In order to meet the development needs of high-speed, light-weight, high-reliability and low-cost modern aircraft, designers have Aluminum alloys put forward more stringent requirements . The design idea of ââaircraft is no longer limited to the original static strength design, and has transformed into higher requirements for safety life design, safety life/damage safety design, safety life/damage tolerance design and durability/damage tolerance design  . For this reason, it is necessary to explore the fatigue properties of aviation aluminum alloy materials as the basis for the reliability design of modern aircraft. High-strength aluminum alloys include copper-containing 2xxx series aluminum alloys and zinc-containing 7xxx series aluminum alloys, which are widely used in the aviation field due to their excellent mechanical properties .
2A70 High Strength Aluminum Alloy Forgings belong to the Al-Cu-Mg-FeNi series of high-strength deformed aluminum alloys, which have the advantages of strong plasticity, easy forging, low density, and good high temperature resistance . At present, the research on
2A70 High Strength Aluminum Alloy Forgings at home and abroad mainly focuses on processing technology [5-7], microstructure [8-9], mechanical properties [10-11], etc., but there are few studies on fatigue properties.
In order to clarify the fatigue properties of 2A70 High Strength Aluminum Alloy Forgings, this paper carried out high-circumferential axial tensile-compression fatigue tests with 2A70 aluminum alloy stress ratio R=-1, temperature T=25â, and 150â. Based on the microstructure observation results, combined with the experimental S-N curve and typical fracture observation, the fatigue limit of 2A70 at different temperatures and the effect of temperature on the fatigue characteristics were determined, and the high-cycle fatigue failure mode and failure mechanism of 2A70 were clarified.