Aircraft structural element, particularly for a supersonic...

Details Aircraft structural element, particularly for a supersonic... Aircraft structural element, particularly for a supersonic...

C - Chemistry, Metallurgy

22

C

C22C 21/16 (2006.01) C22C 21/14 (2006.01)

Patent

CA 2182058

An aircraft structural element, such as a supersonic aircraft fuselage skin or wing, or a frame or reinforcement in contact with this skin is made from an aluminium alloy that contains between 2.00 and 3.00% by weight of copper, between 1.40 and 1.90% of magnesium, between 0.20 and 0.70% of manganese, between 0 and 0.30% of iron, between 0 and 0.30% of nickel, between 0 and 0.15% of titanium, at least 0.05% of silicon and between 0 and 1.10% of silver. Furthermore, the silicon content T(Si), the silver content T(Ag) and the magnesium content T(Mg) satisfy the following relations: 0.40 <= T(Si) + 0.4 T(Ag) <= 0.6 and (1) T(Si) + T(Ag) + 1.1 T(Mg) <= 2.6 (2) The life under stress (250 MPa) and at high temperature (150°C) is thus very much longer (E1, E3) than the life of conventional alloys (Ref.).

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