TY - GEN
T1 - Evaluation of fluidic pitch links for rotor hub vibration controls
AU - Zhang, Jianhua
AU - Smith, Edward C.
AU - Scarborough, Lloyd H.
AU - Rahn, Christopher D.
AU - Jolly, Mark R.
PY - 2014
Y1 - 2014
N2 - Researchers have been exploring the potential for fluidic pitch links to replace traditional rigid pitch links for rotorcraft vibration reduction. Previous studies showed that the hub vibratory loads of a medium-sized helicopter with an articulated rotor system in high speed flight condition could be affected by tailoring the fluidic pitch link impedance. The current research is intended to advance and expand studies of the fluidic pitch link concept. A free wake model is implemented in rotor aeroelastic modeling. The fluidic pitch links have been examined at low forward speed for the vehicle, the results show that they can achieve average 39% vibration reduction at advance ratio 0.15. Fluidic pitch links are also be evaluated on a light helicopter with a hingeless rotor system. Parametric studies of fluidic pitch link properties are conducted, and their effect on rotor hub vibratory loads is evaluated at both low and high forward speeds for its off-design performance. The results indicate that fluidic pitch links work very well at advance ratio of 0.30, and can reduce hub loads by average 45%. The fluidic pitch links are also compared with the active individual blade pitch controls. The simulation results show their performances, in terms of rotor hub vibration reductions are comparable.
AB - Researchers have been exploring the potential for fluidic pitch links to replace traditional rigid pitch links for rotorcraft vibration reduction. Previous studies showed that the hub vibratory loads of a medium-sized helicopter with an articulated rotor system in high speed flight condition could be affected by tailoring the fluidic pitch link impedance. The current research is intended to advance and expand studies of the fluidic pitch link concept. A free wake model is implemented in rotor aeroelastic modeling. The fluidic pitch links have been examined at low forward speed for the vehicle, the results show that they can achieve average 39% vibration reduction at advance ratio 0.15. Fluidic pitch links are also be evaluated on a light helicopter with a hingeless rotor system. Parametric studies of fluidic pitch link properties are conducted, and their effect on rotor hub vibratory loads is evaluated at both low and high forward speeds for its off-design performance. The results indicate that fluidic pitch links work very well at advance ratio of 0.30, and can reduce hub loads by average 45%. The fluidic pitch links are also compared with the active individual blade pitch controls. The simulation results show their performances, in terms of rotor hub vibration reductions are comparable.
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M3 - Conference contribution
AN - SCOPUS:84939527318
T3 - 40th European Rotorcraft Forum 2014
SP - 249
EP - 259
BT - 40th European Rotorcraft Forum 2014
PB - Royal Aeronautical Society
T2 - 40th European Rotorcraft Forum, ERF 2014
Y2 - 2 September 2014 through 5 September 2014
ER -