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Abstract: The high noise levels experienced by a launch vehicle during lift off and trans-atmospheric flight can cause vibration induced damage of on-board payloads and other critical systems of the vehicle itself. Acoustic test facilities simulate such noise spectra in a large reverberation chamber to qualify space bound hardware for structural integrity. The induced vibration response measured for a given input acoustic load will provide an estimate of the capability of the structure in withstanding such loads during the actual launch phase. All test facilities may not be capable of adapting to the changing sound pressure level requirements at the desired frequencies due to limitations in the installed noise generation sources. Extrapolation of the vibration response at the maximum sound pressure levels capable of being generated to the actually required sound pressure level spectra is inevitable in many cases. However, the accuracy of the extrapolated results depends on a number of factors. This paper deals with the factors which influence the prediction of the vibration response using extrapolation techniques, compared to the results obtained by actual experimental studies conducted on a typical test structure in a large reverberation chamber.
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