EP0922779B1 - Metallmatrixverbundkörper mit hoher Steifigkeit und hoher Stabilität in Längsrichtung - Google Patents

Metallmatrixverbundkörper mit hoher Steifigkeit und hoher Stabilität in Längsrichtung Download PDF

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Publication number
EP0922779B1
EP0922779B1 EP98403009A EP98403009A EP0922779B1 EP 0922779 B1 EP0922779 B1 EP 0922779B1 EP 98403009 A EP98403009 A EP 98403009A EP 98403009 A EP98403009 A EP 98403009A EP 0922779 B1 EP0922779 B1 EP 0922779B1
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EP
European Patent Office
Prior art keywords
approximately
ultra
high modulus
fibres
matrix
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
EP98403009A
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English (en)
French (fr)
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EP0922779A1 (de
Inventor
Laetitia Billaud
Jocelyn Gaudin
Martine Nivet Lutz
Joel Poncy
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Airbus Group SAS
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Airbus Group SAS
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Publication date
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Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • C22C47/08—Making alloys containing metallic or non-metallic fibres or filaments by contacting the fibres or filaments with molten metal, e.g. by infiltrating the fibres or filaments placed in a mould
    • 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
    • C22C47/06—Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
    • C22C47/062—Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element from wires or filaments only
    • C22C47/068—Aligning wires
    • 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
    • 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
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
    • Y10T428/249927—Fiber embedded in a metal matrix
    • 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
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
    • Y10T428/249928—Fiber embedded in a ceramic, glass, or carbon matrix
    • Y10T428/249929—Fibers are aligned substantially parallel
    • 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
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
    • Y10T428/249928—Fiber embedded in a ceramic, glass, or carbon matrix
    • Y10T428/249931—Free metal or alloy fiber
    • 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
    • Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
    • Y10T442/30—Woven fabric [i.e., woven strand or strip material]
    • Y10T442/3382—Including a free metal or alloy constituent
    • 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
    • Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
    • Y10T442/60—Nonwoven fabric [i.e., nonwoven strand or fiber material]
    • Y10T442/654—Including a free metal or alloy constituent

