EP0922779A1 - Metal matrix composite bodies with high stiffness and high stability in a longitudinal direction - Google Patents
Metal matrix composite bodies with high stiffness and high stability in a longitudinal direction Download PDFInfo
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- EP0922779A1 EP0922779A1 EP98403009A EP98403009A EP0922779A1 EP 0922779 A1 EP0922779 A1 EP 0922779A1 EP 98403009 A EP98403009 A EP 98403009A EP 98403009 A EP98403009 A EP 98403009A EP 0922779 A1 EP0922779 A1 EP 0922779A1
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- European Patent Office
- Prior art keywords
- fibers
- ultra high
- high modulus
- matrix
- part according
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Classifications
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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 ultra-high modulus carbon fibers, 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 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, said ultra-high modulus fibers being oriented at 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 of a type alloy AG10, 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 at approximately ⁇ 25 ° in the other tablecloths.
- the characteristics targeted are achieved using a piece of matrix composite material metallic, elongated in a given direction, characterized by the fact that it comprises, respectively, from 35% to 45% by volume of a matrix in alloy based on magnesium and from 65% to 55% by volume continuous carbon fibers, arranged in layers successive parallel to said direction, at least approximately 90% of the carbon fibers being fibers with ultra high modulus, said ultra high modulus fibers being oriented at 0 ° ⁇ 5 ° with respect to said direction in at least 90% of the aquifers.
- the alloy matrix based on magnesium is preferably an alloy of the type GA9Z1, containing in particular approximately 9% by volume of aluminum.
- ultra high modulus fibers are then oriented at 0 ° ⁇ 5 ° in about 100% of tablecloths.
- the parts have almost perfect stability at least in the longitudinal direction. Indeed, like all metallic or metallic matrix parts, there is no adsorption of moisture on the ground, so that its dimensions do not change when the part is placed in a vacuum.
- 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.
- ultra high modulus fibers are fibers having a tensile modulus at least equal to about 650 GPa, and which extend from one end to the other of the part, in its longitudinal direction.
- 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 expressions “approximately 40% “and” around 60% mean that the matrix represents from 35% to 45% of the total volume of the part and that the fibers respectively represent 65% at 55% of this same volume.
- 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 modulus fibers, 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 fabrics. 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 parts 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) ⁇ L 0.01 (4) Absolute value of the thermal expansion coefficient in direction T (10-6 / ° C) ⁇ T 5.33 (3) Fiber volume rate (%) Vf 58.5 ⁇ 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)
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- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Inorganic Fibers (AREA)
Abstract
Description
L'invention concerne une pièce de forme allongée, en un matériau composite incluant une matrice métallique à base d'aluminium ou de magnésium, ainsi que des fibres continues de carbone agencées en nappes superposées.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.
Dans l'ensemble du texte l'expression "fibres continues" désigne des fibres de grande longueur, qui s'étendent sans discontinuité d'une extrémité à l'autre de la pièce ou sur tout son pourtour ou sa périphérie, selon l'orientation donnée aux fibres à l'intérieur de la pièce.Throughout the text the expression "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.
Par ailleurs, l'expression "pièce allongée" désigne toute pièce (plaque, tige, tube, etc.) présentant une plus grande dimension selon une direction donnée, dite "direction longitudinale", selon laquelle des efforts doivent être transmis.Furthermore, the expression "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.
En outre, le terme "nappe" désigne ici, par convention, toute couche de fibres tissées ou non tissées, quel que soit son mode de fabrication (drapage, bobinage, etc.).In addition, the term "tablecloth" here means, by convention, any layer of woven or non-woven fibers, whatever its manufacturing method (draping, winding, etc.).
La pièce en matériau composite à matrice métallique conforme à l'invention est particulièrement adaptée à des utilisations dans l'industrie spatiale et, de façon plus générale, à toute utilisation impliquant une grande stabilité dimensionnelle. 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.
Les différentes pièces de structure des satellites, sondes et autres engins destinés à être utilisés dans l'espace subissent des contraintes, notamment mécaniques et thermiques, particulièrement sévères.The different structural parts of the satellites, probes and other devices intended for use in space are subject to constraints, in particular mechanical and thermal, particularly severe.
Ainsi, lors de l'assemblage et des essais au sol, les effets de la gravité, de l'humidité et de la température doivent être surveillés avec attention.Thus, during assembly and testing at soil, the effects of gravity, humidity and temperature should be carefully monitored.
Pendant la phase de lancement, le lanceur transmet à l'engin spatial des efforts de poussée et des vibrations intenses.During the launch phase, the launcher transmits thrust forces to the spacecraft and intense vibrations.
Enfin, lorsque l'engin est opérationnel, il subit des variations de températures très importantes, selon que ses différentes faces sont ou non éclairées par le soleil. A cette contrainte s'ajoute la mise sous vide de l'engin, qui peut avoir pour conséquence une libération de l'humidité.Finally, when the machine is operational, it undergoes very significant temperature variations, depending on whether its different faces are lit or not by the sun. To this constraint is added the placing under vacuum of the machine, which can result in a release of moisture.
