W.G. Luber

Modem fighter aircraft are using high sophisticated power control and automatic flight control systems, which basically are designed to maneuver the airplane and to provide sufficient damping for the rigid body modes. Since the sensors are attached to thc flexible structure, motions of the elastic aircraft will be measured and may influence the control system. In order to avoid instabilities it is necessary to predict the response of the aircraft with the control system and to correlate with flight test data. An analytical approach for the complete system including flight mechanics and unsteady aerodynamic forces is presented. The elastic structure is described by a set of normal modes which have been updated by results of ground resonance survey tests. Fluner calculations in open and closed loop on different flight conditions as weil as incidence variations are demonstrated as common flutter plots. For the flutter analysis a set of notch fitter is required, which should be determined in an integrated design step.

Aeroelastik-Tagung der DGLR; Göttingen 1998

Conference Paper

englisch

14,8 x 21,0 cm, 15 Seiten

DGLR-Bericht, 1998, 1998-01, Aeroelastik-Tagung der DGLR - Tagungsband; S.75-89; 1998; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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1998