An analytical and experimental program was conducted to develop acoustic fatigue design criteria for aircraft structures subjected to intense noise in a high temperature environment. Equations for the dynamic response of a buckled panel were formulated for simply supported boundary conditions using large deflection plate theory. Random amplitude acoustic fatigue testing of representative aircraft structure was accomplished at temperatures up to 600 F to provide data for correlation with the analytical results. Empirical design criteria are presented in the form of design equations and nomographs for predicting the combined thermal and dynamic response of aircraft structures.
Final rept. Apr 1972-Dec 1973
Prepared in cooperation with Acoustics and Vibration Associates, Inc., Smyrna, Ga. Rept. no. AVA/TR-72-184.