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EP2981631B1 - Bleche aus aluminium-kupfer-lithium-legierung zur herstellung von flugzeugrümpfen - Google Patents

Bleche aus aluminium-kupfer-lithium-legierung zur herstellung von flugzeugrümpfen Download PDF

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EP2981631B1
EP2981631B1 EP14719034.2A EP14719034A EP2981631B1 EP 2981631 B1 EP2981631 B1 EP 2981631B1 EP 14719034 A EP14719034 A EP 14719034A EP 2981631 B1 EP2981631 B1 EP 2981631B1
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EP2981631A1 (de
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Juliette CHEVY
Bernard Bes
Frank Eberl
Jean-Christophe Ehrstrom
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Constellium Issoire SAS
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Constellium Issoire SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
    • B22D21/002—Castings of light metals
    • B22D21/007—Castings of light metals with low melting point, e.g. Al 659 degrees C, Mg 650 degrees C
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium

Definitions

  • the invention relates to rolled products aluminum-copper-lithium alloys, more particularly, such products, their manufacturing processes and use, intended in particular for aeronautical and aerospace construction.
  • Aluminum alloy rolled products are being developed to produce fuselage elements for the aerospace industry and the aerospace industry in particular.
  • Aluminum - copper - lithium alloys are particularly promising for this type of product.
  • the US Patent 5,032,359 discloses a large family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, in particular between 0.3 and 0.5 percent by weight, makes it possible to increase the mechanical strength.
  • the US Patent 5,455,003 discloses a process for manufacturing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, particularly through proper work-hardening and tempering.
  • the US Patent 7,438,772 discloses alloys comprising, in weight percent, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourage the use of higher lithium contents due to degradation compromise between toughness and mechanical strength.
  • the US Patent 7,229,509 discloses an alloy comprising (% by weight): (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0) Mg, (0.2-0, 8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain refining agents such as Cr, Ti, Hf, Sc, V.
  • the patent application US 2011/0247730 discloses alloys comprising (% by weight), 2.75 to 5.0% Cu, 0.1 to 1.1% Li, 0.3 to 2.0% Ag, 0.2 to 0.8% Mg, , 50 to 1.5% of Zn, up to 1.0% of Mn, with a Cu / Mg ratio of between 6.1 and 17, this alloy being not very sensitive to wrought iron.
  • composition alloys (in% by weight) Cu 2.8 - 4.0; Li 0.8 - 1.9; Mn 0.2-0.6; Zn 0.20 - 0.80, Zr 0.04 - 0.20, Mg 0.20 - 0.80, Ag 0.1 - 0.7, Si ⁇ 0.10, Fe ⁇ 0.10, Ti ⁇ 0.12.
  • the characteristics required for aluminum sheets for fuselage applications are described for example in the patent EP 1 891 247 .
  • the patent EP 1 966 402 discloses an alloy comprising 2.1 to 2.8% by weight of Cu, 1.1 to 1.7% by weight of Li, 01 to 0.8% by weight of Ag, 0.2 to 0.6% by weight of weight of Mg, 0.2 to 0.6% by weight of Mn, an amount of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities at a content of less than or equal to 0.05 % by weight each and 0.15% by weight in total, the alloy being substantially free of zirconium, particularly suitable for obtaining recrystallized thin sheets.
  • Damage tolerance sizing is the determination of a detectable, limitable fault size that can be guaranteed to not break during a defined time interval. To achieve this dimensioning it is necessary to know the behavior of cracks subjected to a representative load on panels of sufficient size. In addition, in the case of the large damage capability assessment for which the undetected failure of a stiffener is assumed, the width of the crack can be high and it is useful to have accurate data of toughness for very long cracks.
  • the characterization of toughness of the thin sheets is generally carried out on panels with a width of less than or equal to 760 mm by the R curve test.
  • the curve test R is a widely recognized means for characterizing the tenacity properties.
  • the curve R represents the evolution of the critical effective stress intensity factor for the crack propagation as a function of the effective crack extension, under monotonically increasing stress. It allows the determination of the critical load for unstable failure for any configuration relevant to cracked aircraft structures.