Definitions

  • the invention relates to an elongated part, made of a composite material including a matrix metallic based on aluminum or magnesium, as well as continuous carbon fibers arranged in layers superimposed.
  • fibers continuous means fibers of great length, which extend continuously from one end to the other of the room or on its entire periphery or its periphery, according to the orientation given to the fibers inside the room.
  • elongated piece means any part (plate, rod, tube, etc.) with greater dimension in one direction given, called “longitudinal direction”, according to which efforts must be transmitted.
  • tablette here means, by convention, any layer of woven or non-woven fibers, whatever its manufacturing method (draping, winding, etc.).
  • the part in composite material with metallic matrix according to the invention is particularly suitable for uses in the space industry and, from more generally, to any use involving a great dimensional stability.
  • the launcher transmits thrust forces to the spacecraft and intense vibrations.
  • Parts made of matrix composite material organic are much less sensitive to variations temperatures and may exhibit rigidity raised in the longitudinal direction of the workpiece.
  • they have the notable disadvantage, when they arrive in a vacuum, to gradually desorb the water they adsorbed when they found on earth. This progressive desorption is translated by dimensional variations of the part. It requires following very penalizing procedures during the manufacture of the spacecraft. She drives also to equip this machine with more or less complex to reposition the devices high precision, when in space.
  • these are delicate operations and energy consuming, which can affect reliability of the machine and reduce its lifespan.
  • this article recommends the use of fibers with ultra-high modulus carbon, and it announces that an elementary ply or "fold" having a coefficient of longitudinal thermal expansion ⁇ L of 1.10 -6 / ° C (magnesium matrix) or 1.27.10 -6 / ° C (aluminum matrix) and an EL longitudinal traction module of 280 GPa (magnesium matrix) or 302 GPa (aluminum matrix) could be obtained.
  • the molten magnesium alloy is then poured into the cavity, at around 700 ° C, then a piston also preheated to around 200 ° C, is pressed on the top of the mold, in order to compress the molten alloy and to force it to enter the fiber bundle, when the device cools down. After ascent of the piston, the solidified part is extracted towards the high by a pusher. The final piece is obtained by machining during which the housing is eliminated.
  • the subject of the invention is precisely a part made of a metal matrix composite material, the original design allows it to present both high rigidity and great dimensional stability, in particular so that it can be used in space, to support high precision devices.
  • this result is obtained by means of a part made of a metal matrix composite material, elongated shape in a given direction, characterized by the fact that it comprises from 35% to 45% by volume of an aluminum alloy matrix and, respectively, from 65% to 55% by volume of continuous fibers carbon arranged in successive layers in parallel in said direction, at least about 90% of carbon fibers being ultra high modulus fibers having a tensile modulus at least equal to approximately 650 GPa, said ultra-high modulus fibers being oriented to 0 ° ⁇ 5 ° in about 25% to about 60% of the water tables, and between ⁇ 20 ° and ⁇ 40 ° in the other layers, compared to said direction.
  • the alloy-based matrix aluminum is preferably made of an AG10 type alloy, containing in particular approximately 10% by volume of magnesium.
  • ultra high modulus fibers are then oriented at 0 ° ⁇ 5 ° in 45% to 55% of tablecloths and, preferably, in about 50% of the tablecloths.
  • ultra-high modulus fibers are advantageously oriented around ⁇ 25 ° in the others plies.
  • the characteristics targeted are achieved using a piece of matrix composite material metallic, elongated in a given direction, comprising an alloy matrix based on magnesium and continuous carbon fibers, arranged in successive layers parallel to said direction, characterized in that it comprises, respectively, 35% to 45% by volume of said matrix and from 65% to 55% by volume of said fibers, at least about 90% of the carbon fibers being ultra high modulus fibers, having a tensile modulus at least equal to approximately 650 GPa, said ultra-high modulus fibers being oriented at 0 ° ⁇ 5 ° with respect to said direction in at least 90% of the tablecloths.
  • the alloy matrix based on magnesium is preferably an alloy of the type GA9Z1, containing in particular around 9% by volume aluminum.
  • ultra high modulus fibers are then oriented at 0 ° ⁇ 5 ° in about 100% of plies.
  • the parts have almost perfect stability at least in the longitudinal direction.
  • the coefficient of thermal expansion ⁇ L in the longitudinal direction is practically zero. Indeed, its absolute value is less than 0.2.10 -6 / ° C, or close to this value.
  • a part according to the invention has a high specific stiffness in the direction longitudinal above. More specifically, the rigidity specific in this direction being defined as the ratio between the longitudinal traction module EL and the relative density ⁇ , this ratio is, in in most cases, more than 100 MPa.
  • the tablecloths are fabrics, for example of the taffeta type, comprising around 90% of warp threads, made up of continuous ultra high modulus carbon fibers and about 10% of weft threads, made up of other continuous carbon fibers, of lower modulus.
  • the weft yarns have the particular function of maintaining the sons of chain.
  • the sheets are arranged according to mirror symmetry with respect to a longitudinal surface median, parallel to the longitudinal direction.
  • this part must be made of a composite material with metal matrix having characteristics well determined.
  • very high specific rigidity in the direction of its length means a relationship between the tensile modulus EL and the relative density ⁇ generally greater than 100 GPa in this direction. In the preferred embodiments which will be described, this objective is achieved since the rigidity specific measured in the longitudinal direction is, as the case may be, 119 GPa (aluminum-based matrix) or 197 (magnesium base matrix).
