Effect of Airframe Materials on Spectrum Modification for Full Scale Fatigue Testing sf an Ageing Aircraft

Manjunatha, CM and Ranganath, VR (2006) Effect of Airframe Materials on Spectrum Modification for Full Scale Fatigue Testing sf an Ageing Aircraft. In: Proceedings of the 14th National Seminar on Aerospace Structures: Fatigue, Fracture and Ageing Structures, 30-31 Jan 2006, Nagpur, India.

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    Abstract

    In order to accelerate full scale fatigue testing, the original flight load spectrum of a combat aircraft was modified by eliminating small amplitude load excursions lower than a prefixed filter value. Different levels of filter value were used to derive several different test load spectrum having lesser number of fatigue cycles than the flight load spectrum. The fatigue crack growth behavior under all these spectrum load sequences was predicted in two different airframe materials viz., D16 aluminum and Ti6A14V alloys using a fatigue crack growth model derived from constant amplitude fatigue crack growth tests, which incorporated crack closure effects. Results show that the basis of spectrum modification should not only be the elimination of small amplitude load cycles but also on the fatigue crack growth behavior of the structural materials used in airframe construction.

    Item Type: Conference or Workshop Item (Paper)
    Uncontrolled Keywords: Full scale fatigue test;Spectrum load;Airframe materials
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Structural Integrity Division, Structural Integrity Division
    Depositing User: Ms. Alphones Mary
    Date Deposited: 23 Nov 2010 13:59
    Last Modified: 25 Nov 2010 14:09
    URI: http://nal-ir.nal.res.in/id/eprint/9104

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