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 transport aircraft lower wing skin stiffened panels of end load capacities 1.5 and 3 MN/m. Results show that the performance of 2024-T3 is much superior, owing mainly to greater retardation of crack growth after severe flights. The effect of load truncation is also greater for 2024-T3. The significance of the results in the choice of advanced structural concepts and materials as well as in the choice of truncation level is discussed. A recommendation for further investigation is given.


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    Title :

    Flight Simulation Fatigue Crack Propagation Evaluation of Candidate Lower Wing Skin Materials with Particular Consideration of Spectrum Truncation


    Contributors:

    Publication date :

    1979


    Size :

    34 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English