Stress and deflection of honeycomb panels loaded by spatially uniform white noise.

Abstract

The stress and deflection response of lower harmonic modes relative to the fundamental mode is obtained theoretically for rectangular, simply supported honeycomb panels with isotropic facings and isotropic cores loaded by spatially uniform white noise. The panels are flat or cylindrically curved and shallow. It is quantitatively shown that when only the lower modes (including the fundamental mode) are excited, the response at the panel center is principally from the fundamental mode for square or nearly square honeycomb panels. Qualitative experimental evidence obtained in tests on flat honeycomb panels with aluminum core and facings supports this theoretical observation. Formulas and curves are presented for stress and deflection response at the panel center dependent on aspect ratio, cylindrical curvature, and the ratio of core shear rigidity to facing bending rigidity.