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DE03740569T1 - KNEE PRODUCTS OF A HIGH-MECHANICAL CHARACTERISTICS AL-ZN-MG-CU ALLOY AND STRUCTURAL COMPONENTS FOR AN AIRCRAFT - Google Patents

KNEE PRODUCTS OF A HIGH-MECHANICAL CHARACTERISTICS AL-ZN-MG-CU ALLOY AND STRUCTURAL COMPONENTS FOR AN AIRCRAFT Download PDF

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Publication number
DE03740569T1
DE03740569T1 DE03740569T DE03740569T DE03740569T1 DE 03740569 T1 DE03740569 T1 DE 03740569T1 DE 03740569 T DE03740569 T DE 03740569T DE 03740569 T DE03740569 T DE 03740569T DE 03740569 T1 DE03740569 T1 DE 03740569T1
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product according
mpa
stiffeners
elements
alloy
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DE03740569T
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German (de)
Inventor
Frank Eberl
Christophe Sigli
Timothy Warner
Sjoerd Van Der Veen
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Constellium Issoire SAS
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Pechiney Rhenalu SAS
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Application filed by Pechiney Rhenalu SAS filed Critical Pechiney Rhenalu SAS
Publication of DE03740569T1 publication Critical patent/DE03740569T1/en
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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
    • C22F1/053—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 zinc as the next major constituent
    • 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
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
  • Extrusion Of Metal (AREA)
  • Metal Rolling (AREA)
  • Conductive Materials (AREA)
  • Crushing And Pulverization Processes (AREA)
  • Preparation Of Clay, And Manufacture Of Mixtures Containing Clay Or Cement (AREA)
  • Physical Vapour Deposition (AREA)

Abstract

Walz-, Strangpress- oder Schmiedeerzeugnis aus AlZnMgCu-Legierung, dadurch gekennzeichnet, dass es enthält (in Masseprozent):
a) Zn 8,3–14,0 Cu 0,3–2,0 Mg 0,5–4,5
Zr 0,03–0,15 Fe + Si < 0,25;
b) mindestens ein aus der Gruppe bestehend aus Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb gewähltes Element, wobei der Gehalt eines jeden dieser Elemente, falls es gewählt wird, 0,02 bis 0,7% beträgt;
c) Rest Aluminium und unvermeidbare Verunreinigungen, und dass es folgende Bedingungen erfüllt:
d) Mg/Cu > 2,4 und
e) (7,9–0,4 Zn) > (Cu + Mg) > (6,4–0,4 Zn).Rolled, extruded or forged product of AlZnMgCu alloy, characterized in that it contains (in percentage by mass):
a) Zn 8.3-14.0 Cu 0.3-2.0 Mg 0.5-4.5
Zr 0.03-0.15 Fe + Si <0.25;
b) at least one element selected from the group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, the content of each of these elements, if chosen is 0.02 to 0.7%;
c) balance aluminum and unavoidable impurities, and that it meets the following conditions:
d) Mg / Cu> 2.4 and
e) (7.9-0.4 Zn)> (Cu + Mg)> (6.4-0.4 Zn).