  • the values of the effective stress intensity factor and the effective crack extension are actual values as defined in ASTM E561. It is generally believed that the width of the panel should not change the level of the R curve, namely the effective stress intensity factor for a given effective crack growth, but only the valid length of the curve. However, it has been found in the context of the present invention that this hypothesis is not always verified and that in fact the characterization on larger panels, such as panels of width 1220 mm, accounts for certain specific properties. material that can not be deduced from the characterizations performed on smaller panels. Thus the knowledge of the state of the art It is not possible to predict which alloys and which thermomechanical treatments will achieve the most advantageous properties for K app and for the level of the R curve on wide panels, but these properties will influence the dimensioning in damage tolerance.
  • the toughness be high in the L-T direction. Indeed, in some configurations the bending stresses on the fuselage around the axis of the wings become critical, especially for the upper part of the fuselage. The cracks on the plates whose longitudinal direction and also the longitudinal direction of the fuselage are then biased in the L-T direction.
  • Yet another object of the invention is the use of a sheet according to the invention in an aircraft fuselage panel.
  • alloys are in accordance with the regulations of The Aluminum Association, known to those skilled in the art. The density depends on the composition and is determined by calculation rather than by a method of measuring weight. The values are calculated in accordance with the procedure of The Aluminum Association, which is described on pages 2-12 and 2-13 of "Aluminum Standards and Data". Unless otherwise stated, the definitions of the metallurgical states given in the European standard EN 515 apply.
  • the static mechanical characteristics in tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0.2 , and the elongation at break A% are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
  • the mechanical characteristics are measured in full thickness.
  • the term "substantially uncrystallized granular structure” refers to a granular structure such that the degree of recrystallization at 1 ⁇ 2-thickness is less than 30% and preferably less than 10%, and a substantially recrystallized granular structure is called a structure. granular such that the recrystallization rate at 1 ⁇ 2 thickness is greater than 70% and preferably greater than 90%.
  • the recrystallization rate is defined as the surface fraction on a metallographic section occupied by recrystallized grains.
  • a curve giving the effective stress intensity factor as a function of the effective crack extension, known as the R curve, is determined according to ASTM E 561.
  • the critical stress intensity factor K c in d other words the intensity factor that makes the crack unstable, is calculated from the curve R.
  • the stress intensity factor K CO is also calculated by assigning the crack length initial at the beginning of the monotonic load, at the critical load. These two values are calculated for a specimen of the required form.
  • K app represents the K CO factor corresponding to the specimen that was used to perform the R curve test.
  • K eff represents the K C factor corresponding to the specimen that was used to perform the R curve test.
  • ⁇ a eff (max) represents the crack extension of the last point of the curve R, valid according to the ASTM E561 standard.
  • the crack size at the end of the pre-fatigue cracking stage is W / 3 for M (T) type specimens, where W is the specimen width as defined in ASTM E561.
  • EN 12258 Unless otherwise specified, the definitions of EN 12258 apply.
  • the present inventors have surprisingly found that the toughness measured in the LT direction on 1220 mm wide panels is improved for a precise range of yield strength values in the longitudinal direction R p0,2 (L) while this effect is not observed when the measurement is made on panels of width 760 mm.
  • R p0,2 L
  • there is an optimum range of elastic limit value specific to the width 1220 mm which can not be interpreted by considerations based on the plasticization of the uncracked ligament. , these underlying the validity limits of ASTM E561.
  • the present inventors have therefore established that sheets obtained by a process comprising casting, homogenization, hot rolling and optionally cold rolling, solution-setting, quenching and tempering have the advantageous properties when the composition and the combined so that the yield strength in the longitudinal direction R p0,2 (L) is between 395 and 435 MPa.
  • the sheets have the advantageous properties when the income is made "at the peak".
  • the so-called "peak” income is an income for which the yield strength in the transverse direction R p0,2 (TL) has a value of at least 95%.
