Vibration reduction analyses using individual blade pitch controls for lift-offset rotors
Vibration reduction analyses using individual blade pitch controls for lift-offset rotors
dc.contributor.author | Park, J.S. | |
dc.contributor.author | Kim, D.H. | |
dc.contributor.author | Chae, S. | |
dc.contributor.author | Lee, Y.L. | |
dc.contributor.author | Go, J.I. | |
dc.date.accessioned | 2021-03-04T15:52:31Z | |
dc.date.available | 2021-03-04T15:52:31Z | |
dc.date.issued | 2018 | |
dc.description.abstract | This work attempts to reduce the hub vibratory loads of a lift-offset rotor using IBC (Individual Blade pitch Control) in high-speed forward flight. As a lift-offset rotor for the present study, the rigid coaxial rotor of XH-59A compound helicopter is considered, and CAMRAD II is used to predict the hub vibration and rotor performance. Using the IBC with a single harmonic input at 200 knots, the vibration index of the XH-59A rotor is minimized by about 62% when the 3/rev actuation frequency is applied with the IBC amplitude of 1� and control phase angle of 270� (3P/1�/270�); however, the rotor effective lift-to-drag ratio is reduced by 3.43%. When the 2/rev actuation frequency with the amplitude of 2� and control phase angle of 270� (2P/2�/270�) and the 3/rev actuation frequency using the magnitude of 1� and control phase angle of 210� (3P/1�/210�) are used in combination for the IBC with multiple harmonic inputs, the vibration index is reduced by about 62%, while the rotor effective lift-to-drag ratio increases by 0.37% at a flight speed of 200 knots. This study shows that the hub vibration of the lift-offset rotor in high-speed flight can be reduced significantly but the rotor performance increases slightly, using the IBC with multiple harmonic inputs. | |
dc.identifier.other | 41 - Vibration Reduction Analyses using Individual Blade Pitch Controls for Lift-offset Rotors.pdf | |
dc.identifier.uri | http://hdl.handle.net/20.500.11881/3953 | |
dc.language.iso | en | |
dc.title | Vibration reduction analyses using individual blade pitch controls for lift-offset rotors |
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