  • the expression "practically perfect dimensional stability in the direction of its length” means that the absolute value of the coefficient of longitudinal thermal expansion ⁇ L is generally less than 0.2.10 -6 / ° C. In the preferred embodiments, this result is also achieved, since the absolute value of the measured coefficient of longitudinal thermal expansion is, as the case may be, 0.08.10 -6 / ° C (aluminum-based matrix) or 0 , 01.10 -6 / ° C (magnesium-based matrix).
  • the composite material used to make an elongated piece includes an aluminum-based alloy matrix or magnesium, as well as continuous carbon fibers which are arranged in successive layers, in parallel to the longitudinal direction of the part.
  • the matrix and the fibers make up approximately 40% and approximately 60% of the total volume of the room. If the room includes one or several inserts made of another material, by metallic example, this volume proportion does not concerns that the part of the part made of material composite.
  • the alloy in which the matrix is an aluminum alloy containing in particular about 10% by volume of magnesium.
  • Such an alloy is generally known under the name "AG10 alloy”.
  • At least about 90% of the continuous fibers carbon are ultra high fibers. module, i.e. fibers whose tensile modulus is at least equal to around 650 GPa. More specifically, the. continuous carbon fibers are "K139" fibers of the MITSUBISHI Company.
  • ultra high carbon fibers module are oriented between -5 ° and + 5 ° relative to the longitudinal direction of the part in 45 to 55% tablecloths.
  • the fibers of ultra high modulus carbon are alternately oriented in either direction between 20 ° and 40 ° by relative to the longitudinal direction of the part.
  • the part comprises an even number of layers of fibers and these layers are arranged in a mirror symmetry by relative to a median longitudinal area of the part, parallel to the longitudinal direction.
  • This surface is flat or cylindrical, depending on whether the part has a rectangular or circular section, respectively.
  • the fibers with ultra high modulus are parallel to each other and they extend from one end to the other of the room, according to the longitudinal direction thereof.
  • a part in accordance with the invention is produced by first making a fibrous preform, then by infiltrating this preform of the alloy forming the matrix.
  • the completion of the fiber preform depends on the shape of the part to be manufactured.
  • ultra high modulus fibers can be used alone (in the case of a winding), in association with others fibers (in the case of a fabric), or by combining these two processes.
  • all the layers are formed only ultra high modulus fibers, parallel between them in each layer, all of the carbon fibers forming the fibrous matrix is made of ultra ultra fibers high modulus.
  • all the layers are in the form of a fabric in which the ultra high modulus fibers make up the chain, about 90% of the fibers in the fibrous matrix are ultra high modulus fibers.
  • a part of the sheets is formed only of fibers with ultra high modulus and the other layers are formed of tissue. According to the percentage of the tablecloths of each category, the percentage of ultra high modulus fibers in the fibrous preform is then between approximately 90% and 100%.
  • the fibers with ultra high modulus are woven to maintain these fibers together, in the sheet considered, for ensure satisfactory manufacture of the part.
  • a fabric is then produced, by taffeta type example, comprising about 90% of chain yarns made up of carbon fibers ultra high modulus and around 10% of weft yarns, made up of other continuous carbon fibers, lesser module.
  • these other fibers are fibers of the type "M40" or "M50" from the company TORAY.
  • a piece of matrix composite material metal according to the invention is manufactured by pressure foundry.
  • the first embodiment of the invention six different pieces, numbered 1 to 6, of composite material with a metal matrix, of elongated parallelepiped shape, were produced by this pressure foundry technique.
  • the pieces numbered 1 to 5 had the same dimensions of 260mm x 130mm x 3mm.
  • the piece numbered 6 had dimensions of 160 mm x 80 mm x 3 mm. All the parts presented the same matrix in AG10. They differed essentially in the structure of their fibrous preform.
  • the preforms defined in Table I correspond to reference parts, allowing show the importance of fiber orientation to inside the composite material, to get the desired result.
  • Test pieces were then cut with the diamond wheel in each of the pieces thus obtained, to allow in particular mechanical tests and physical measurements.
  • the expression “sense L” means longitudinal direction
  • the expression “sense T” means transverse direction
  • the values given between parentheses indicate the number of tests performed at every time.
  • Exhibit 5 therefore presents the best compromise in order to obtain both a high rigidity and a great stability in the longitudinal direction.
  • the matrix is made of an alloy with magnesium base, containing in particular approximately 9% in volume of aluminum.
  • This alloy is GA9Z1 High type Purity.
  • the matrix and the continuous carbon fibers have respective volume ratios of approximately 40% and around 60%.
  • the fabric comprises approximately 90% by volume of ultra-high modulus carbon fibers, type K 139, placed in the longitudinal direction, and 10% of carbon fibers type M 50, placed in the direction transverse, in order to hold the fibers K 139.
  • the stack of fabric layers is made of in such a way that, in all the layers, the fibers to ultra high modulus are oriented at 0 ° ⁇ 5 ° from to the longitudinal direction of the part.
  • the density of the part 7 was determined at 1.95 g / cm 3 by physical measurements.
  • Table III gives, at room temperature (approximately 20 ° C.), the results of the mechanical and physical measurements carried out (the notations are the same as in Table II). Measured characteristics Symbol Exhibit 7 Young's modulus L (GPa) EL 384 (3) Absolute value of the thermal expansion coefficient in direction L (10-6 / ° C) aL 0.01 (4) Absolute value of the thermal expansion coefficient in direction T (10-6 / ° C) ⁇ T 5.33 (3) Fiber volume rate (%) vf 58.3 ⁇ 2.5 (3)
  • the parts made of composite material with metal matrix according to the invention have mechanical and physical characteristics that allow to consider their use especially in the space industry, for all applications requiring both high rigidity and excellent stability in a longitudinal direction of the room.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Inorganic Fibers (AREA)