  • the yield strength in the transverse direction R p0.2 (TL) obtained for an income having a time equivalent to 155 ° C of 48 h.
  • a "peak" income is preferred.
  • thermal stability is understood to mean the stability of the mechanical properties during a temperature exposure representative of the conditions experienced in civil aviation, this being for example simulated by an aging of 1000 hours at 85 ° C. vs. Therefore, it is chosen to perform, if necessary, an under-income for which the yield strength in the transverse direction R p0.2 (TL) has a value of between 88% and 94% and preferably at least 91% of the value obtained for an income having a time equivalent to 155 ° C of 48 hours.
  • the copper content of the products according to the invention is between 2.6 and 3.0% by weight. In an advantageous embodiment of the invention, the copper content is between 2.8 and 3.0% by weight.
  • the copper content is at most 2.95% by weight and advantageously at most 2.9% by weight.
  • the yield strength R p0.2 (L) is too high to reach the advantageous range under the under- feed conditions according to the invention.
  • the copper content is too low, the minimum static mechanical characteristics are not reached, even for a peak income.
  • the lithium content of the products according to the invention is between 0.5 and 0.8% by weight.
  • the lithium content is between 0.55% and 0.75% by weight.
  • the lithium content is between 0.60% and 0.73% by weight.
  • the addition of lithium can contribute to the increase of the mechanical strength and the toughness, a content that is too high or too low does not make it possible to obtain a high value of tenacity and / or a sufficient limit of elasticity.
  • the magnesium content of the products according to the invention is between 0.2 and 0.7% by weight, preferably between 0.25 and 0.50% by weight and preferably between 0.30 and 0.45% by weight. in weight. In an advantageous embodiment of the invention, the magnesium content is at most 0.4% by weight.
  • the zirconium content is between 0.06 and 0.20% by weight and preferably between 0.10 and 0.18% by weight. When an essentially non-recrystallized granular structure is preferred, the zirconium content is advantageously between 0.14 and 0.17% by weight.
  • the silver content is between 0.1 and 0.4% by weight. In an advantageous embodiment of the invention, the silver content is between 0.2 and 0.3% by weight. In one embodiment of the invention the silver content is between 0.15 and 0.28% by weight.
  • the titanium content is between 0.01 and 0.15% by weight. The addition of titanium helps to control the granular structure, especially during casting.
  • the alloy may optionally contain at least one element selected from Mn, V, Cr, Sc, and Hf, the amount of the element, if selected, being from 0.01 to 0.8% by weight for Mn 0.05 to 0.2% by weight for V, 0.05 to 0.3% by weight for Cr, 0.02 to 0.3% by weight for Sc, 0.05 to 0.5% by weight for Hf.
  • Mn, V, Cr or Sc are not added and their content is less than or equal to 0.05% by weight.
  • the iron and silicon contents are each at most 0.1% by weight.
  • the iron and silicon contents are at most 0.08% and preferably at most 0.04% by weight.
  • a controlled and limited iron and silicon content contributes to the improvement of the compromise between mechanical resistance and damage tolerance.
  • the zinc content is less than 0.2% by weight and preferably less than 0.1% by weight.
  • the zinc content is advantageously less than 0.04% by weight.
  • the unavoidable impurities are maintained at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total.
  • the manufacturing process of the sheets according to the invention comprises steps of production, casting, rolling, dissolution, quenching controlled traction and income.
  • a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
  • the bath of liquid metal is then cast into a form of rolling plate.
  • the rolling plate is then homogenized at a temperature between 450 ° C and 535 ° and preferably between 480 ° C and 530 ° C.
  • the homogenization time is preferably between 5 and 60 hours.
  • the rolling plate is generally cooled to room temperature before being preheated to be hot deformed.
  • Preheating aims to achieve a temperature preferably between 400 and 500 ° C for deformation by hot rolling.
  • the hot rolling and optionally cold rolling is carried out so as to obtain a sheet thickness of 0.5 to 8 mm.
  • Intermediate heat treatments during rolling and / or after rolling can be carried out in some cases. However, preferably, the process does not include intermediate heat treatment during rolling and / or after rolling.
