A. Suleman, P.A. Moniz, A.P. Costa, J. Rocha, B. Carreiro

In this paper, new design methods and concepts, aiming at improved performance, with less structural weight and better control effectiveness by using adaptive aeroelasticity to eliminate, create and modulate on command and in a controlled way the desired structural deformations induced by the aerodynamic loads are presented. Wind tunnel and flight RPV models were designed, fabricated, installed, and tested. Computational wing models were created, in order to determine the wing natural frequencies and modal shapes, and to calculate its flutter speed. A digital control law was designed and implemented. Open and closed loop vibration and flutter tests were conducted in the wind tunnel and in flight. The active spar wing concept is analyzed in this research: a wing with piezoelectric materials mounted in the main spar. The experimental results proved that the active wing vibration had improvements in almost all the RPV flying conditions compared to the corresponding passive wing vibration. Also, with the wind tunnel test it was demonstrated that the flutter speed of the active wings had increased, compared to the corresponding passive wings.

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;

actuators, aeroelasticity, aircraft structures

Bibliothek

2005