Claims (12)

  1. Metallmatrixverbundstoffteil einer in einer gegebenen Richtung gestreckten Form, dadurch gekennzeichnet, dass es jeweils zu 35 bis 45 Vol.-% eine Matrix aus einer Legierung auf Aluminiumbasis und zu 65 bis 55 Vol.-% durchgehende Carbonfasern, die in aufeinanderfolgenden Schichten parallel zu dieser Richtung angeordnet sind, umfasst, wobei mindestens etwa 90 % der Carbonfasern Fasern eines supergroßen Moduls sind, die einen Zugmodul von mindestens gleich etwa 650 GPa aufweisen, wobei die Fasern eines supergroßen Moduls in Bezug auf diese Richtung auf 0° ± 5° in etwa 25 bis etwa 60 % der Schichten und zwischen ± 20° und ± 40° in den anderen Schichten ausgerichtet sind.
  2. Teil nach Anspruch 1, in dem die Matrix aus einer Legierung auf Aluminiumbasis, die etwa 10 Vol.-% Magnesium enthält, besteht.
  3. Teil nach einem der vorhergehenden Ansprüche, in dem die Fasern eines supergroßen Moduls auf 0° ± 5° in 45 bis 55 % der Schichten ausgerichtet sind.
  4. Teil nach Anspruch 3, in dem die Fasern eines supergroßen Moduls auf 0° ± 5° in etwa 50 % der Schichten ausgerichtet sind.
  5. Teil nach einem der vorhergehenden Ansprüche, in dem die Fasern eines supergroßen Moduls auf etwa ± 25° in den anderen Schichten ausgerichtet sind.
  6. Metallmatrixverbundstoffteil einer in einer gegebenen Richtung gestreckten Form, das eine Matrix aus einer Legierung auf Magnesiumbasis und durchgehende Carbonfasern, die in aufeinanderfolgenden Schichten parallel zu dieser Richtung angeordnet sind umfasst, dadurch gekennzeichnet, dass es jeweils zu 35 bis 45 Vol.-% die Matrix und zu 65 bis 55 Vol.-% die Fasern umfasst, wobei mindestens etwa 90 % der Carbonfasern Fasern eines supergroßen Moduls sind, die einen Zugmodul von mindestens gleich etwa 650 GPa aufweisen, wobei die Fasern eines supergroßen Moduls auf 0° ± 5 ° in Bezug auf diese Richtung in mindestens 90 % der Schichten ausgerichtet sind.
  7. Teil nach Anspruch 6, in dem die Matrix eine Legierung auf Magnesiumbasis, die etwa 9 Vol.-% Aluminium enthält, ist.
  8. Teil nach einem der Ansprüche 6 oder 7, in dem die Fasern eines supergroßen Moduls auf 0° ± 5° in etwa 100 % der Schichten ausgerichtet sind.
  9. Teil nach einem der vorhergehenden Ansprüche, in dem mindestens einige der Schichten Gewebe sind, die zu etwa 90 % Kettfäden, die aus den durchgehenden Carbonfasern eines supergroßen Moduls gebildet sind, und zu etwa 10 % Schussfäden, die aus anderen durchgehenden Carbonfasern gebildet sind, eines geringeren Moduls umfassen.
  10. Teil nach einem der vorhergehenden Ansprüche, in dem die Fasern eines supergroßen Moduls sich von einem Ende des Teils bis zum anderen in dieser Richtung erstrecken.
  11. Teil nach einem der vorhergehenden Ansprüche, in dem die Schichten spiegelsymmetrisch bezüglich einer Mittenlängsfläche parallel zu dieser Richtung angelegt sind.
  12. Teil gemäß einem der vorhergehenden Ansprüche, das zu einem Raumfahrzeug gehört.
EP98403009A 1997-12-04 1998-12-01 Metallmatrixverbundkörper mit hoher Steifigkeit und hoher Stabilität in Längsrichtung Expired - Lifetime EP0922779B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9715306 1997-12-04
FR9715306A FR2772049B1 (fr) 1997-12-04 1997-12-04 Piece en materiau composite a matrice metallique a haute rigidite et a grande stabilite dans une direction longitudinale