En présence de toutes ces contraintes, la réalisation des pièces de structure pose un problème délicat, notamment lorsqu'elles servent à supporter des appareils de haute précision tels que des miroirs appartenant à des systèmes optiques.In the presence of all these constraints, the realization structural parts pose a delicate problem, especially when they are used to support high-precision devices such as mirrors belonging to optical systems.
Dans ce contexte, il n'existe pas actuellement de matériau présentant, en lui-même, une stabilité dimensionnelle et une rigidité suffisantes pour réaliser des pièces de structure aptes à supporter les contraintes précitées, tout en assurant la précision de positionnement requise. C'est pourquoi des régulateurs thermiques plus ou moins complexes sont parfois associés à de telles pièces.In this context, it does not currently exist of material having, in itself, stability sufficient dimension and rigidity to achieve structural parts capable of supporting the aforementioned constraints, while ensuring the precision of positioning required. This is why regulators more or less complex thermals are sometimes associated to such rooms.
Ainsi, les pièces métalliques présentent toujours un coefficient de dilatation non nul, qui se traduit par une instabilité de positionnement lorsque la pièce subit des variations thermiques. De plus, la rigidité des pièces purement métalliques est généralement insuffisante pour l'application considérée.So the metal parts always have a non-zero coefficient of expansion, which translates by positioning instability when the part undergoes thermal variations. In addition, the stiffness of purely metallic parts is generally insufficient for the application considered.
Les pièces en matériau composite à matrice organique sont beaucoup moins sensibles aux variations de températures et peuvent présenter une rigidité élevée dans la direction longitudinale de la pièce. Cependant, elles ont pour inconvénient notable, lorsqu'elles arrivent dans le vide, de désorber progressivement l'eau qu'elles ont adsorbée lorsqu'elles se trouvaient sur terre. Cette désorbtion progressive se traduit par des variations dimensionnelles de la pièce. Elle impose de suivre des procédures très pénalisantes lors de la fabrication de l'engin spatial. Elle conduit également à équiper cet engin de dispositifs plus ou moins complexes permettant de repositionner les appareils de haute précision, lorsqu'ils se trouvent dans l'espace. Il s'agit toutefois d'opérations délicates et consommatrices d'énergie, ce qui peut affecter la fiabilité de l'engin et en réduire la durée de vie.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. However, 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. However, these are delicate operations and energy consuming, which can affect reliability of the machine and reduce its lifespan.
L'utilisation de pièces en matériau composite à matrice métallique permet, grâce à la présence de fibres continues, d'accroítre sensiblement la rigidité, par rapport aux pièces purement métalliques. De plus, les problèmes de variations dimensionnelles dus à la désorbtion dans le vide sont supprimés. Ces avantages sont exposés, notamment, dans l'article "High Stable Advanced Materials For Space Telescope, An Application Of Metal Matrix Composites" de C. Désagulier et al., IAF-96-I.3.01, dans le cas de composites fibres de carbone-aluminium et fibres de carbone-magnésium. Plus précisément, cet article préconise l'emploi de fibres de carbone à ultra haut module, et il annonce qu'une nappe ou un "pli" élémentaire présentant un coefficient de dilatation thermique longitudinal αL de 1.10-6/°C (matrice magnésium) ou de 1,27.10-6/°C (matrice aluminium) et un module de traction longitudinal EL de 280 GPa (matrice magnésium) ou de 302 GPa (matrice aluminium) a pu être obtenu.The use of parts made of composite material with a metallic matrix makes it possible, thanks to the presence of continuous fibers, to substantially increase the rigidity, compared to purely metal parts. In addition, the problems of dimensional variations due to desorbtion in a vacuum are eliminated. These advantages are explained, in particular, in the article "High Stable Advanced Materials For Space Telescope, An Application Of Metal Matrix Composites" by C. Désagulier et al., IAF-96-I.3.01, in the case of fiber composites. carbon-aluminum and carbon-magnesium fibers. More specifically, this article recommends the use of ultra-high modulus carbon fibers, and it announces that an elementary ply or "fold" having a coefficient of longitudinal thermal expansion αL 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.
Toutefois, aucune technique n'est suggérée en ce qui concerne la réalisation d'une pièce épaisse (ensemble de nappes) devant présenter un coefficient de dilatation thermique longitudinal αL pratiquement nul, c'est-à-dire dont la valeur absolue est, de préférence, inférieure à 0,2. 10-6/°C.However, no technique is suggested with regard to the production of a thick part (set of plies) which must have a practically zero coefficient of longitudinal thermal expansion αL, that is to say the absolute value of which is preferably less than 0.2. 10 -6 / ° C.
L'invention a précisément pour objet une pièce en matériau composite à matrice métallique, dont la conception originale lui permet de présenter à la fois une haute rigidité et une grande stabilité dimensionnelle, afin notamment de pouvoir être utilisée dans l'espace, pour y supporter des appareils de haute précision.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.