Claims (28)

Walz-, Strangpress- oder Schmiedeerzeugnis aus AlZnMgCu-Legierung, dadurch gekennzeichnet, dass es enthält (in Masseprozent): a) Zn 8,3–14,0 Cu 0,3–2,0 Mg 0,5–4,5 Zr 0,03–0,15 Fe + Si < 0,25; b) mindestens ein aus der Gruppe bestehend aus Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb gewähltes Element, wobei der Gehalt eines jeden dieser Elemente, falls es gewählt wird, 0,02 bis 0,7% beträgt; c) Rest Aluminium und unvermeidbare Verunreinigungen, und dass es folgende Bedingungen erfüllt: d) Mg/Cu > 2,4 und e) (7,9–0,4 Zn) > (Cu + Mg) > (6,4–0,4 Zn).Rolled, extruded or forged product of AlZnMgCu alloy, characterized in that it contains (by mass): a) Zn 8.3-14.0 Cu 0.3-2.0 Mg 0.5-4.5 Zr 0.03-0.15 Fe + Si <0.25; b) at least one element selected from the group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, the content of each of these elements, if chosen is 0.02 to 0.7%; c) balance aluminum and unavoidable impurities, and that it satisfies the following conditions: d) Mg / Cu> 2.4 and e) (7.9-0.4 Zn)> (Cu + Mg)> (6.4-0 , 4 Zn). Erzeugnis nach Anspruch 1, dadurch gekennzeichnet, dass Mg/Cu > 2,8, bevorzugt > 3,5 und besonders bevorzugt > 4,0.Product according to claim 1, characterized in that that Mg / Cu> 2.8, preferably> 3.5 and particularly preferably> 4.0. Erzeugnis nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Massekonzentration der Elemente Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb insgesamt 1,5% nicht überschreitet.Product according to claim 1 or 2, characterized that the mass concentration of the elements Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, He, Y, Yb does not exceed 1.5%. Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass aus der Gruppe bestehend aus Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb nur Titan gewählt wird.Product according to any one of claims 1 to 3, characterized in that from the group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, He, Y, Yb only titanium is chosen. Walz-, Strangpress- oder Schmiedeerzeugnis aus AlZnMgCu-Legierung, dadurch gekennzeichnet, dass es enthält (in Masseprozent): a) Zn 9,5–14,0 Cu 0,3–2,0 Mg 0,5–4,5 Fe + Si < 0,25; b) mindestens ein aus der Gruppe bestehend aus Zr, Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, Cr, Mn gewähltes Element, wobei der Gehalt eines jeden dieser Elemente, falls es gewählt wird, 0,02 bis 0,7% beträgt; c) Rest Aluminium und unvermeidbare Verunreinigungen, und dass es folgende Bedingungen erfüllt: d) Mg/Cu > 2,4 und e) (7,9–0,4 Zn) > (Cu + Mg) > (6,4–0,4 Zn).Rolled, extruded or forged product of AlZnMgCu alloy, characterized in that it contains (in percentage by mass): a) Zn 9.5-14.0 Cu 0.3-2.0 mg 0.5-4.5 Fe + Si <0.25;  b) at least one of Zr, Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, Cr, Mn selected element, the content of each of these elements, if chosen, 0.02 to 0.7%; c) Rest aluminum and unavoidable impurities, and that it following Conditions fulfilled: d) Mg / Cu> 2.4 and e) (7.9 to 0.4 Zn)> (Cu + Mg)> (6.4-0.4 Zn). Erzeugnis nach Anspruch 5, dadurch gekennzeichnet, dass die Massekonzentration der Elemente Zr, Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb insgesamt 1,5% nicht überschreitet.Product according to claim 5, characterized in that in that the mass concentration of the elements Zr, Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb does not exceed 1.5%. Erzeugnis nach einem der Ansprüche 1 bis 4, wobei Zn > 9,0%.Product according to one of claims 1 to 4, wherein Zn> 9.0%. Erzeugnis nach Anspruch 7, wobei Zn > 9,5%.Product according to claim 7, wherein Zn> 9.5%. Erzeugnis nach Anspruch 7, wobei der Zinkgehalt 9,0% bis 11% beträgt.Product according to claim 7, wherein the zinc content is 9.0% up to 11%. Erzeugnis nach einem der Ansprüche 1 bis 9, wobei Cu > 0,6%.A product according to any one of claims 1 to 9, wherein Cu is> 0.6%. Erzeugnis nach irgendeinem der Ansprüche 1 bis 10, wobei Cu 0,6–1,2% und Mg 2,5–3,4% beträgt.Product