Publications (2)

Publication Number Publication Date
EP0922779A1 EP0922779A1 (de) 1999-06-16
EP0922779B1 true EP0922779B1 (de) 2002-08-21

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EP98403009A Expired - Lifetime EP0922779B1 (de) 1997-12-04 1998-12-01 Metallmatrixverbundkörper mit hoher Steifigkeit und hoher Stabilität in Längsrichtung

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Country Link
US (1) US6197411B1 (de)
EP (1) EP0922779B1 (de)
JP (1) JP4283359B2 (de)
CA (1) CA2255402A1 (de)
DE (1) DE69807306T2 (de)
ES (1) ES2182246T3 (de)
FR (1) FR2772049B1 (de)
RU (1) RU2217522C2 (de)

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CN108723309A (zh) * 2018-06-25 2018-11-02 牛乾 高强度铝镁合金铸锭及其制备方法

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DE10126926B4 (de) 2001-06-01 2015-02-19 Astrium Gmbh Brennkammer mit Innenmantel aus einem keramischen Komposit-Material und Verfahren zur Herstellung
AT413704B (de) * 2004-06-23 2006-05-15 Arc Leichtmetallkompetenzzentrum Ranshofen Gmbh Kohlenstofffaserverstärktes leichtmetallteil und verfahren zur herstellung desselben
CN100503872C (zh) 2004-11-09 2009-06-24 岛根县 金属基碳纤维复合材料的制造方法
DE102005051269B3 (de) * 2005-10-26 2007-05-31 Infineon Technologies Ag Verbundwerkstoff und Bodenplatte
DE102006023041B4 (de) * 2006-05-17 2015-11-12 Bayerische Motoren Werke Aktiengesellschaft Partikelverstärkte Magnesium- oder Aluminiumlegierung
RU2613830C1 (ru) * 2015-10-07 2017-03-21 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Волокнистый композиционный материал
DE102015221078A1 (de) * 2015-10-28 2017-05-04 Airbus Operations Gmbh Faserverstärktes Metallbauteil für ein Luft- oder Raumfahrzeug und Herstellungsverfahren für faserverstärkte Metallbauteile
ITUA20162826A1 (it) * 2016-04-22 2017-10-22 Freni Brembo Spa Corpo pinza di una pinza per freno a disco
CN107312984A (zh) * 2017-05-16 2017-11-03 苏州莱特复合材料有限公司 一种改性碳纤维增强镁基复合材料及其制备方法
CN107267826A (zh) * 2017-05-16 2017-10-20 苏州莱特复合材料有限公司 一种改性石墨烯增强镁基金属材料及其制备方法
CN110385437B (zh) * 2019-07-03 2021-09-10 西安理工大学 一种定向纤维原位增强钛及其合金支架的制备方法

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JPS613864A (ja) * 1984-06-15 1986-01-09 Toyota Motor Corp 炭素繊維強化マグネシウム合金
DK0536264T3 (da) * 1990-06-29 1995-05-29 Jager Gui G De Fremgangsmåde til fremstilling af armerede kompositmaterialer og filamentmateriale til anvendelse i fremgangsmåden

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108723309A (zh) * 2018-06-25 2018-11-02 牛乾 高强度铝镁合金铸锭及其制备方法
CN108723309B (zh) * 2018-06-25 2021-01-01 临沂利信铝业有限公司 铝镁合金铸锭及其制备方法

Also Published As

Publication number Publication date
CA2255402A1 (fr) 1999-06-04
FR2772049A1 (fr) 1999-06-11
RU2217522C2 (ru) 2003-11-27
JP4283359B2 (ja) 2009-06-24
ES2182246T3 (es) 2003-03-01
DE69807306T2 (de) 2003-04-17
US6197411B1 (en) 2001-03-06
FR2772049B1 (fr) 2000-02-18
EP0922779A1 (de) 1999-06-16
JPH11256254A (ja) 1999-09-21
DE69807306D1 (de) 2002-09-26

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