TY - GEN
T1 - Individual Blade Pitch Control (IBC) for Vibration Reduction of Lift-Offset Coaxial Rotor Vehicles with Auxiliary Propulsion
AU - Beyer, Jessica
AU - Smith, Edward
AU - Schmitz, Sven
AU - Zhang, Jianhua
N1 - Funding Information:
This research is funded by the Government under Cooperative Agreement No. W911W6-21-2-0002. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation thereon. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies or position, either expressed or implied, of the U.S. Army Combat Capabilities Development Command (DEVCOM), Aviation & Missile Center (AvMC), or the U.S. Government.
Funding Information:
The authors would like to thank Dr. George Jacobellis, Dr. Louis Centolanza, Dr. Hyeonsoo Yeo, and Dr. Mark Fulton from the U.S. Army Combat Capabilities Development Command for their technical guidance and discussions in addition to the other members of the VLRCOE review team, including Mr. William A. Welsh from Sikorsky Aircraft, A Lockheed Martin Company. The authors also wish to extend gratitude to ART for their assistance with RCAS. This research is funded by the Government under Cooperative Agreement No. W911W6-21-2-0002. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation thereon. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies or position, either expressed or implied, of the U.S. Army Combat Capabilities Development Command (DEVCOM), Aviation & Missile Center (AvMC), or the U.S. Government. The views expressed in this publication are those of the author and do not reflect the official policy or position of the United States Air Force, Department of Defense, or the U.S. Government.
Publisher Copyright:
Copyright © 2023 by the Vertical Flight Society. All rights reserved.
PY - 2023
Y1 - 2023
N2 - The present study investigates the vibration reduction potential of single harmonic individual blade pitch control (IBC) applied to a lift-offset coaxial main rotor. An open-loop phase sweep is conducted using comprehensive aeroelastic simulations of the XH-59A rotor to quantify the effects of IBC on the hub vibration index and the rotor effective lift-to-drag ratio. Applying 4/rev, 1° amplitude IBC at 0° phase to both rotors decreased the hub vibration index by 64% at 200 knots and only decreased the rotor lift-to-drag ratio by 2%. Single harmonic IBC retained effective hub vibration index reduction with varying flight speed, including a 56% decrease at 160 knots and a 69% decrease at 240 knots. Higher amplitude IBC inputs were more effective at higher forward flight speeds. The vibration reduction of single harmonic IBC with 2° pitch amplitude increased from 24% to 69% when the forward flight speed increased from 160 to 240 knots. Application of a closed-loop control algorithm using multiple-harmonic IBC achieved an 84% decrease in the hub vibration index with only a 2% decrease in the rotor effective lift-to-drag ratio.
AB - The present study investigates the vibration reduction potential of single harmonic individual blade pitch control (IBC) applied to a lift-offset coaxial main rotor. An open-loop phase sweep is conducted using comprehensive aeroelastic simulations of the XH-59A rotor to quantify the effects of IBC on the hub vibration index and the rotor effective lift-to-drag ratio. Applying 4/rev, 1° amplitude IBC at 0° phase to both rotors decreased the hub vibration index by 64% at 200 knots and only decreased the rotor lift-to-drag ratio by 2%. Single harmonic IBC retained effective hub vibration index reduction with varying flight speed, including a 56% decrease at 160 knots and a 69% decrease at 240 knots. Higher amplitude IBC inputs were more effective at higher forward flight speeds. The vibration reduction of single harmonic IBC with 2° pitch amplitude increased from 24% to 69% when the forward flight speed increased from 160 to 240 knots. Application of a closed-loop control algorithm using multiple-harmonic IBC achieved an 84% decrease in the hub vibration index with only a 2% decrease in the rotor effective lift-to-drag ratio.
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M3 - Conference contribution
AN - SCOPUS:85167672429
T3 - FORUM 2023 - Vertical Flight Society 79th Annual Forum and Technology Display
BT - FORUM 2023 - Vertical Flight Society 79th Annual Forum and Technology Display
PB - Vertical Flight Society
T2 - 79th Vertical Flight Society Annual Forum and Technology Display, FORUM 2023
Y2 - 16 May 2023 through 18 May 2023
ER -