Method of calculating fatigue life of panel subject to jet noise for aircraft ground and flight conditions; to calculate acoustic fatigue life of aircraft structure it is necessary to have rms S-N curves for each type of panel joint used in design; estimation of panel joint rms stress and of skin rms stress at rib positions is shown; with overall sound pressure level calculated for whole of flight and spectrum level distribution known, instantaneous values of rms stress can be estimated for variety of flight plans; scatter factor to be used in assessing panel life is proposed as eight; flight tests required to check estimated values of rms stress are given.


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    Title :

    Acoustic fatigue


    Additional title:

    Aircraft Eng


    Contributors:

    Published in:

    Publication date :

    1966


    Size :

    3 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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