Selon une première forme de réalisation de l'invention, ce résultat est obtenu au moyen d'une pièce en matériau composite à matrice métallique, de forme allongée selon une direction donnée, caractérisée par le fait qu'elle comprend de 35 % à 45 % en volume d'une matrice en alliage à base d'aluminium et, respectivement, de 65 % à 55 % en volume de fibres continues de carbone disposées en nappes successives parallèlement à ladite direction, au moins environ 90 % des fibres de carbone étant des fibres à ultra haut module, lesdites fibres à ultra haut module étant orientées à 0° ± 5° dans environ 25 % à environ 60 % des nappes, et entre ± 20° et ± 40° dans les autres nappes, par rapport à ladite direction.According to a first embodiment of the invention, 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, said ultra-high modulus fibers being oriented at 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.
Dans ce cas, la matrice en alliage à base d'aluminium est, de préférence, en un alliage de type AG10, contenant notamment environ 10 % en volume de magnésium.In this case, the alloy-based matrix aluminum is preferably of a type alloy AG10, containing in particular approximately 10% by volume of magnesium.
Avantageusement, les fibres à ultra haut module sont alors orientées à 0° ± 5° dans 45 % à 55 % des nappes et, de préférence, dans environ 50 % des nappes.Advantageously, ultra high modulus fibers are then oriented at 0 ° ± 5 ° in 45% to 55% of tablecloths and, preferably, in about 50% of the tablecloths.
Par ailleurs, les fibres à ultra haut module sont orientées avantageusement à environ ± 25° dans les autres nappes.In addition, ultra high modulus fibers are advantageously oriented at approximately ± 25 ° in the other tablecloths.
Selon une deuxième forme de réalisation de l'invention, les caractéristiques visées sont atteintes au moyen d'une pièce en matériau composite à matrice métallique, de forme allongée selon une direction donnée, caractérisée par le fait qu'elle comprend, respectivement, de 35 % à 45 % en volume d'une matrice en alliage à base de magnésium et de 65 % à 55 % en volume de fibres continues de carbone, disposées en nappes successives parallèlement à ladite direction, au moins environ 90 % des fibres de carbone étant des fibres à ultra haut module, lesdites fibres à ultra haut module étant orientées à 0° ± 5° par rapport à ladite direction dans au moins 90 % des nappes.According to a second embodiment of the invention, the characteristics targeted are achieved using a piece of matrix composite material metallic, elongated in a given direction, characterized by the fact that it comprises, respectively, from 35% to 45% by volume of a matrix in alloy based on magnesium and from 65% to 55% by volume continuous carbon fibers, arranged in layers successive parallel to said direction, at least approximately 90% of the carbon fibers being fibers with ultra high modulus, said ultra high modulus fibers being oriented at 0 ° ± 5 ° with respect to said direction in at least 90% of the aquifers.
Dans ce cas, la matrice en alliage à base de magnésium est, de préférence, en un alliage de type GA9Z1, contenant notamment environ 9 % en volume d'aluminium. In this case, the alloy matrix based on magnesium is preferably an alloy of the type GA9Z1, containing in particular approximately 9% by volume of aluminum.
Avantageusement, les fibres à ultra haut module sont alors orientées à 0° ± 5° dans environ 100 % des nappes.Advantageously, ultra high modulus fibers are then oriented at 0 ° ± 5 ° in about 100% of tablecloths.
Dans les deux formes de réalisation, les pièces présentent une stabilité quasi parfaite au moins dans la direction longitudinale. En effet, comme toutes les pièces métalliques ou à matrice métallique, il n'y a pas d'adsorbtion d'humidité au sol, de sorte que ses dimensions ne changent pas lorsque la pièce est mise dans le vide. De plus, grâce aux caractéristiques propres au matériau selon l'invention, le coefficient de dilatation thermique αL dans la direction longitudinale est pratiquement nul. En effet, sa valeur absolue est inférieure à 0,2.10-6/°C, ou proche de cette valeur.In both embodiments, the parts have almost perfect stability at least in the longitudinal direction. Indeed, like all metallic or metallic matrix parts, there is no adsorption of moisture on the ground, so that its dimensions do not change when the part is placed in a vacuum. In addition, thanks to the characteristics specific to the material according to the invention, the coefficient of thermal expansion αL in the longitudinal direction is practically zero. Indeed, its absolute value is less than 0.2.10 -6 / ° C, or close to this value.
Par ailleurs, une pièce conforme à l'invention présente une haute rigidité spécifique dans la direction longitudinale précitée. Plus précisément, la rigidité spécifique dans cette direction étant définie comme le rapport entre le module de traction longitudinal EL et la densité relative ρ, ce rapport est, dans la plupart des cas, supérieur à 100 MPa.Furthermore, 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 ρ, this ratio is, in in most cases, more than 100 MPa.
De préférence, au moins certaines des nappes sont des tissus, par exemple de type taffetas, comprenant environ 90 % de fils de chaíne, constitués par les fibres continues de carbone à ultra haut module et environ 10% de fils de trame, constitués par d'autre fibres continues de carbone, de moindre module. Les fils de trame ont notamment pour fonction de maintenir les fils de chaíne.Preferably, at least some of 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.
