Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors
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 a XH-59A compound helicopter is considered and CAMRAD II is used to predict th...
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| Format: | Article |
| Language: | English |
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Wiley
2019-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2019/9589415 |
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| _version_ | 1832554140665905152 |
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| author | Jae-Sang Park Do-Hyung Kim Sanghyun Chae Ye-Lin Lee Jeong-In Go |
| author_facet | Jae-Sang Park Do-Hyung Kim Sanghyun Chae Ye-Lin Lee Jeong-In Go |
| author_sort | Jae-Sang Park |
| collection | DOAJ |
| description | 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 a 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 decreases 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. |
| format | Article |
| id | doaj-art-30eb870cb5664e8f9ec0915c8d473e66 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2019-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-30eb870cb5664e8f9ec0915c8d473e662025-02-03T05:52:12ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742019-01-01201910.1155/2019/95894159589415Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset RotorsJae-Sang Park0Do-Hyung Kim1Sanghyun Chae2Ye-Lin Lee3Jeong-In Go4Department of Aerospace Engineering, Chungnam National University, Daejeon 34134, Republic of KoreaAircraft System Division, Korea Aerospace Research Institute, Daejeon 34133, Republic of KoreaAircraft System Division, Korea Aerospace Research Institute, Daejeon 34133, Republic of KoreaDepartment of Aerospace Engineering, Chungnam National University, Daejeon 34134, Republic of KoreaAeronautical Technology Directorate, Agency for Defense Development, Daejeon 34060, Republic of KoreaThis 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 a 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 decreases 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.http://dx.doi.org/10.1155/2019/9589415 |
| spellingShingle | Jae-Sang Park Do-Hyung Kim Sanghyun Chae Ye-Lin Lee Jeong-In Go Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors International Journal of Aerospace Engineering |
| title | Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors |
| title_full | Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors |
| title_fullStr | Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors |
| title_full_unstemmed | Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors |
| title_short | Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors |
| title_sort | vibration and performance analyses using individual blade pitch controls for lift offset rotors |
| url | http://dx.doi.org/10.1155/2019/9589415 |
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