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 - 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 -