Dans les formes de réalisation préférées de l'invention, les fibres à ultra haut module sont des fibres ayant un module de traction au moins égal à environ 650 GPa, et qui s'étendent d'une extrémité à l'autre de la pièce, selon sa direction longitudinale.In the preferred embodiments of the invention, ultra high modulus fibers are fibers having a tensile modulus at least equal to about 650 GPa, and which extend from one end to the other of the part, in its longitudinal direction.
De préférence, les nappes sont agencées selon une symétrie miroir par rapport à une surface longitudinale médiane, parallèle à la direction longitudinale.Preferably, the sheets are arranged according to mirror symmetry with respect to a longitudinal surface median, parallel to the longitudinal direction.
Conformément à l'invention, pour qu'une pièce de forme allongée présente à la fois une très grande rigidité spécifique et une stabilité dimensionnelle pratiquement parfaite dans la direction de sa longueur, cette pièce doit être réalisée dans un matériau composite à matrice métallique présentant des caractéristiques bien déterminées.According to the invention, for a room of elongated shape presents both a very large specific stiffness and dimensional stability practically perfect in the direction of its length, this part must be made of a composite material with metal matrix having characteristics well determined.
L'expression "très grande rigidité spécifique dans la direction de sa longueur", signifie un rapport entre le module de traction EL et la densité relative ρ généralement supérieur à 100 GPa dans cette direction. Dans les formes de réalisation préférées qui vont être décrites, cet objectif est atteint puisque la rigidité spécifique mesurée dans la direction longitudinale est, selon le cas, de 119 GPa (matrice à base d'aluminium) ou de 197 (matrice de base de magnésium).The expression "very high specific rigidity in the direction of its length ", means a relationship between the tensile modulus EL and the relative density ρ 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).
De façon comparable, l'expression "stabilité dimensionnelle pratiquement parfaite dans la direction de sa longueur" signifie que la valeur absolue du coefficient de dilatation thermique longitudinale αL est généralement inférieure à 0,2.10-6/°C. Dans les formes de réalisation préférées, ce résultat est également atteint, puisque la valeur absolue du coefficient de dilatation thermique longitudinale mesuré est, selon le cas, de 0,08.10-6/°C (matrice à base d'aluminium) ou de 0,01.10-6/°C (matrice à base de magnésium).In a comparable manner, the expression "practically perfect dimensional stability in the direction of its length" means that the absolute value of the coefficient of longitudinal thermal expansion αL 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).
Conformément à l'invention, le matériau composite utilisé pour fabriquer une pièce de forme allongée comprend une matrice en alliage à base d'aluminium ou de magnésium, ainsi que des fibres continues de carbone qui sont disposées en nappes successives, parallèlement à la direction longitudinale de la pièce.According to the invention, 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.
De façon plus précise, la matrice et les fibres forment respectivement environ 40 % et environ 60 % du volume total de la pièce. Si la pièce comprend un ou plusieurs inserts réalisés en un autre matériau, par exemple métallique, cette proportion volumique ne concerne que la partie de la pièce réalisée en matériau composite. Dans la pratique, les expressions "environ 40 %" et "environ 60 %" signifient que la matrice représente de 35 % à 45 % du volume total de la pièce et que les fibres représentent respectivement 65 % à 55 % de ce même volume.More precisely, 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. In practice, the expressions "approximately 40% "and" around 60% "mean that the matrix represents from 35% to 45% of the total volume of the part and that the fibers respectively represent 65% at 55% of this same volume.
Dans une première forme de réalisation préférée de l'invention, l'alliage dans lequel est réalisé la matrice est un alliage d'aluminium contenant notamment environ 10 % en volume de magnésium. Un tel alliage est généralement connu sous la dénomination "alliage AG10".In a first preferred embodiment of the invention, 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".
Dans cette première forme de réalisation de l'invention, au moins environ 90 % des fibres continues de carbone sont des fibres à ultra haut module, c'est-à-dire des fibres dont le module de traction est au moins égal à environ 650 GPa. Plus précisément, les fibres continues de carbone sont des fibres "K139" de la Société MITSUBISHI.In this first embodiment of the invention, at least about 90% of the continuous fibers carbon are ultra high modulus fibers, 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.
De plus, les fibres de carbone à ultra haut module sont orientées entre -5° et + 5° par rapport à la direction longitudinale de la pièce dans 45 à 55 % des nappes. Dans les nappes restantes, c'est-à-dire respectivement dans 55 à 45 % des nappes, les fibres de carbone à ultra haut module sont orientées alternativement dans l'un ou l'autre sens entre 20° et 40° par rapport à la direction longitudinale de la pièce.In addition, ultra high carbon fibers module are oriented between -5 ° and + 5 ° relative to the longitudinal direction of the part in 45 to 55% tablecloths. In the remaining layers, that is to say respectively in 55 to 45% of the sheets, 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.
Dans la première forme de réalisation préférée, la pièce comporte un nombre pair de nappes de fibres et ces nappes sont agencées selon une symétrie miroir par rapport à une surface longitudinale médiane de la pièce, parallèle à la direction longitudinale. Cette surface est plane ou cylindrique, selon que la pièce présente une section rectangulaire ou circulaire, respectivement.In the first preferred embodiment, 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.
