| 摘要 |
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) + T(Ag) + 1.1 T(Mg) The life under stress (250 MPa) and at high temperature (150.degree.C) is thus very much longer (E1, E3) than the life of conventional alloys (Ref.).
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