With the continuous development of the modern aerospace field, nuclear industry, and transportation industry, higher requirements are put forward for the comprehensive performance of structural parts. A new generation of ultra-high-strength aluminum alloy that combines light weight, high strength, high toughness, high fracture toughness, and stress corrosion resistance is undoubtedly the first choice.
The traditional aluminum alloys for large aircraft structures are mainly high-strength 2000 series(2024, 2224, 2324,2424, 2524,etc.) and 7000 series( 7075, 7475, 7050, 7055, 7085,etc.) After the 1980s, although there are some new materials like aluminum-lithium alloys, rapidly solidified aluminum alloys, and composite materials, traditional aluminum alloys like 2000 and 7000 series still show strong vitality.
7075 aluminum welding is a high strength, heat treatable wrought alloy developed by Alcoa in 1943. The alloy contains zinc, magnesium, chromium and copper as hardeners, and small amounts of iron, silicon, manganese and titanium. Al-7075 is much stronger than carbon steel after heat treatment. The common tempers are 7075-T6, T651, T7351, T73, T76, T7651, O, W, W51, etc.
These excellent properties make 7075 aircraft aluminum widely used in aerospace and related fields, especially in the manufacture of aircraft structures and other high-stress structures that require high strength and strong corrosion resistance, such as the front fuselage stringer of C919 aircraft, middle fuselage stringer, keel beam flange, keel beam web, floor transition beam, middle and rear fuselage stringer and cargo door frame.
2024 aluminum alloy belongs to the Al-Cu-Mg series high-strength deformed aluminum alloy, which is widely used in aviation, aerospace and other military products. The heat treatment state commonly used in aviation parts is the T42 (solid solution + natural aging) state.
AA2024 is mainly alloyed with copper. It also contains manganese and magnesium and may sometimes contain smaller amounts of silicon, iron, chromium, zinc and/or titanium. The common tempers are T3, T4/T351 and T851. It is stronger than 6061, but less versatile. While 7075 is suitable for applications requiring high stress and strain resistance, 2024 has high resistance to cyclic fatigue.
Original Source:https://www.aircraftaluminium.com/a/why-is-aluminum-used-for-aircraft-bodies-primarily.html
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