Dans chacune des nappes, les fibres à ultra haut module sont parallèles entre elles et elles s'étendent d'une extrémité à l'autre de la pièce, selon la direction longitudinale de celle-ci.In each of the layers, 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.
Une pièce conforme à l'invention est fabriquée en réalisant tout d'abord une préforme fibreuse, puis en infiltrant cette préforme de l'alliage formant la matrice. La réalisation de la préforme fibreuse dépend de la forme de la pièce à fabriquer. En particulier, les fibres à ultra haut module peuvent être utilisées seules (cas d'un bobinage), en association avec d'autres fibres (cas d'un tissu), ou en combinant ces deux procédés.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. In particular, 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.
Lorsque toutes les nappes sont formées uniquement de fibres à ultra haut module, parallèles entre elles dans chaque nappe, la totalité des fibres de carbone formant la matrice fibreuse est en fibres à ultra haut module. A l'inverse, lorsque toutes les nappes se présentent sous la forme d'un tissu dans lequel les fibres à ultra haut module constituent le fil de chaíne, environ 90 % des fibres de la matrice fibreuse sont des fibres à ultra haut module. Dans certains cas, une partie des nappes est formée uniquement de fibres à ultra haut module et les autres nappes sont formées de tissus. Selon le pourcentage des nappes de chaque catégorie, le pourcentage de fibres à ultra haut module dans la préforme fibreuse est alors compris entre environ 90 % et 100 %.When 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. Conversely, when all the layers are 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. In some cases, a part of the sheets is formed only of fibers with ultra high modulus and the other layers are formed of fabrics. 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%.
Dans le cas de l'exemple décrit, les fibres à ultra haut module sont tissées afin de maintenir ces fibres entre elles, dans la nappe considérée, pour assurer une fabrication satisfaisante de la pièce. Pour assurer ce maintien, on réalise alors un tissu, par exemple de type taffetas, comprenant environ 90 % de fils de chaíne constitués par les fibres de carbone à ultra haut module et environ 10 % de fils de trame, constitués par d'autres fibres continues de carbone, de moindre module. Dans la première forme de réalisation décrite, ces autres fibres sont des fibres de type "M40" ou "M50" de la Société TORAY.In the case of the example described, the fibers with ultra high modulus are woven to maintain these fibers together, in the sheet considered, for ensure satisfactory manufacture of the part. For ensure this maintenance, 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. In the first embodiment described, these other fibers are fibers of the type "M40" or "M50" from the company TORAY.
Une pièce en matériau composite à matrice métallique conforme à l'invention est fabriquée par fonderie sous pression.A piece of matrix composite material metal according to the invention is manufactured by pressure foundry.
Selon cette technique, on place dans un même récipient hermétique, comparable à un autoclave, un creuset contenant des blocs de l'alliage destiné à former la matrice de la pièce, ainsi qu'un moule dans lequel on a introduit auparavant la préforme fibreuse préalablement fabriquée selon l'agencement précédemment décrit.According to this technique, we place in the same airtight container, comparable to an autoclave, a crucible containing blocks of the alloy intended to form the matrix of the part, as well as a mold in which the fiber preform was previously introduced previously manufactured according to the arrangement previously described.
Lors d'une première étape, on fait le vide à l'intérieur du récipient et du moule, on chauffe le creuset contenant les blocs d'alliage métallique et on préchauffe le moule.During a first step, we vacuum inside the container and the mold, we heat the crucible containing the metal alloy blocks and we preheats the mold.
Lorsque l'alliage contenu dans le creuset est totalement fondu, il est transféré à l'intérieur du moule. Ce transfert est effectué automatiquement en pressurisant le récipient à un niveau de pression généralement compris entre environ 30 bars et environ 100 bars.When the alloy contained in the crucible is completely melted, it is transferred inside the mold. This transfer is carried out automatically in pressurizing the container to a pressure level generally between approximately 30 bars and approximately 100 bars.
Dès que le moule est rempli, le refroidissement de la pièce est accéléré en amenant un organe réfrigérant au contact d'une paroi du moule. Tant que la température n'est pas redescendue en dessous de la température de solidification de l'alliage, la pression est maintenue dans le récipient afin de compenser le rétreint naturel du métal.As soon as the mold is filled, cooling of the room is accelerated by bringing in a cooling element in contact with a wall of the mold. As long as the temperature did not drop below the temperature solidification of the alloy, the pressure is kept in the container to compensate for the natural shrinking of metal.
Pour plus de détails concernant les principales techniques connues de mise en oeuvre de ce procédé, on se reportera utilement à l'article "Pressure Infiltration Casting of Metal Matrix Composites" de Arnold J. COOK et Paul S. WERNER, dans "Materials Science and Engineering" A 144 (Octobre 1991) pages 189 à 206.For more details on the main known techniques for implementing this method, usefully refer to the article "Pressure Infiltration Casting of Metal Matrix Composites "by Arnold J. COOK and Paul S. WERNER, in "Materials Science and Engineering" A 144 (October 1991) pages 189 to 206.