  • the sheet thus obtained is then put in solution by heat treatment between 450 and 535 ° C, preferably for 5 min to 8 h, and then quenched.
  • An income is made comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably from 10 to 40h so as to achieve a limit of elasticity in the direction longitudinal R p0.2 (L) between 395 and 435 MPa.
  • a yield strength in the longitudinal direction R p0.2 (L) of 395 and 415 MPa may be preferred in some cases.
  • a yield strength in the longitudinal direction R p0.2 (L) of 415 and 435 MPa may be preferred in some cases.
  • the composition makes it possible to reach the desired longitudinal elasticity limit with a time equivalent to 155 ° C. of less than 48 hours and preferably less than 30 hours.
  • the final metallurgical state is a T8 state.
  • t i is expressed in hours.
  • the present inventors have found in particular that the preferred field of magnesium content makes it possible to limit the duration of the income by reaching a favorable property compromise.
  • a short heat treatment is performed after controlled pulling and before tempering so as to improve the formability of the sheets.
  • the sheets can thus be shaped by a process such as stretch-forming before being returned.
  • the most favorable granular structure depends on the thickness of the products.
  • sheets according to the invention in an aircraft fuselage panel is advantageous.
  • the sheets according to the invention are also advantageous in aerospace applications such as the manufacture of rockets.
  • the granular structure of the samples was characterized from microscopic observation of cross sections after anodic oxidation under polarized light.
  • the granular structure of the sheets was essentially non-recrystallized for all sheets except D # 2 and E # 2 sheets for which the granular structure was essentially recrystallized.
  • the samples were mechanically tested to determine their static mechanical properties as well as their resistance to crack propagation. Tensile yield strength, ultimate strength and elongation at break are given in Table 3.
  • Table 4 summarizes the results of the tenacity tests on CCT test pieces of width 760 mm for these samples. Table 4 results of the R curves for 760 mm wide specimens.
  • Table 5 summarizes the results of the toughness tests for the R curves obtained with CCT specimens of width 12

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
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  • Organic Chemistry (AREA)
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Claims (12)

  1. Blech mit einer Dicke von 0,5 bis 8 mm aus einer Legierung auf Basis von Aluminium umfassend
    2,6 bis 3,0 Gew.-% Cu,
    0,5 bis 0,8 Gew.-% Li,
    0,1 bis 0,4 Gew.-% Ag,
    0,2 bis 0,5 Gew.-% Mg,
    0,06 bis 0,20 Gew.-% Zr,
    0,01 bis 0,15 Gew.-% Ti,
    wahlweise mindestens ein Element ausgewählt unter Mn, V, Cr, Sc und Hf, wobei die Menge des Elements, falls gewählt, 0,01 bis 0,8 Gew.-% für Mn, 0,05 bis 0,2 Gew.-% für V, 0,05 bis 0,3 Gew.-% für Cr, 0,02 bis 0,3 Gew.-% für Sc, 0,05 bis 0,5 Gew.-% für Hf beträgt,
    eine Menge Zn von weniger als 0,2 Gew.-%, eine Menge Fe und Si jeweils kleiner oder gleich 0,1 Gew.-%, Rest Aluminium und unvermeidbare Verunreinigungen mit einem Gehalt von jeweils höchstens 0,05 Gew.-% und insgesamt 0,15 Gew.-%,
    wobei das Blech mit einem Verfahren erhalten wird, welches die Schritte Gießen, Homogenisieren, Warmwalzen und wahlweise Kaltwalzen, Lösungsglühen, Abschrecken und Auslagern umfasst, wobei die Zusammensetzung und die Auslagerung so kombiniert sind, dass die Dehngrenze in Längsrichtung Rp0,2(L) zwischen 395 und 435 MPa liegt.
  2. Blech nach Anspruch 1, dessen Kupfergehalt zwischen 2,8 und 3,0 Gew.-% und vorzugsweise zwischen 2,8 und 2,9 Gew.-% liegt.
