P.P. Friedmann

This paper describes research on actively controlled partial span trailing edge flaps that can be used for vibration and noise reduction in rotorcraft. It traces the evolution of this concept and describes the basic features of aeroelastic simulation codes needed for predicting the performance of actively controlled flaps. Validation of a simulation code is also presented by comparing the results obtained with experimental data. The vibration and noise reduction potential of this approach is illustrated by several examples. Full scale implementations of this approach in both the US and Europe are also discussed. Simultaneous noise and vibration reduction has been also demonstrated in recent simulation. It is shown that the primary problem in this approach is a relatively small drag penalty. This drag penalty can be alleviated by judicious design. Thus the concept has remarkable potential for improving rotorcraft technology.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 32 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-32; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

flaps (control surfaces), noise reduction, vibration reduction

Bibliothek

2005