Dans la première forme de réalisation de
l'invention, six pièces différentes, numérotées 1 à 6,
en matériau composite à matrice métallique, de forme
parallélépipèdique allongée, ont été fabriquées par
cette technique de fonderie sous pression. Les pièces
numérotées 1 à 5 présentaient les mêmes dimensions de
260mm x 130mm x 3mm. La pièce numérotée 6 présentait
des dimensions de 160 mm x 80 mm x 3 mm. Toutes les
pièces présentaient la même matrice en AG10. Elles différaient
essentiellement par la structure de leur préforme
fibreuse. En effet, si chacune de ces préformes
était formée de seize (pièces 1 à 5) ou dix (pièce 6)
nappes de tissu incluant chacune 90 % de fibres K139 et
10 % de fibres M40 (pièces 1 à 5) ou M50 (pièce 6),
l'orientation des fibres K139 à ultra haut module était
différente d'une préforme à l'autre. Cette orientation
est donnée dans le Tableau I.
Les préformes définies par le Tableau I correspondent à des pièces de référence, permettant de montrer l'importance de l'orientation des fibres à l'intérieur du matériau composite, pour obtenir le résultat désiré.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.
A partir des préformes ainsi réalisées, chacune des pièces a ensuite été élaborée, par la technique de fonderie sous pression, dans des conditions d'élaboration identiques. Ces conditions sont les suivantes :
- température du bain de métal constitué par l'alliage d'aluminium AG10 : 720°C;
- température de la préforme : 670°C ;
- pression maximale d'infiltration : 60 bars ;
- montée en pression : 1 bar/s ;
- vitesse moyenne de refroidissement : environ 50°C/min.
- temperature of the metal bath constituted by the aluminum alloy AG10: 720 ° C;
- preform temperature: 670 ° C;
- maximum infiltration pressure: 60 bars;
- pressure build-up: 1 bar / s;
- average cooling rate: around 50 ° C / min.
Des éprouvettes ont ensuite été découpées à la meule diamant dans chacune des pièces ainsi obtenues, pour permettre d'effectuer notamment des essais mécaniques et des mesures physiques.Test pieces were then cut with the diamond wheel in each of the parts thus obtained, to allow in particular mechanical tests and physical measurements.
Préalablement à la découpe des éprouvettes, la qualité de l'infiltration des préformes fibreuses par l'alliage a été contrôlée à la fois par radiographie aux rayons X et par des observations métallographiques. Ces contrôles ont mis en évidence une très bonne infiltration de la préforme et l'absence de défaut de fonderie.Before cutting the test pieces, the quality of infiltration of fibrous preforms by the alloy was checked both by radiography X-rays and metallographic observations. These checks revealed very good infiltration of the preform and the absence of a foundry defect.
Les essais mécaniques effectués sur les éprouvettes usinées dans les pièces sont principalement des essais de traction. Les mesures physiques concernent notamment le coefficient de dilatation thermique dans la direction transversale, le coefficient de dilatation thermique dans la direction longitudinale et la fraction volumique en fibre.Mechanical tests carried out on test pieces machined in parts are mainly tensile tests. Physical measurements concern in particular the coefficient of thermal expansion in transverse direction, coefficient of expansion thermal in the longitudinal direction and the fiber volume fraction.
Les mesures physiques ont montré que la masse volumique du composite était toujours comprise entre 2,26 g/cm3 et 2,30g/cm3.Physical measurements showed that the density of the composite was always between 2.26 g / cm 3 and 2.30 g / cm 3 .
Les résultats des essais mécaniques et des mesures physiques effectués sur chacune des éprouvettes, à température ambiante (environ 20°C), sont rassemblés dans le Tableau II. The results of the mechanical tests and of the physical measurements carried out on each of the test pieces, at ambient temperature (approximately 20 ° C.), are collated in Table II.
Sur ce Tableau, l'expression "sens L" signifie direction longitudinale, l'expression "sens T" signifie direction transversale et les valeurs données entre parenthèses indiquent le nombre d'essais effectué à chaque fois.In this Table, the expression "sense L" means longitudinal direction, the expression "sense T" means transverse direction and the values given between parentheses indicate the number of tests performed at every time.
Les résultats présentés dans le Tableau II montrent que le coefficient de dilatation thermique αL dans la direction longitudinale décroít progressivement en valeur absolue, de la pièce 1 à la pièce 5, les pièces 2, 3 et 6 présentant un coefficient de dilatation thermique sensiblement d'égale valeur, dans cette direction. Seules les pièces 4 et 5 présentent un coefficient αL inférieur à 0,2.10-6/°C, dans la direction longitudinale. Par ailleurs, seules les pièces 1, 5 et 6 présentent une rigidité spécifique dans la direction longitudinale EL/ρ supérieure à 100 GPa.The results presented in Table II show that the coefficient of thermal expansion αL in the longitudinal direction decreases progressively in absolute value, from part 1 to part 5, parts 2, 3 and 6 having a coefficient of thermal expansion substantially of equal value, in this direction. Only parts 4 and 5 have a coefficient αL less than 0.2.10 -6 / ° C, in the longitudinal direction. Furthermore, only parts 1, 5 and 6 have a specific rigidity in the longitudinal direction EL / ρ greater than 100 GPa.
