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    HELICOPTER BLADE VORTEX INTERACTION NOISE REDUCING METHOD AND DEVICE
    2.
    发明申请
    HELICOPTER BLADE VORTEX INTERACTION NOISE REDUCING METHOD AND DEVICE 失效
    直升机叶片VORTEX交互噪声减少方法和装置

    公开(公告)号：US20100044505A9

    公开(公告)日：2010-02-25

    申请号：US10570082

    申请日：2006-02-28

    申请人： Yasutada Tanabe ,  Takeshi Akasaka ,  Shigeru Saito ,  Noboru Kobiki

    发明人： Yasutada Tanabe ,  Takeshi Akasaka ,  Shigeru Saito ,  Noboru Kobiki

    IPC分类号： B64C27/473 ,  B64C23/00 ,  B64C11/20

    CPC分类号： B64C27/001 ,  B64C27/473 ,  B64C27/615 ,  B64C2027/7266 ,  B64C2027/7277 ,  Y02T50/34

    摘要： The present method is characterized by providing the rotor blade with a tab 3, which can advance and retreat with respect to rear of rotating direction of the rotor blade between a position where the tab protrudes from a trailing edge of the rotor blade and a position where the tab does not, and providing an actuator 4, which advances and retreats the tab 3, and operating the actuator 4 so that the tab advances and retreats in response to rotating timing of the rotor blade 2, when reducing the BVI noise of the rotor blade of a helicopter. Thus, the BVI noise of a helicopter can be reduced effectively.

    摘要翻译： 本方法的特征在于为转子叶片提供了一个突片3，其可以在转子叶片的旋转方向的后方在从转子叶片的后缘突出的位置和转子叶片的后缘之间的位置前进和后退， 并且提供致动器4，该致动器4使突片3前进和后退，并且当减小转子的BVI噪声时，响应于转子叶片2的旋转定时，操作致动器4使得突片前进和后退 直升机的刀片 因此，可以有效降低直升机的BVI噪声。

    BVI NOISE REDUCTION METHOD AND APPARATUS FOR HELICOPTER
    3.
    发明申请
    BVI NOISE REDUCTION METHOD AND APPARATUS FOR HELICOPTER 失效
    BVI噪声减少方法和直升机装置

    公开(公告)号：US20080237395A1

    公开(公告)日：2008-10-02

    申请号：US10570082

    申请日：2006-02-28

    申请人： Yasutada Tanabe ,  Takeshi Akasaka ,  Shigeru Saito ,  Noboru Kobiki

    发明人： Yasutada Tanabe ,  Takeshi Akasaka ,  Shigeru Saito ,  Noboru Kobiki

    IPC分类号： B64C27/473 ,  B64C23/00 ,  B64C11/20

    CPC分类号： B64C27/001 ,  B64C27/473 ,  B64C27/615 ,  B64C2027/7266 ,  B64C2027/7277 ,  Y02T50/34

    摘要： The present method is characterized by providing the rotor blade with a tab 3, which can advance and retreat with respect to rear of rotating direction of the rotor blade between a position where the tab protrudes from a trailing edge of the rotor blade and a position where the tab does not, and providing an actuator 4, which advances and retreats the tab 3, and operating the actuator 4 so that the tab advances and retreats in response to rotating timing of the rotor blade 2, when reducing the BVI noise of the rotor blade of a helicopter. Thus, the BVI noise of a helicopter can be reduced effectively.

    摘要翻译： 本方法的特征在于为转子叶片提供了一个突片3，其可以在转子叶片的旋转方向的后方在从转子叶片的后缘突出的位置和转子叶片的后缘之间的位置前进和后退， 并且提供致动器4，该致动器4使突片3前进和后退，并且当减小转子的BVI噪声时，响应于转子叶片2的旋转定时，操作致动器4使得突片前进和后退 直升机的刀片 因此，可以有效降低直升机的BVI噪声。

    Helicopter rotor equipped with flaps
    4.
    发明授权
    Helicopter rotor equipped with flaps 失效
    直升机转子配备襟翼

    公开(公告)号：US5639215A

    公开(公告)日：1997-06-17

    申请号：US607103

    申请日：1996-02-26

    申请人： Eiichi Yamakawa ,  Noboru Kobiki ,  Eiji Shima

    发明人： Eiichi Yamakawa ,  Noboru Kobiki ,  Eiji Shima

    IPC分类号： B64C27/46 ,  B64C27/467 ,  B64C27/615

    CPC分类号： B64C27/615 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A blade of the rotor is attached to a main rotor shaft, and is rotated counterclockwise at a high speed when viewed from above. In the vicinity of the blade tip, a flap having a wing shape in section is pivotally supported with a hinge so as to be angularly displaceable and at the end a part of the rear end of the blade is cut out. A hinge line which indicates the center of the angular displacement of the hinge is formed so as to be parallel to a straight line passing through the rotation center of the rotor and the center of gravity of the flap. A helicopter rotor equipped with flaps is provided in which the influence of the centrifugal force acting on the center of gravity of a blade can be largely reduced, and a flap control mechanism can be reduced in size and weight.

    摘要翻译： 转子叶片安装在主转子轴上，从上方观察时以高速逆时针旋转。 在叶片尖端附近，具有翼形截面的翼片以铰链枢转地支撑以便可角度地移位，并且在末端切割叶片后端的一部分。 指示铰链的角位移的中心的铰链线形成为平行于通过转子的旋转中心的直线和皮瓣的重心。 提供了配备有襟翼的直升机转子，其中可以大大减小作用在叶片重心上的离心力的影响，并且能够减小翼片控制机构的尺寸和重量。

    Higher harmonic control apparatus for a helicopter rotor
    5.
    发明授权
    Higher harmonic control apparatus for a helicopter rotor 失效
    用于直升机转子的高次谐波控制装置

    公开(公告)号：US5655878A

    公开(公告)日：1997-08-12

    申请号：US604343

    申请日：1996-02-21

    申请人： Eiichi Yamakawa ,  Atsushi Murashige ,  Noboru Kobiki

    发明人： Eiichi Yamakawa ,  Atsushi Murashige ,  Noboru Kobiki

    IPC分类号： B64C27/51 ,  B64C27/58 ,  B64C27/64 ,  B64C27/72 ,  B64C11/40

    CPC分类号： B64C27/72 ,  Y02T50/34 ,  Y10S416/50

    摘要： A control system has an HHC actuator having a basal portion and a movable portion. A load acting on the control system is detected by a semiconductor gauge. The load detected by the semiconductor gauge is compared with a threshold value in a computer. If the detected load is larger than the threshold load, the movable portion is fixed to the basal portion by a fixing mechanism. By detecting the sign of stall of blades, the HHC actuator is fixed in a neutral position, allowing safe flight. A fixing switch is provided for allowing the fixing mechanism to operate regardless of the result of the comparison with the computer.

    摘要翻译： 控制系统具有具有基部和可动部的HHC致动器。 通过半导体测量仪检测作用在控制系统上的负载。 将半导体量规检测到的负载与计算机中的阈值进行比较。 如果检测到的负载大于阈值负载，则可动部通过固定机构固定在基部上。 通过检测叶片失速的符号，HHC执行器被固定在中立位置，允许安全飞行。 提供了一种用于允许固定机构操作的固定开关，而不管与计算机的比较结果如何。