A. Gravelle, M. Lepart, P. Lubrina

A complete modal identification method using aircraft flight control surfaces as exciters has been implemented. The excitation signals applied to several control surfaces are coherent sweep frequency signals. The measurements of the strain on the actuators shafts are used to determine the introduced forces allowing to derive the generalized masses. The method was applied first to a numerical model of a fighter aircraft, then a comparative ground vibration test of a MIRAGE 2000 aircraft has been performed by means of both the classical appropriation method and the present control surfaces excitation method. The consistency of the results obtained with the two methods is satisfactory and the control surface excitation method seems promising as far as the adaptation of the excitation can be realized for the different mode shapes.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 6 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.150-155; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991