Flight simulation fatigue crack propagation tests were carried out on 2024-T3, 7475-T761, and mill annealed Ti-6Al-4V sheet in thicknesses up to 3 mm. These materials are representative of those used in transport aircraft lower wing skin stiffened panels with end load capacitied of 1.5 and 3 MN/m. The performance of 2024-T3 was much superior to the others, owing mainly to greater retardation of crack growth after severe flights. The effect of load truncation was also greater for 2024-T3. The significance of the results of the choice of advanced structural concepts and materials, and the choice of truncation level is discussed. A recommendation for further investigation is given.


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    Title :

    Gust Spectrum Fatigue Crack Propagation in Candidate Skin Materials


    Contributors:

    Publication date :

    1978


    Size :

    32 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English