Acoustic Fatigue of Aircraft Structures at Elevated Temperatures
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Report Number: AFFDL TR 73-155 Part 1
Author(s): Schneider, Cecil W.
Corporate Author(s): Lockheed-Georgia Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1974-03
Pages: 219
Contract: F33615-72-C-1141
DoD Project: 1471
DoD Task: 147101
Identifier: AD0920282
Abstract:
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.
Author(s): Schneider, Cecil W.
Corporate Author(s): Lockheed-Georgia Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1974-03
Pages: 219
Contract: F33615-72-C-1141
DoD Project: 1471
DoD Task: 147101
Identifier: AD0920282
Abstract:
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.