<DOC>
<DOCNO>
729
</DOCNO>
<TITLE>
stresses in continuous skin stiffener panels under random loading .
</TITLE>
<AUTHOR>
lin, y.k.
</AUTHOR>
<BIBLIO>
j. aero. sc. january 1962 .
</BIBLIO>
<TEXT>
theoretical aspects involved in the prediction of stress levels for
continuous skin-stiffener panels subjected to a random pressure field
are considered in the light of powell's general theory for statistical
superposition of modal response . the choice of structural model is
dictated by the prevalence of skin-stiffener construction in modern
flight vehicle design . the present study clearly demonstrates that any
truly adequate prediction of stress levels in actual aircraft structures
 requires a much better representation of structural characteristics
than can be provided by single panel idealizations . in an example considering
fuselage panels exposed to jet engine noise, essential agreement
is shown with experimental data, although better correlation is
shown for rms stress than for power spectrum . it is shown that reduction
of stress level by increasing damping is effective only in the
higher frequency range .
</TEXT>
</DOC>