  3. Blech nach Anspruch 1 oder Anspruch 2, dessen Lithiumgehalt zwischen 0,55 und 0,75 Gew.-% und vorzugsweise zwischen 0,60 und 0,73 Gew.-% liegt.
  4. Blech nach irgendeinem der Ansprüche 1 bis 3, dessen Silbergehalt zwischen 0,2 und 0,3 Gew.-% liegt.
  5. Blech nach irgendeinem der Ansprüche 1 bis 4, dessen Magnesiumgehalt zwischen 0,25 und 0,50 Gew.-% und vorzugsweise zwischen 0,30 und 0,45 Gew.-% liegt.
  6. Blech nach irgendeinem der Ansprüche 1 bis 5, bei dem die Auslagerung unter Zeitbedingungen durchgeführt wird, die zu maximaler Festigkeit führen.
  7. Blech nach irgendeinem der Ansprüche 1 bis 6, dessen Dicke zwischen 0,5 und 3,3 mm liegt und das folgende Eigenschaften aufweist:
    - eine Bruchzähigkeit bei flächiger Belastung Kapp, gemessen an Proben vom Typ CCT760 (2ao = 253 mm), in L-T-Richtung von mindestens 120 MPa √m und
    - eine Bruchzähigkeit bei flächiger Belastung Kapp, gemessen an Proben vom Typ CCT1120 (2ao = 253 mm), in L-T-Richtung von mindestens 120 MPa √m.
  8. Blech nach Anspruch 7, dessen Korngefüge im Wesentlichen rekristallisiert ist und das folgende Eigenschaften aufweist:
    - eine Bruchzähigkeit bei flächiger Belastung Kapp, gemessen an Proben vom Typ CCT760 (2ao = 253 mm), in L-T-Richtung von mindestens 140 MPa √m und
    - eine Bruchzähigkeit bei flächiger Belastung Kapp, gemessen an Proben vom Typ CCT1120 (2ao = 253 mm), in L-T-Richtung von mindestens 150 MPa √m.
  9. Blech nach irgendeinem der Ansprüche 1 bis 6, dessen Dicke zwischen 3,4 bis 6 mm liegt und das folgende Eigenschaften aufweist:
    - eine Bruchzähigkeit bei flächiger Belastung Kapp, gemessen an Proben vom Typ CCT760 (2ao = 253 mm), in L-T-Richtung von mindestens 150 MPa √m und vorzugsweise mindestens 155 MPa √m,
    - eine Bruchzähigkeit bei flächiger Belastung Kapp, gemessen an Proben vom Typ CCT1120 (2ao = 253 mm), in L-T-Richtung von mindestens 170 MPa √m und vorzugsweise mindestens 180 MPa √m.
  10. Blech nach irgendeinem der Ansprüche 1 bis 6, dessen Dicke zwischen 3,4 und 8 mm und vorzugsweise zwischen 4 und 8 mm liegt und dessen Korngefüge im Wesentlichen nicht rekristallisiert ist.
