Estimation of the r.m.s. stress in skin panels subjected to random acoustic loading.
Abstract:A complete theory to describe the response of aircraft structures to acoustic loads has been developed by Powell but because of its complexity it cannot readily be used for design. ESDU 67028 outlines the complete theory for the estimation of the spectral density of stresses in order to show the significance of the major parameters and also the limitations, in practice, of any simplified theory. Graphs show the comparison of estimated and measured surface r.m.s. stresses on flat plates and aircraft control surfaces. The important parameters in determining the response of typical aircraft structures to high intensity acoustic loads are outlined in ESDU 20005.
|Data Item ESDU 67028|