T.A. Weisshaar, S.M. Ehlers

The use of piezoelectric materials to control the static aeroelastic response of a wing structure is examined. These materials are considered to be an integral part of the wing structure and are used together with a feedback control law to change the lift effectiveness of the wing and thus to generate forces and moments for maneuvering the aircraft. The limiting case of an unswept wing with only torsional flexibility is considered as is the case of a swept wing with coupled bending and torsioll. Among the conclusions drawn is the fact that piezoelectrical material requirements increase with aircraft weight. In addition, it is seen that piezoelectric material properties are coupled together with aircraft performance objectives and measures of structural stiffness.

Workshop on Smart Material Systems and Structures, 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

DGLR-Bericht, 1991, 1991-09, Workshop on Smart Material Systems and Structures - Proceedings; S.65-75; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

structural design

Bestellbar

1991