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首页> 外文期刊>International journal of aerospace engineering >Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors
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Vibration and Performance Analyses Using Individual Blade Pitch Controls for Lift-Offset Rotors

机译：使用单独的桨距控制来控制偏心转子的振动和性能

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摘要

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 degrees and control phase angle of 270 degrees (3P/1 degrees/270 degrees); however, the rotor effective lift-to-drag ratio decreases by 3.43%. When the 2/rev actuation frequency with the amplitude of 2 degrees and control phase angle of 270 degrees (2P/2 degrees/270 degrees) and the 3/rev actuation frequency using the magnitude of 1 degrees and control phase angle of 210 degrees (3P/1 degrees/210 degrees) 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.
机译：这项工作试图在高速向前飞行中使用IBC（单独的桨距控制）来减少升空偏置转子的轮毂振动负荷。作为本研究的升空偏置旋翼，考虑了XH-59A复合直升机的刚性同轴旋翼，并使用CAMRAD II来预测轮毂振动和旋翼性能。使用具有200节的单次谐波输入的IBC，当以1度的IBC幅值和270度的控制相角施加3 / rev激励频率时，XH-59A转子的振动指数可降低约62％。 （3P / 1度/ 270度）；但是，转子的有效升阻比降低了3.43％。当幅度为2度的2 / rev激励频率和270度（2P / 2度/ 270度）的控制相角以及幅度为1度和210度的控制相位角的3 / rev激励频率时（ 3P / 1度/ 210度）与具有多个谐波输入的IBC结合使用，在200的飞行速度下，振动指数降低了约62％，而转子的有效升/降比则提高了0.37％。结。这项研究表明，通过使用具有多个谐波输入的IBC，可以在高速飞行中显着降低升空偏置转子的轮毂振动，但转子性能却略有提高。

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  • 来源
    《International journal of aerospace engineering》 |2019年第2期|9589415.1-9589415.13|共13页
  • 作者

    Park Jae-Sang; Kim Do-Hyung; Chae Sanghyun; Lee Ye-Lin; Go Jeong-In;

  • 作者单位

    Chungnam Natl Univ, Dept Aerosp Engn, Daejeon 34134, South Korea;

    Korea Aerosp Res Inst, Aircraft Syst Div, Daejeon 34133, South Korea;

    Korea Aerosp Res Inst, Aircraft Syst Div, Daejeon 34133, South Korea;

    Chungnam Natl Univ, Dept Aerosp Engn, Daejeon 34134, South Korea;

    Agcy Def Dev, Aeronaut Technol Directorate, Daejeon 34060, South Korea;

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