according to any one of claims 1 to 10, where Cu is 0.6-1.2% and Mg 2.5-3.4% is. Erzeugnis nach irgendeinem der Ansprüche 1 bis 10, wobei Cu 0,8–1,5% und Mg 2,2–3,0% beträgt.Product according to any one of claims 1 to 10, where Cu is 0.8-1.5% and Mg 2.2-3.0% is. Erzeugnis nach irgendeinem der Ansprüche 1 bis 12, wobei Mg 0,5%–3,6% beträgt.Product according to any one of claims 1 to 12, where Mg is 0.5% -3.6% is. Erzeugnis nach irgendeinem der Ansprüche 1 bis 13, wobei Mg > 1,95 + 0,5(Cu–2,3) + 0,16(Zn–6) + 1,9(Si–0,04).Product according to any one of claims 1 to 13, where Mg> 1.95 + 0.5 (Cu-2.3) + 0.16 (Zn-6) + 1.9 (Si-0.04). Erzeugnis nach irgendeinem der Ansprüche 1 bis 14, wobei folgende Höchstkonzentrationen nicht überschritten werden: Cr 0,40 Mn 0,60 Sc 0,50 Zr 0,15 Hf 0,60 Ti 0,15 Ce, Nd und Eu jeweils 0,35 und bevorzugt jeweils 0,30 Gd 0,35 Tb 0,35 Ho 0,40 Dy 0,40 Er 0,40 Yb 0,40 Y 0,20.Product according to any one of claims 1 to 14, the following maximum concentrations not exceeded become: Cr 0.40 Mn 0.60 Sc 0.50 Zr 0.15 Hf 0.60 Ti 0.15 Ce, Nd and Eu each 0.35 and preferably 0.30 each Gd 0.35 Tb 0.35 Ho 0.40 Dy 0.40 He 0.40 Yb 0.40 Y 0.20. Erzeugnis nach irgendeinem der Ansprüche 1 bis 15, dadurch gekennzeichnet, dass es zusätzlich ein aus der Gruppe bestehend aus Ag, Sn, Cd, Ge, In gewähltes Element enthält, wobei der Gehalt eines jeden dieser Elemente, falls es gewählt wird, 0,02% bis 0,15% und bevorzugt 0,05% bis 0,10% beträgt.Product according to any one of claims 1 to 15, characterized in that it additionally consists of one of the group selected from Ag, Sn, Cd, Ge, In Contains element the content of each of these elements, if chosen, 0.02% to 0.15% and preferably 0.05% to 0.10%. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 16, dadurch gekennzeichnet, dass es im Zustand T6511, gemessen an aus einem flachen Abschnitt entnommenen Proben: a) einen Biegewinkel, gemessen bei 130°C mit einem 3-Punkt-Biegetest nach DIN 50 111 (Abschnitt 3.1) an einer Probe von 1,6 mm Dicke und ausgedrückt als Mittelwert berechnet aus an verschiedenen, über die Länge des Profils verteilten Stellen entnommenen Proben durchgeführten Einzelberechnungen, von mindestens 34° und b) eine Dehngrenze Rp0,2 von mindestens 720 MPa, und bevorzugt einen Biegewinkel von mindestens 35° und eine Dehngrenze von mindestens 750 MPa aufweist.Extruded product according to any one of claims 1 to 16, characterized in that it is in the condition T6511, measured on samples taken from a flat section: a) a bending angle, measured at 130 ° C with a 3-point bending test according to DIN 50 111 (Section 3.1) on a sample of 1.6 mm thickness and expressed as an average calculated from individual samples taken at different locations over the length of the profile, of at least 34 ° and b) a yield strength R p0.2 of at least 720 MPa, and preferably has a bending angle of at least 35 ° and a yield strength of at least 750 MPa. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 16, dadurch gekennzeichnet, dass es im Zustand T76511, gemessen an aus einem flachen Abschnitt entnommenen Proben: a) einen Biegewinkel, gemessen bei 130°C mit einem 3-Punkt-Biegetest nach DIN 50 191 (Abschnitt 3.1) an einer Probe von 1,6 mm Dicke und ausgedrückt als Mittelwert berechnet aus an verschiedenen, über die Länge des Profils verteilten Stellen entnommenen Proben durchgeführten Einzelberechnungen, von mindestens 37° und bevorzugt mindestens 40° und b) eine Dehngrenze Rp0,2 von mindestens 670 MPa aufweist.Extruded product according to any one of claims 1 to 16, characterized in that it is in the state T76511, measured on samples taken from a flat section: a) a bending angle, measured at 130 ° C with a 3-point bending test according to DIN 50 191 (Section 3.1) on a sample of 1.6 mm thickness and expressed as an average calculated from individual samples taken at different locations over the length of the profile, of at least 37 ° and preferably at least 40 ° and