D. Song, L. Librescu, C.A. Rogers

The static aeroelastic behavior of adaptive swept- forward wing aircraft modelled as thin-walled beams and incorporating piezoelectric effects is investigated. Based on the direct and converse piezoelectric effects, the system of piezoelectric sensors and actuators, conveniently located on the wing, yields a control of both aeroelastic divergence instability and, in the sub-critical speed range, of aeroelastic lift distribution. The numerical illustrations reveal the great capabilities of adaptive swept-forward wings to control their static aeroelastic behavior and, as a result, to fully exploit the advantages offered by such a wing aircraft configuration.

Workshop on Smart Material Systems and Structures, 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1991, 1991-09, Workshop on Smart Material Systems and Structures - Proceedings; S.46-55; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

structural design

Bestellbar

1991