M.N.F. Acton, M.F. Platten, J.R. Wright, D. Bond, A. Olsson

In the aerospace industry, the problem of predicting the response of a panel type structure to acoustic loading is becoming more important. Experimental data indicates the presence of peak broadening and upwards frequency shift in the Power Spectral Density found in a Progressive Wave Tube test. Such behaviour is typically attributed to non-linear hardening stiffness due the stretching of the panel centre line. However, it is possible that some of the features may also be due to damping non-linearities. In this paper, the variation in Kurtosis of the random response with excitation level is examined as a potential indicator of non-linear stiffness or damping. Initially a simulation is performed and shows that Kurtosis can indicate such behaviour. Then a clamped plate structure is tested using narrow band random excitation centred about the natural frequency of the first mode, with and without the presence of a discrete non-linear damper. Results for Kurtosis show similar characteristics to those seen for the simulation. The method has promise for handing higher frequency modes by applying the approach on a mode by mode basis.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-12; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

damping, nonlinearity, structural dynamics

Bibliothek

2005