b) has a yield strength R p0.2 of at least 670 MPa. Strangpresserzeugnis nach Anspruch 18, dadurch gekennzeichnet, dass die Korrosionsfestigkeit, bestimmt nach dem EXCO-Test (Norm ASTM G34) im Zustand T6511 an unbearbeiteten Proben mindestens dem Niveau EB entspricht.Extruded product according to claim 18, characterized in that that the corrosion resistance, determined according to the EXCO test (Norm ASTM G34) in condition T6511 on unprocessed samples at least the Level EB corresponds. Strukturelement für Luftfahrzeuge, hergestellt aus einem Erzeugnis nach irgendeinem der Ansprüche 1 bis 19.Structural element for aircraft, made from A product according to any one of claims 1 to 19. Strukturelement nach Anspruch 20, dadurch gekennzeichnet, dass das Element eine Rumpfverstärkung ist.Structural element according to claim 20, characterized that the element has a hull reinforcement is. Strukturelement nach Anspruch 20, dadurch gekennzeichnet, dass das Element eine Sitzschiene ist.Structural element according to claim 20, characterized that the element is a seat rail. Sitzschiene nach Anspruch 22, dadurch gekennzeichnet, dass ihre Bruchfestigkeit im Zustand T76511 im Befestigungsbereich der Sitze mindestens 670 MPa und bevorzugt mindestens 680 MPa beträgt.Seat rail according to claim 22, characterized that their breaking strength in the state T76511 in the attachment area the seats is at least 670 MPa and preferably at least 680 MPa. Sitzschiene nach Anspruch 22 oder 23, dadurch gekennzeichnet, dass ihre Dehngrenze im Zustand T76511 im Befestigungsbereich der Sitze mindestens 640 MPa und bevorzugt mindestens 660 MPa beträgt.Seat rail according to claim 22 or 23, characterized that their yield strength in the state T76511 in the attachment area of Seats at least 640 MPa and preferably at least 660 MPa. Strukturelement nach Anspruch 20, dadurch gekennzeichnet, dass das Element ein Fußbodenprofil ist.Structural element according to claim 20, characterized that the element has a floor profile is. Luftfahrzeug mit einem aus einer Vielzahl von Versteifungen und einer Vielzahl von Blechen zusammengesetzten Rumpf, dadurch gekennzeichnet, dass mindestens ein Teil der Versteifungen Strukturelemente nach Anspruch 20 sind.Aircraft with one of a variety of stiffeners and a plurality of sheets of composite hull, characterized in that at least part of the stiffeners structural elements according to claim 20 are. Rumpfstruktur zusammengesetzt aus einer Vielzahl von Verstärkungen nach Anspruch 21 und einer Vielzahl von Blechen, dadurch gekennzeichnet, dass bei einem Abstand der Versteifungen von 200 mm und einem Versteifungsfaktor (Querschnitt der Versteifung/Gesamtquerschnitt) von 0,25 der Spannungsintensitätsfaktor für einen Riss mit einer Länge von zwei Versteifungen mit gebrochener Mittelversteifung um mindestens 5% im Vergleich zu Versteifungen aus einer Legierung 2024 T3 reduziert ist.Hull structure composed of a variety of reinforcements according to claim 21 and a plurality of sheets, characterized in that at a distance of the stiffeners of 200 mm and a stiffening factor (Cross section of stiffening / total cross section) of 0.25 the stress intensity factor for one Crack with a length of two stiffeners with broken central stiffening by at least 5% compared to stiffeners made of an alloy 2024 T3 reduced is. Rumpfstruktur zusammengesetzt aus einer Vielzahl von Verstärkungen nach Anspruch 21 und einer Vielzahl von Blechen, dadurch gekennzeichnet, dass die Knickfestigkeit der Versteifungen um mindestens 15% im Vergleich zu derselben Struktur mit Z-förmigen Versteifungen gleicher Geometrie aus einer Legierung 7150 T77511 verbessert ist.Hull structure composed of a variety of reinforcements according to claim 21 and a plurality of sheets, characterized in that the kink resistance of the stiffeners by at least 15% in comparison to the same structure with Z-shaped Stiffeners of the same geometry made of an alloy 7150 T77511 is improved.