  11. Verfahren zur Herstellung eines Blechs nach irgendeinem der Ansprüche 1 bis 10 mit einer Dicke von 0,5 bis 8 mm aus einer Legierung auf Basis von Aluminium, wobei nacheinander
    a) ein Flüssigmetallbad hergestellt wird, umfassend
    2,6 bis 3,0 Gew.-% Cu,
    0,5 bis 0,8 Gew.-% Li,
    0,1 bis 0,4 Gew.-% Ag,
    0,2 bis 0,5 Gew.-% Mg,
    0,06 bis 0,20 Gew.-% Zr,
    0,01 bis 0,15 Gew.-% Ti,
    wahlweise mindestens ein Element ausgewählt unter Mn, V, Cr, Sc und Hf, wobei die Menge des Elements, falls gewählt, 0,01 bis 0,8 Gew.-% für Mn, 0,05 bis 0,2 Gew.-% für V, 0,05 bis 0,3 Gew.-% für Cr, 0,02 bis 0,3 Gew.-% für Sc, 0,05 bis 0,5 Gew.-% für Hf beträgt,
    eine Menge Zn von weniger als 0,2 Gew.-%, eine Menge Fe und Si jeweils kleiner oder gleich 0,1 Gew.-%, Rest Aluminium und unvermeidbare Verunreinigungen mit einem Gehalt von jeweils höchstens 0,05 Gew.-% und insgesamt 0,15 Gew.-%,
    b) aus dem Flüssigmetallbad ein Walzbarren gegossen wird,
    c) der Walzbarren bei einer Temperatur zwischen 450°C und 535°C homogenisiert wird,
    d) der Walzbarren durch Warm- und wahlweise Kaltwalzen zu einem Blech mit einer Dicke von 0,5 bis 8 mm gewalzt wird,
    e) das Blech bei einer Temperatur zwischen 450°C und 535°C lösungsgeglüht und dann abgeschreckt wird,
    h) das Blech mit einer bleibenden Verformung von 0,5 bis 5 % kontrolliert gezogen wird, wobei die gesamte Kaltumformung nach Lösungsglühen und Abschrecken weniger als 15 % beträgt,
    i) eine Auslagerung durchgeführt wird, umfassend ein Erwärmen auf eine Temperatur zwischen 130 und 170°C und vorzugsweise zwischen 150 und 160°C für 5 bis 100 Stunden und vorzugsweise 10 bis 40 Stunden, wobei die Zusammensetzung und die Auslagerung so kombiniert werden, dass die Dehngrenze in Längsrichtung Rp0,2(L) zwischen 395 und 435 MPa liegt.
  12. Verwendung eines Blechs nach irgendeinem der Ansprüche 1 bis 10 in einer Rumpfplatte für Luftfahrzeuge.
EP14719034.2A 2013-04-03 2014-04-01 Bleche aus aluminium-kupfer-lithium-legierung zur herstellung von flugzeugrümpfen Active EP2981631B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1300763A FR3004196B1 (fr) 2013-04-03 2013-04-03 Toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion.
PCT/FR2014/000069 WO2014162068A1 (fr) 2013-04-03 2014-04-01 Tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion

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EP2981631A1 EP2981631A1 (de) 2016-02-10
EP2981631B1 true EP2981631B1 (de) 2017-08-02

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US (1) US20160060741A1 (de)
EP (1) EP2981631B1 (de)
CN (1) CN105102647B (de)
BR (1) BR112015024820B1 (de)
CA (1) CA2907807C (de)
FR (1) FR3004196B1 (de)
WO (1) WO2014162068A1 (de)

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CA3032261A1 (en) 2016-08-26 2018-03-01 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
CA3040622A1 (en) 2016-10-24 2018-05-03 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
FR3059578B1 (fr) * 2016-12-07 2019-06-28 Constellium Issoire Procede de fabrication d'un element de structure
US20180291489A1 (en) * 2017-04-11 2018-10-11 The Boeing Company Aluminum alloy with additions of copper, lithium and at least one alkali or rare earth metal, and method of manufacturing the same
DE102017116785B3 (de) * 2017-07-25 2019-01-24 P3 Aero Systems Gmbh Verfahren zum Überprüfen funktechnischer Eigenschaften eines Verkehrsmittels
US20190233921A1 (en) * 2018-02-01 2019-08-01 Kaiser Aluminum Fabricated Products, Llc Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application
FR3082210B1 (fr) * 2018-06-08 2020-06-05 Constellium Issoire Toles minces en alliage d’aluminium-cuivre-lithium pour la fabrication de fuselages d’avion
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WO2014162068A1 (fr) 2014-10-09
CA2907807C (fr) 2021-06-01
BR112015024820A2 (pt) 2017-07-18
CA2907807A1 (fr) 2014-10-09
EP2981631A1 (de) 2016-02-10
BR112015024820B1 (pt) 2020-05-12
CN105102647B (zh) 2017-10-13
CN105102647A (zh) 2015-11-25
FR3004196B1 (fr) 2016-05-06
US20160060741A1 (en) 2016-03-03

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