Dans la première forme de réalisation de l'invention, la pièce 5 présente donc le meilleur compromis afin d'obtenir à la fois une haute rigidité et une grande stabilité dans la direction longitudinale.In the first embodiment of the invention, Exhibit 5 therefore presents the best compromise in order to obtain both a high rigidity and a great stability in the longitudinal direction.
Dans une deuxième forme de réalisation préférée de l'invention, la matrice est réalisée en un alliage à base de magnésium, contenant notamment environ 9 % en volume d'aluminium. Cet alliage est de type GA9Z1 Haute Pureté.In a second preferred embodiment of the invention, 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.
Comme dans la première forme de réalisation décrite, la matrice et les fibres continues de carbones présentent des taux volumiques respectifs d'environ 40 % et d'environ 60 %.As in the first embodiment described, the matrix and the continuous carbon fibers have respective volume ratios of approximately 40% and around 60%.
Dans l'exemple choisi pour illustrer cette deuxième forme de réalisation de l'invention, on réalise une préforme à partir d'un empilement de nappes de tissu. Le tissu comprend environ 90 % en volume de fibres de carbone à ultra haut module, de type K 139, placées dans la direction longitudinale, et 10 % de fibres de carbone de type M 50, placées dans la direction transverse, afin de maintenir les fibres K 139.In the example chosen to illustrate this second embodiment of the invention, one realizes a preform from a stack of layers of fabric. 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.
L'empilement des nappes de tissu est réalisé de façon telle que, dans toutes les nappes, les fibres à ultra haut module soient orientées à 0° ± 5° par rapport à la direction longitudinale de la pièce.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.
Comme dans la première forme de réalisation décrite, la pièce est fabriquée par fonderie sous pression, dans les conditions suivantes :
- température du bain d'alliage de magnésium GA9Z1 : 750°C ;
- température de la préforme : 750°C ;
- pression maximale d'infiltration : 60 bars ;
- montée en pression : 1 bar/s ;
- vitesse moyenne de refroidissement : environ 25°C/min.
- temperature of the GA9Z1 magnesium alloy bath: 750 ° C;
- preform temperature: 750 ° C;
- maximum infiltration pressure: 60 bars;
- pressure build-up: 1 bar / s;
- average cooling rate: around 25 ° C / min.
Des échantillons de la pièce obtenue, appelée "pièce 7" ont été découpés afin d'effectuer les mêmes mesures mécaniques et physiques que sur les pièces 1 à 6 illustrant la première forme de réalisation de l'invention.Samples of the part obtained, called "piece 7" have been cut to perform the same mechanical and physical measurements only on parts 1 to 6 illustrating the first embodiment of the invention.
La masse volumique de la pièce 7 a été déterminée à 1,95 g/cm3 par les mesure physiques.The density of the part 7 was determined at 1.95 g / cm 3 by physical measurements.
Le Tableau III donne, à température ambiante
(environ 20°C), les résultats des mesures mécaniques et
physiques effectués (les notations sont les mêmes que
dans le Tableau II).
L'observation du Tableau III montre que la pièce 7 présente, en valeur absolue, un coefficient de dilatation thermique αL, dans la direction longitudinale, très inférieur à 0,2.10-6/°C. De plus, la rigidité spécifique EL/ρ dans la direction longitudinale est largement supérieure à 100 GPa. Les objectifs visés sont donc également atteints par cette deuxième forme de réalisation de l'invention, dès lors que l'orientation des libres est à 0° ± 5° dans au moins 90 % des nappes.The observation in Table III shows that the part 7 has, in absolute value, a coefficient of thermal expansion αL, in the longitudinal direction, much less than 0.2.10 -6 / ° C. In addition, the specific rigidity EL / ρ in the longitudinal direction is much greater than 100 GPa. The objectives sought are therefore also achieved by this second embodiment of the invention, since the orientation of the free is at 0 ° ± 5 ° in at least 90% of the sheets.
En conclusion, les pièces en matériau composite à matrice métallique conformes à l'invention présentent des caractéristiques mécaniques et physiques qui permettent d'envisager leur utilisation notamment dans l'industrie spatiale, pour toutes les applications nécessitant à la fois une haute rigidité et une excellente stabilité dans une direction longitudinale de la pièce.In conclusion, 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.
