A helicopter individual blade control (BC) system was tested on a full-scale BO 105 rotor in the NASA Ames 40- by 80-Foot Wind Tunnel. For this test, the rotating pitchlinks were prelaced by servo-actuators developed by ZF Luftfahrttechnik, Germany. Using these actuators, IBC inputs consisting of single-frequency harmonics (2P to 6P), pitch pulses, pitch wavelets, and doublet pitch schedules were introduced in an open-loop manner. IBC inputs of 1P-12P were also tested without blades. An extensive amount of data were acquired for each IBC data point. These data include rotor performance, vibratory hub forces and moments, blade loads, control system loads, blade root pitch motion, blade up accelerations, and BVI noise data. These data indicate very significant reductions of all vibratory rotor forces and moments and suppression of BVI noise using IBC.
Full-scale wind tunnel test of a helicopter individual blade control system
Ein im Maßstab 1:1 durchgeführter Windkanaltest eines individuellen Rotorblatt-Überwachungssystems für Hubschrauber
Forum, Annual Forum, American Helicopter Society, 50 ; 1 ; 579-596
1994
18 Seiten, 25 Bilder, 7 Tabellen, 23 Quellen
Conference paper
English
Full-scale wind tunnel investigation of a helicopter individual blade control system
Tema Archive | 1993
|FULL-SCALE WIND TUNNEL TEST OF AN INDIVIDUAL BLADE CONTROL SYSTEM FOR A UH-60 HELICOPTER
British Library Conference Proceedings | 2002
|British Library Conference Proceedings | 1996
|