The flight-by-flight usage of 1,838 flight hrs consisting of 2,886 flights was recorded by the usage monitoring system installed on 8 Navy and 11 Marine helicopters. This information was used to obtain a flight sequence and regime sequence within a flight and the associated number of cycles in each regime to which the airframe was subjected during each flight. A harmonic analysis of the measured rotating hub loads was performed to obtain the amplitude and frequency content. The amplitude and frequency content of rotating frame loads was used to construct fixed system loads using Fourier Coordinate Transformation. The front and aft rotor hub loads were balanced by inertia loads at the aircraft center of gravity using the equations of motions.


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    Title :

    Development of a helicopter airframe flight-by-flight fatigue load spectrum


    Contributors:
    Moon, S. (author) / Peterson, H. (author) / Zhu, Tulong (author) / Divekar, A. (author)


    Publication date :

    1999


    Size :

    22 Seiten, 9 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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