J.E. Cooper, P.R. Emmett, J.R. Wright, M.J. Schofield

In this paper a new tool for flutter clearance is presented, intended to be complementary to other approaches. The method is based on quantifying the change in the shape of the decay envelope associated with control pulse responses or impulse response functions. An indication of overall stability is obtained without curve fitting via a shape parameter which shows quickly whether there has been any significant change since the last test point. In addition the envelope functions can be overlayed from different speeds. The method is illustrated upon data from a simulated aeroelastic model of a multi-engined transport aircraft and effects of turbulence considered.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.578-586; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991