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.
Acoustic fatigue
Aircraft Eng
Aircraft Engineering ; 38 , n 7
1966
3 pages
Article (Journal)
English
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