Claims (13)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR9715306 | 1997-12-04 | ||
FR9715306A FR2772049B1 (en) | 1997-12-04 | 1997-12-04 | PIECE OF COMPOSITE MATERIAL WITH HIGH RIGIDITY AND HIGH STABILITY METAL MATRIX IN A LONGITUDINAL DIRECTION |
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EP0922779A1 true EP0922779A1 (en) | 1999-06-16 |
EP0922779B1 EP0922779B1 (en) | 2002-08-21 |
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US (1) | US6197411B1 (en) |
EP (1) | EP0922779B1 (en) |
JP (1) | JP4283359B2 (en) |
CA (1) | CA2255402A1 (en) |
DE (1) | DE69807306T2 (en) |
ES (1) | ES2182246T3 (en) |
FR (1) | FR2772049B1 (en) |
RU (1) | RU2217522C2 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107267826A (en) * | 2017-05-16 | 2017-10-20 | 苏州莱特复合材料有限公司 | A kind of modified graphene enhancing magnesium-base metal material and preparation method thereof |
CN107312984A (en) * | 2017-05-16 | 2017-11-03 | 苏州莱特复合材料有限公司 | A kind of modified carbon fiber enhancing magnesium-based composite material and preparation method thereof |
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DE10126926B4 (en) * | 2001-06-01 | 2015-02-19 | Astrium Gmbh | Internal combustion chamber of a ceramic composite material and method of manufacture |
AT413704B (en) * | 2004-06-23 | 2006-05-15 | Arc Leichtmetallkompetenzzentrum Ranshofen Gmbh | CARBON FIBER REINFORCED LIGHT METAL PART AND METHOD FOR THE PRODUCTION THEREOF |
US20080248309A1 (en) | 2004-11-09 | 2008-10-09 | Shimane Prefectural Government | Metal-Based Carbon Fiber Composite Material and Producing Method Thereof |
DE102005051269B3 (en) * | 2005-10-26 | 2007-05-31 | Infineon Technologies Ag | Composite material used in the assembly of electrical components comprises fibers in the upper surfaces horizontally orientated to a reference surface and the fibers in the lower surfaces orientated vertically to the reference surface |
DE102006023041B4 (en) * | 2006-05-17 | 2015-11-12 | Bayerische Motoren Werke Aktiengesellschaft | Particle-reinforced magnesium or aluminum alloy |
RU2613830C1 (en) * | 2015-10-07 | 2017-03-21 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Fibrous composite material |
DE102015221078A1 (en) * | 2015-10-28 | 2017-05-04 | Airbus Operations Gmbh | Fiber reinforced metal component for an aerospace vehicle and manufacturing process for fiber reinforced metal components |
ITUA20162826A1 (en) * | 2016-04-22 | 2017-10-22 | Freni Brembo Spa | BODY CALIPER OF A CLAMP FOR DISC BRAKE |
CN108723309B (en) * | 2018-06-25 | 2021-01-01 | 临沂利信铝业有限公司 | Aluminum-magnesium alloy cast ingot and preparation method thereof |
CN110385437B (en) * | 2019-07-03 | 2021-09-10 | 西安理工大学 | Preparation method of directional fiber in-situ reinforced titanium and alloy bracket thereof |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0164536A2 (en) * | 1984-06-15 | 1985-12-18 | Toyota Jidosha Kabushiki Kaisha | Composite material with carbon reinforcing fibers and magnesium alloy matrix metal including zinc |
WO1992000182A1 (en) * | 1990-06-29 | 1992-01-09 | Flexline Services Ltd. | A process for manufacturing reinforced composites and filament material for use in said process |
-
1997
- 1997-12-04 FR FR9715306A patent/FR2772049B1/en not_active Expired - Fee Related
-
1998
- 1998-11-13 US US09/190,302 patent/US6197411B1/en not_active Expired - Fee Related
- 1998-12-01 EP EP98403009A patent/EP0922779B1/en not_active Expired - Lifetime
- 1998-12-01 ES ES98403009T patent/ES2182246T3/en not_active Expired - Lifetime
- 1998-12-01 DE DE69807306T patent/DE69807306T2/en not_active Expired - Fee Related
- 1998-12-02 CA CA002255402A patent/CA2255402A1/en not_active Abandoned
- 1998-12-03 RU RU98122445/02A patent/RU2217522C2/en not_active IP Right Cessation
- 1998-12-04 JP JP34617898A patent/JP4283359B2/en not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0164536A2 (en) * | 1984-06-15 | 1985-12-18 | Toyota Jidosha Kabushiki Kaisha | Composite material with carbon reinforcing fibers and magnesium alloy matrix metal including zinc |
WO1992000182A1 (en) * | 1990-06-29 | 1992-01-09 | Flexline Services Ltd. | A process for manufacturing reinforced composites and filament material for use in said process |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107267826A (en) * | 2017-05-16 | 2017-10-20 | 苏州莱特复合材料有限公司 | A kind of modified graphene enhancing magnesium-base metal material and preparation method thereof |
CN107312984A (en) * | 2017-05-16 | 2017-11-03 | 苏州莱特复合材料有限公司 | A kind of modified carbon fiber enhancing magnesium-based composite material and preparation method thereof |
Also Published As
Publication number | Publication date |
---|---|
JPH11256254A (en) | 1999-09-21 |
DE69807306T2 (en) | 2003-04-17 |
US6197411B1 (en) | 2001-03-06 |
CA2255402A1 (en) | 1999-06-04 |
EP0922779B1 (en) | 2002-08-21 |
DE69807306D1 (en) | 2002-09-26 |
JP4283359B2 (en) | 2009-06-24 |
ES2182246T3 (en) | 2003-03-01 |
FR2772049A1 (en) | 1999-06-11 |
FR2772049B1 (en) | 2000-02-18 |
RU2217522C2 (en) | 2003-11-27 |
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