DE03740569T 2002-04-05 2003-04-04 KNEE PRODUCTS OF A HIGH-MECHANICAL CHARACTERISTICS AL-ZN-MG-CU ALLOY AND STRUCTURAL COMPONENTS FOR AN AIRCRAFT Pending DE03740569T1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0204250 2002-04-05
FR0204250A FR2838135B1 (en) 2002-04-05 2002-04-05 CORROSIVE ALLOY PRODUCTS A1-Zn-Mg-Cu WITH VERY HIGH MECHANICAL CHARACTERISTICS, AND AIRCRAFT STRUCTURE ELEMENTS
PCT/FR2003/001063 WO2003085146A1 (en) 2002-04-05 2003-04-04 Al-zn-mg-cu alloys welded products with high mechanical properties, and aircraft structural elements

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DE03740569T1 true DE03740569T1 (en) 2005-06-23

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DE03740569T Pending DE03740569T1 (en) 2002-04-05 2003-04-04 KNEE PRODUCTS OF A HIGH-MECHANICAL CHARACTERISTICS AL-ZN-MG-CU ALLOY AND STRUCTURAL COMPONENTS FOR AN AIRCRAFT

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US (2) US20050072497A1 (en)
EP (1) EP1492896B1 (en)
JP (1) JP2005530032A (en)
AT (1) ATE415498T1 (en)
AU (1) AU2003260003A1 (en)
DE (2) DE60324903D1 (en)
ES (1) ES2316779T3 (en)
FR (1) FR2838135B1 (en)
WO (1) WO2003085146A1 (en)

Families Citing this family (64)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2292331B2 (en) * 2003-03-17 2009-09-16 Corus Aluminium Walzprodukte Gmbh METHOD TO PRODUCE A MONOLITICAL STRUCTURE OF INTEGRATED ALUMINUM AND A MACHINED ALUMINUM PRODUCT FROM THAT STRUCTURE.
CN101693968B (en) * 2003-04-10 2013-09-18 克里斯铝轧制品有限公司 Al-zn-mg-cu alloy
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
US20060032560A1 (en) * 2003-10-29 2006-02-16 Corus Aluminium Walzprodukte Gmbh Method for producing a high damage tolerant aluminium alloy
US7883591B2 (en) * 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
ES2292075T5 (en) * 2005-01-19 2010-12-17 Otto Fuchs Kg ALUMINUM ALLOY NOT SENSITIVE TO BRUSH COOLING, AS WELL AS A PROCEDURE FOR MANUFACTURING A SEMI-FINISHED PRODUCT FROM THIS ALLOY.
EP1848835A2 (en) 2005-02-01 2007-10-31 Timothy Langan Aluminum-zinc-magnesium-scandium alloys and methods of fabricating same
US8157932B2 (en) * 2005-05-25 2012-04-17 Alcoa Inc. Al-Zn-Mg-Cu-Sc high strength alloy for aerospace and automotive castings
US20060289093A1 (en) * 2005-05-25 2006-12-28 Howmet Corporation Al-Zn-Mg-Ag high-strength alloy for aerospace and automotive castings
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
US8083871B2 (en) * 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
WO2008005852A2 (en) * 2006-06-30 2008-01-10 Alcan Rolled Products-Ravenswood, Llc, High strength, heat treatable al-zn-mg aluminium alloy
WO2008003506A2 (en) * 2006-07-07 2008-01-10 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminium alloy products and a method of manufacturing thereof
CN101484604B (en) * 2006-07-07 2013-01-09 阿勒里斯铝业科布伦茨有限公司 Aa7000-series aluminium alloy products and a method of manufacturing thereof
FR2910874B1 (en) 2007-01-02 2009-02-13 Airbus France Sas SMOOTH ASSEMBLIES AT THE LEVEL OF A CIRCUMFERENTIAL JUNCTION OF AN AIRCRAFT FUSELAGE.
