S. Hanagud, J.V.R. Prasad, T. Bowles, G.L. Nagesh Babu

During the operation of a rotorcraft, rotor blades interact with vortices shed by preceding blades. As a result of the interaction, large pressure pulses are created at the leading edge of the airfoil. In this paper, feasibilities studies have been conducted to investigate if a combination of active camber changes by the use of smart structures concepts and optimum control techniques can be used to reduce the magnitude of the large pressure pulse created by the interaction of the airfoil and vortices shed by the preceding blade. The optimum control techniques used in this paper include a technique based on the use of a quadratic performance index and a technique based on H[infinity] control concepts.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Dieser Aufsatz ist nicht Teil der Veröffentlichung!

aerodynamics, blade-vortex interaction, helicopters

Bestellbar

1991