EP 1891247 B1 20081112 - HIGH-STRENGTH ALUMINUM-COPPER-LITHIUM SHEET METAL FOR AIRCRAFT FUSELAGES
Title (en)
HIGH-STRENGTH ALUMINUM-COPPER-LITHIUM SHEET METAL FOR AIRCRAFT FUSELAGES
Title (de)
HOCHFESTES ALUMINIUM-KUPFER-LITHIUM-BLECH FÜR FLUGZEUGRÜMPFE
Title (fr)
TOLE EN ALUMINIUM-CUIVRE-LITHIUM A HAUTE TENACITE POUR FUSELAGE D'AVION
Publication
Application
Priority
- FR 2006001250 W 20060602
- US 68744405 P 20050606
- FR 0508374 A 20050805
Abstract (en)
[origin: WO2006131627A1] The invention relates to an aluminum-based alloy having a low density that is useful in an aircraft structure for fuselage sheet metal applications that have a high mechanical resistance, a high level of strength and a high resistance to corrosion, containing in % by weight, 2.7 to 3.4 of Cu, 0.8 to 1.4 of Li, 0.1 to 0.8 of Ag, 0.2 to 0.6 of Mg and an element such as Zr, Mn, Cr, Sc, Hf, Ti or a combination thereof, of which the quantity, in % by weight, is 0.05 to 0.13 for Zr, 0.05 to 0.8 for Mn, 0.05 to 0.3 for Cr and Sc, 0.05 to 0.5 for Hf and 0.05 to 0.15 for Ti. The quantity of Cu and of Li is determined according to the formula Cu ( % by weight) + 5/3 Li ( % by weight) < 5.2.
IPC 8 full level
C22C 21/12 (2006.01); C22F 1/057 (2006.01)
CPC (source: EP)
C22C 21/12 (2013.01); C22F 1/057 (2013.01)
Designated contracting state (EPC)
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR
DOCDB simple family (publication)
WO 2006131627 A1 20061214; AT E414183 T1 20081115; BR PI0610937 A2 20100803; BR PI0610937 B1 20151208; CA 2608971 A1 20061214; CA 2608971 C 20140916; DE 602006003656 D1 20081224; EP 1891247 A1 20080227; EP 1891247 B1 20081112; EP 2017361 A1 20090121; ES 2314929 T3 20090316; RU 2007145191 A 20090610; RU 2415960 C2 20110410
DOCDB simple family (application)
FR 2006001250 W 20060602; AT 06764718 T 20060602; BR PI0610937 A 20060602; CA 2608971 A 20060602; DE 602006003656 T 20060602; EP 06764718 A 20060602; EP 08018130 A 20060602; ES 06764718 T 20060602; RU 2007145191 A 20060602