EP2274454B1 (en) 2007-03-30 2020-11-25 Director General, Defence Research & Development Organisation Alloy composition and preparation thereof
US8840737B2 (en) * 2007-05-14 2014-09-23 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8673209B2 (en) * 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8002912B2 (en) 2008-04-18 2011-08-23 United Technologies Corporation High strength L12 aluminum alloys
US8017072B2 (en) 2008-04-18 2011-09-13 United Technologies Corporation Dispersion strengthened L12 aluminum alloys
US7811395B2 (en) 2008-04-18 2010-10-12 United Technologies Corporation High strength L12 aluminum alloys
US7875131B2 (en) 2008-04-18 2011-01-25 United Technologies Corporation L12 strengthened amorphous aluminum alloys
US8409373B2 (en) 2008-04-18 2013-04-02 United Technologies Corporation L12 aluminum alloys with bimodal and trimodal distribution
US20090263273A1 (en) 2008-04-18 2009-10-22 United Technologies Corporation High strength L12 aluminum alloys
US7875133B2 (en) 2008-04-18 2011-01-25 United Technologies Corporation Heat treatable L12 aluminum alloys
US7871477B2 (en) 2008-04-18 2011-01-18 United Technologies Corporation High strength L12 aluminum alloys
US7879162B2 (en) 2008-04-18 2011-02-01 United Technologies Corporation High strength aluminum alloys with L12 precipitates
US8778098B2 (en) 2008-12-09 2014-07-15 United Technologies Corporation Method for producing high strength aluminum alloy powder containing L12 intermetallic dispersoids
US8778099B2 (en) 2008-12-09 2014-07-15 United Technologies Corporation Conversion process for heat treatable L12 aluminum alloys
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
US9611522B2 (en) 2009-05-06 2017-04-04 United Technologies Corporation Spray deposition of L12 aluminum alloys
US9127334B2 (en) 2009-05-07 2015-09-08 United Technologies Corporation Direct forging and rolling of L12 aluminum alloys for armor applications
US8728389B2 (en) 2009-09-01 2014-05-20 United Technologies Corporation Fabrication of L12 aluminum alloy tanks and other vessels by roll forming, spin forming, and friction stir welding
US8409496B2 (en) 2009-09-14 2013-04-02 United Technologies Corporation Superplastic forming high strength L12 aluminum alloys
US9194027B2 (en) 2009-10-14 2015-11-24 United Technologies Corporation Method of forming high strength aluminum alloy parts containing L12 intermetallic dispersoids by ring rolling
US8409497B2 (en) 2009-10-16 2013-04-02 United Technologies Corporation Hot and cold rolling high strength L12 aluminum alloys
CN102108463B (en) * 2010-01-29 2012-09-05 北京有色金属研究总院 Aluminium alloy product suitable for manufacturing structures and preparation method
US9163304B2 (en) 2010-04-20 2015-10-20 Alcoa Inc. High strength forged aluminum alloy products
JP5535957B2 (en) 2011-02-21 2014-07-02 三菱航空機株式会社 Formation method of wing panel
US9551050B2 (en) * 2012-02-29 2017-01-24 The Boeing Company Aluminum alloy with additions of scandium, zirconium and erbium
KR101526661B1 (en) 2013-05-07 2015-06-05 현대자동차주식회사 Wear-resistant alloys having a complex microstructure
KR101526656B1 (en) 2013-05-07 2015-06-05 현대자동차주식회사 Wear-resistant alloys having a complex microstructure
KR101526660B1 (en) 2013-05-07 2015-06-05 현대자동차주식회사 Wear-resistant alloys having a complex microstructure
CN105377469B (en) * 2013-07-12 2018-08-10 麦格纳国际公司 The method for being used to form the aluminium alloy part with special mechanical performance
DE102013012259B3 (en) 2013-07-24 2014-10-09 Airbus Defence and Space GmbH Aluminum material with improved precipitation hardening, process for its production and use of the aluminum material
CN103572106B (en) * 2013-11-22 2016-08-17 湖南稀土金属材料研究院 Aluminum alloy materials
WO2015132932A1 (en) 2014-03-06 2015-09-11 株式会社Uacj Structural aluminum alloy and process for producing same
