| 2E12 is a newly developed domestic aluminum alloy material, which is intended to be used for fuselage skin.Whether the damage tolerance performance of the material meets the requirements and can be applied to the aircraft structure, the damage tolerance performance is one of the key indicators.According to the damage tolerance design requirements, this paper designed three typical test pieces of fuselage panel structure , including single span crack, double span crack and crack repair. First, the crack propagation and residual strength numerical analysis were completed, followed by the verification test, and the comparative analysis with the 2024 aluminum alloy test piece.The results show that the damage tolerance performance of 2E12 aluminum can meet the design requirements;Compared with single crack growth,the total life of multiple cracks is shortened about 30% ;the error between the crack growth analysis results and the test’s is less than 10%; the residual strength result of each test piece is very consistent, and the difference between the analysis result and the test result is about 2.3%. |
