公开(公告)号：US07980510B2

公开(公告)日：2011-07-19

申请号：US10569653

申请日：2004-05-12

申请人： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

发明人： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

IPC分类号： B64C11/46 ,  B64D27/00 ,  B64D33/00

CPC分类号： A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

摘要： A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

摘要翻译： 一架小型无人机包括 主翼具有下表面近似平坦的弧形翼型，其锥形形状变窄到其前端具有遮光角度的叶片尖端，其具有无风翼型的空气动力学表面的飞翼型，并且是低方位 比; 在主翼的左右两侧的后缘部分中大致极宽的可动翼片至少在水平飞行中具有二面角; 放置在主翼左右叶片尖端的垂直稳定器; 并安装在主翼顶面的两个螺旋桨。 这可以实现小型化和轻量化的小型无人驾驶飞机的个人承载能力和适合性，例如用手抛出。

公开(公告)号：US06384594B1

公开(公告)日：2002-05-07

申请号：US09626083

申请日：2000-07-26

申请人： Yasuo Uehara ,  Yasutada Tanabe ,  Toshiaki Suzuki

发明人： Yasuo Uehara ,  Yasutada Tanabe ,  Toshiaki Suzuki

IPC分类号： G01P348

CPC分类号： G01P3/46 ,  G01P3/44 ,  G01P3/488 ,  G01P3/49

摘要： Through differentiation of input signal Vw from a sensor the angular frequency &ohgr; becomes included in the amplitude component. Through a plurality of differential operations the amplitude including the angular frequency &ohgr; varies, but the time-dependent term becomes equal. Since the amplitude of the signal Vw outputted from the revolution speed sensor 10 is approximately constant, the angular frequency &ohgr; proportional to the revolution speed can be extracted by determining a ratio thereof.

摘要翻译： 通过输入信号Vw与传感器的区分，角频率ω被包括在振幅分量中。 通过多个差分运算，包括角频率ω的振幅变化，但时间依赖项变为相等。 由于从转速传感器10输出的信号Vw的幅度近似恒定，因此可以通过确定其比例来提取与转速成比例的角频率ω。

公开(公告)号：US20070063096A1

公开(公告)日：2007-03-22

申请号：US10569653

申请日：2004-05-12

申请人： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

发明人： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

IPC分类号： B64C39/02

CPC分类号： A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

摘要： A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

摘要翻译： 一架小型无人机包括 主翼具有下表面近似平坦的弧形翼型，其锥形形状变窄为其前端具有遮光角度的叶片尖端，具有无风翼型的空气动力学表面的飞翼型，低侧面 比; 在主翼的左右两侧的后缘部分中大致极宽的可动翼片至少在水平飞行中具有二面角; 放置在主翼左右叶片尖端的垂直稳定器; 并安装在主翼顶面的两个螺旋桨。 这可以实现小型化和轻量化的小型无人驾驶飞机的个人承载能力和适合性，例如用手抛出。

公开(公告)号：US07757991B2

公开(公告)日：2010-07-20

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： B64C3/50 ,  B64C3/54 ,  B64C23/00

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

摘要： In a blade vortex interaction (BVI) noise reduction system for a helicopter a rotor blade, a tab is movable via an actuator from a first position, wherein the tab is within the blade, to a second position, wherein the tab extends outwardly from a trailing edge of the rotor blade. The actuator is operated so that the tab advances and retreats in response to rotating timing of the rotor blade, to reduce the BVI noise of the rotor blade.

摘要翻译： 在用于直升机的转子叶片的叶片涡流相互作用（BVI）降噪系统中，翼片可经由致动器从第一位置移动，其中翼片在叶片内，到第二位置，其中翼片从 转子叶片的后缘。 致动器被操作，使得突片响应于转子叶片的旋转定时而前进和后退，以减小转子叶片的BVI噪声。

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。

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。