CN104109784B (en) * 2014-04-30 2016-09-14 广西南南铝加工有限公司 A kind of superhigh intensity Al-Zn-Mg-Cu aluminum alloy big specification rectangle ingot and manufacture method thereof
JP6638193B2 (en) * 2015-02-20 2020-01-29 日本軽金属株式会社 Aluminum alloy processing material and method of manufacturing the same
JP6638192B2 (en) * 2015-02-20 2020-01-29 日本軽金属株式会社 Aluminum alloy processing material and method of manufacturing the same
CN106367644B (en) * 2016-09-23 2018-03-13 北京工业大学 A kind of superelevation is strong, high rigidity TiB2Particle REINFORCED Al Zn Mg Cu composites and preparation method thereof
CN106399776B (en) * 2016-11-11 2018-05-01 佛山科学技术学院 A kind of 800MPa grades of ultra-high-strength aluminum alloy and preparation method thereof
US11879166B2 (en) 2018-11-12 2024-01-23 Novelis Koblenz Gmbh 7XXX-series aluminium alloy product
CN109977457B (en) * 2019-02-02 2020-11-24 浙江大学 A method for predicting the ultimate load of vanadium-added steel cylinder joints considering the influence of warm coils
US11958140B2 (en) 2019-05-10 2024-04-16 General Cable Technologies Corporation Aluminum welding alloys with improved performance
CN110331319B (en) * 2019-05-27 2020-06-30 中国航发北京航空材料研究院 High-strength and high-plasticity corrosion-resistant aluminum alloy containing scandium and erbium and preparation method thereof
CA3125048A1 (en) 2019-06-03 2021-02-18 Novelis Inc. Ultra-high strength aluminum alloy products and methods of making the same
CN112226636A (en) * 2020-09-08 2021-01-15 烟台南山学院 Preparation method of high-strength corrosion-resistant Al-Zn-Mg-Cu-Zr-Ce alloy plate
CN112981196B (en) * 2021-02-10 2022-04-22 北京科技大学 Ultrahigh-strength and high-toughness Al-Zn-Mg-Cu aluminum alloy and preparation method thereof
CN115216674B (en) * 2022-07-11 2023-02-24 上海交通大学 7000 series aluminum alloy sheet for automobile and preparation method thereof
FR3138122A1 (en) * 2022-07-25 2024-01-26 Airbus Operations Aircraft cabin floor grid transport system for assembling an aircraft fuselage body and method of calibrating said transport system.
CN115287511A (en) * 2022-09-06 2022-11-04 安徽辉隆集团辉铝新材料科技有限公司 7020 superhard aluminum alloy section and preparation method thereof
CN115537615A (en) * 2022-10-26 2022-12-30 山东南山铝业股份有限公司 High-brightness aluminum alloy for automobile door and window trim and preparation method

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
US4063936A (en) * 1974-01-14 1977-12-20 Alloy Trading Co., Ltd. Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack
FR2457908A1 (en) * 1979-06-01 1980-12-26 Gerzat Metallurg PROCESS FOR PRODUCING HOLLOW BODIES OF ALUMINUM ALLOY AND PRODUCTS THUS OBTAINED
FR2517702B1 (en) * 1981-12-03 1985-11-15 Gerzat Metallurg
JPH0635624B2 (en) * 1985-05-10 1994-05-11 昭和アルミニウム株式会社 Manufacturing method of high strength aluminum alloy extruded material
FR2601967B1 (en) 1986-07-24 1992-04-03 Cerzat Ste Metallurg AL-BASED ALLOY FOR HOLLOW BODIES UNDER PRESSURE.
US5221377A (en) 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
FR2640644B1 (en) * 1988-12-19 1991-02-01 Pechiney Recherche PROCESS FOR OBTAINING "SPRAY-DEPOSIT" ALLOYS FROM AL OF THE 7000 SERIES AND COMPOSITE MATERIALS WITH DISCONTINUOUS REINFORCEMENTS HAVING THESE ALLOYS WITH HIGH MECHANICAL RESISTANCE AND GOOD DUCTILITY
FR2716896B1 (en) * 1994-03-02 1996-04-26 Pechiney Recherche Alloy 7000 with high mechanical resistance and process for obtaining it.
US6562154B1 (en) * 2000-06-12 2003-05-13 Aloca Inc. Aluminum sheet products having improved fatigue crack growth resistance and methods of making same
FR2838136B1 (en) * 2002-04-05 2005-01-28 Pechiney Rhenalu ALLOY PRODUCTS A1-Zn-Mg-Cu HAS COMPROMISED STATISTICAL CHARACTERISTICS / DAMAGE TOLERANCE IMPROVED
US7060139B2 (en) * 2002-11-08 2006-06-13 Ues, Inc. High strength aluminum alloy composition

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