Publikationsdatum:
2019-07-13
Beschreibung:
Helicopter blade-vortex interaction noise is one of the most severe noise sources and is very important both in community annoyance and military detection. Research over the decades has substantially improved basic physical understanding of the mechanisms generating rotor blade-vortex interaction noise and also of controlling techniques, particularly using active rotor control technology. This paper reviews active rotor control techniques currently available for rotor blade vortex interaction noise reduction, including higher harmonic pitch control, individual blade control, and on-blade control technologies. Basic physical mechanisms of each active control technique are reviewed in terms of noise reduction mechanism and controlling aerodynamic or structural parameters of a blade. Active rotor control techniques using smart structures/materials are discussed, including distributed smart actuators to induce local torsional or flapping deformations, Published by Elsevier Science Ltd.
Schlagwort(e):
Aerodynamics
Materialart:
NASA/TM-97-207568
,
NAS 1.15:207568
,
Progress in Aerospace Sciences (ISSN 0376-0421); 33; 647-687
Format:
application/pdf
Permalink
