P.P. Friedmann

The use of active controls whereby the pitch of a helicopter rotor blade is modified by a control system so as to alleviate dynamic effects represents a typical aeroservoelastic problem. The level and scope of activity in this area has been increasing steadily during the last twenty years, and the body of literature which exists in this area is quite substantial. The purpose of this paper to provide an assessment of the state-of-the-art in this field, to identify the more promising developments, and speculate on potentially useful future activities. The specific topics covered in this paper are: (1) active control of aeromechanical and aeroelastic problems; (2) individual blade control; (3) active control for vibration reduction using a conventional swashplate; and (4) coupled rotor/fuselage vibration reduction using open-loop active control. The paper contains a selected number of representative results which illustrate the various applications mentioned above.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 15 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.481-495; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991