Abstract
Control of low-frequency cabin noise is a difficult problem in all commercial aircraft. The subject is analyzed in terms of the response of a pressurized fuselage structure subjected to broadband random pressure fluctuations. It is shown that in the so called stiffness controlled region, the structural response and noise transmission may be governed by the resonances of the stiffeners, with the skin acting like an attached mass. As a result, cabin noise at low frequencies may be reduced by application of constrained viscoelastic damping treatments on the stringers and frames of the fuselage. Nomenclature a,Ast = stringer spacing and area of cross section b = frame spacing Cws = warping constant of the stringer cross section, about the point of skin contact Esk,Est = Young's modulii of the skin and the stringer materials / = frequency Gs( = shear modulus of the stringer material h = skin thickness I^Js = stringer moments of inertia in bending and torsion js( =St. Venant constant of uniform torsion for the
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