981-01-14 1985-03-28 Respublikanskij gosudarstvennyj institut po proektirovaniju ob"ektov proizvodstvennoj bazy vodochozjajstvennych organizacij "Rosgiprovodprom", Rostov-na-Donu Vorrichtung zum Innenemaillieren von Hohlgefäßen
GB2219006A (en) * 1988-05-26 1989-11-29 Rolls Royce Plc Coated fibre for use in a metal matrix
GB2222793A (en) * 1988-09-16 1990-03-21 British Aerospace "Method of forming a fibre reinforced material"
US5017438A (en) * 1989-12-22 1991-05-21 General Electric Company Silicon carbide filament reinforced titanium aluminide matrix with reduced cracking tendency
CA2060520A1 (en) * 1991-03-11 1994-12-09 Jonathan G. Storer Metal matrix composites

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2683671A (en) * 1952-07-17 1954-07-13 Westinghouse Electric Corp Low primary and secondary electron emission surface
US2699415A (en) * 1953-02-25 1955-01-11 Owens Corning Fiberglass Corp Method of producing refractory fiber laminate
US2920385A (en) * 1956-02-08 1960-01-12 Borg Warner Process of bonding carbon to aluminum
US3085317A (en) * 1959-12-31 1963-04-16 Union Carbide Corp Coated graphite bodies
US3098723A (en) * 1960-01-18 1963-07-23 Rand Corp Novel structural composite material
US3384463A (en) * 1965-03-22 1968-05-21 Dow Chemical Co Graphite metal body composite

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2683671A (en) * 1952-07-17 1954-07-13 Westinghouse Electric Corp Low primary and secondary electron emission surface
US2699415A (en) * 1953-02-25 1955-01-11 Owens Corning Fiberglass Corp Method of producing refractory fiber laminate
US2920385A (en) * 1956-02-08 1960-01-12 Borg Warner Process of bonding carbon to aluminum
US3085317A (en) * 1959-12-31 1963-04-16 Union Carbide Corp Coated graphite bodies
US3098723A (en) * 1960-01-18 1963-07-23 Rand Corp Novel structural composite material
US3384463A (en) * 1965-03-22 1968-05-21 Dow Chemical Co Graphite metal body composite

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3623981A (en) * 1967-05-04 1971-11-30 Nat Res Dev Composite bearing materials
US3674689A (en) * 1969-06-25 1972-07-04 Nat Res Dev Carbon fiber filled composite materials
US3720257A (en) * 1970-01-07 1973-03-13 Bbc Brown Boveri & Cie Method of producing carbon fiber-reinforced metal
US3936277A (en) * 1970-04-09 1976-02-03 Mcdonnell Douglas Corporation Aluminum alloy-boron fiber composite
JPS5138643B1 (de) * 1970-09-30 1976-10-22
US3871834A (en) * 1970-12-25 1975-03-18 Hitachi Ltd Carbon-fiber-reinforced aluminum composite material
US3894677A (en) * 1971-03-24 1975-07-15 Nasa Method of preparing graphite reinforced aluminum composite
US4058052A (en) * 1971-08-30 1977-11-15 Hart Mark M Cooking grill and briquettes therefor
US3949804A (en) * 1973-03-26 1976-04-13 Toyota Jidosha Kogyo Kabushiki Kaisha Method of manufacturing a metal-impregnated body
US4364300A (en) * 1978-06-26 1982-12-21 The United States Of America As Represented By The Secretary Of The Army Composite cored combat vehicle armor
US4534400A (en) * 1981-09-16 1985-08-13 Honda Giken Kogyo Kabushiki Kaisha Method for making a reinforced article for an internal combustion engine
US4892130A (en) * 1981-09-16 1990-01-09 Honda Giken Kogyo Kabushiki Kaisha Method for making a reinforced article for an internal combustion engine
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
US4661403A (en) * 1982-03-16 1987-04-28 American Cyanamid Company Yarns and tows comprising high strength metal coated fibers, process for their production, and articles made therefrom
US4909910A (en) * 1982-03-16 1990-03-20 American Cyanamid Yarns and tows comprising high strength metal coated fibers, process for their production, and articles made therefrom
US4578287A (en) * 1984-10-09 1986-03-25 The United States Of America As Represented By The Secretary Of The Navy Process for producing graphite fiber/aluminum-magnesium matrix composites
US6466414B1 (en) * 2000-08-29 2002-10-15 International Business Machines Corporation Continuously wound fiber-reinforced disk drive actuator assembly
EP2208706A1 (de) * 2007-09-18 2010-07-21 Shimane Prefectural Government Metallbeschichtetes kohlenstoffmaterial und kohlenstoff-metall-verbundwerkstoff mit dem metallbeschichteten kohlenstoffmaterial
EP2208706A4 (de) * 2007-09-18 2013-03-27 Shimane Prefectural Government Metallbeschichtetes kohlenstoffmaterial und kohlenstoff-metall-verbundwerkstoff mit dem metallbeschichteten kohlenstoffmaterial

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Publication number Publication date
FR1559658A (de) 1969-03-14
GB1185349A (en) 1970-03-25
DE1621379A1 (de) 1972-05-04
DE1621379B2 (de) 1972-05-04

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Owner name: AMOCO CORPORATION, A CORP. OF INDIANA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:UNION CARBIDE CORPORATION;REEL/FRAME:004634/0001

Effective date: 19860620