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71. 发明授权

US07757991B2 Helicopter blade vortex interaction noise reducing method and device 失效
标题翻译：直升机叶片涡流相互作用减噪方法及装置
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。

72. 发明申请

US20100155529A1 Landing gear with noise reduction fairing 有权
标题翻译：起落架减噪整流罩
公开(公告)号：US20100155529A1
公开(公告)日：2010-06-24
申请号：US12458407
申请日：2009-07-10
申请人： Leung Choi Chow , Philip Campbell , Christopher Wood , Andrew John Dyer
发明人： Leung Choi Chow , Philip Campbell , Christopher Wood , Andrew John Dyer
IPC分类号： B64C23/00 , B64C1/40 , B64C25/10
CPC分类号： B64C25/001 , B64C7/00 , B64C2025/003
摘要： An aircraft noise reduction apparatus is provided which includes an aircraft landing gear assembly and a noise reduction fairing 12. The landing gear assembly comprises a landing gear 10 arranged to be moveable between a stowed position and a fully deployed position. The noise reduction fairing 12 may comprise a wrap-around fairing which, when the landing gear 10 is in its fully deployed position, wraps around the landing gear 10 and extends along the majority of the length of a landing gear leg 11. A landing gear bay door assembly 16, 17 comprising at least one door may also be provided. The fairing 12 may have a recess 24 for accommodating one of landing gear bay doors when the door 16 is in its fully open position.
摘要翻译：提供了一种包括飞机起落架组件和降噪整流罩12的飞机降噪装置。起落架组件包括起落架10，起落架10布置成可在收起位置和完全展开位置之间移动。减噪整流罩12可以包括一个环绕整流罩，当起落架10处于其完全展开位置时，环绕整流罩围绕起落架10卷绕并沿起落架脚11的大部分长度延伸。起落架还可以设置包括至少一个门的舱门组件16,17。当门16处于其完全打开位置时，整流罩12可以具有用于容纳一个起落架舱门的凹部24。

73. 发明申请

US20100078863A1 ATMOSPHERIC TURBULENCE ISOLATION SYSTEM AND METHOD 有权
标题翻译：大气湍流分离系统及方法
公开(公告)号：US20100078863A1
公开(公告)日：2010-04-01
申请号：US12240754
申请日：2008-09-29
申请人： Alan Z. Ullman , Steven F. Griffin
发明人： Alan Z. Ullman , Steven F. Griffin
IPC分类号： F16M1/08 , B64C23/00 , F16F1/00
CPC分类号： B64D47/08 , B64C1/40 , F16F9/306
摘要： A vibration isolation assembly for an aerodynamic object comprises a viscoelastic inner layer disposed on the aerodynamic object and being configured to attenuate vibration. The vibration isolation assembly further comprises a rigid or stiff outer layer disposed on an inner layer. The vibration isolation assembly may attenuate the transmission of aerodynamically-induced vibration to components contained or mounted to the aerodynamic object.
摘要翻译：用于空气动力学对象的隔振组件包括设置在空气动力学对象上并被配置为衰减振动的粘弹性内层。隔振组件还包括设置在内层上的刚性或刚性外层。振动隔离组件可以将空气动力学振动的传播衰减到包含或安装到空气动力学对象的部件。

74. 发明申请

US20100044505A9 HELICOPTER BLADE VORTEX INTERACTION NOISE REDUCING METHOD AND DEVICE 失效
标题翻译：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。

75. 发明授权

US07641153B2 Directed energy off-body heating for supersonic vehicle shockwave and sonic boom control 有权
标题翻译：用于超音速车辆冲击波和声波控制的定向能量离体加热
公开(公告)号：US07641153B2
公开(公告)日：2010-01-05
申请号：US11284337
申请日：2005-11-21
申请人： Philip Smereczniak
发明人： Philip Smereczniak
IPC分类号： B64C23/00
CPC分类号： B64C30/00 , B64C2220/00
摘要： Methods and apparatus for suppressing noise. The present invention provides a method that includes directing a laser at a first volume of gas and directing microwave radiation to a second volume. The method includes selecting the location of the second volume so that it is overrun by a shockwave system of a supersonic vehicle. Preferably, the directing of the radiation is from a vehicle that flies at high altitude and is of practical length (e.g., 100-400 feet or more). The radiation may be pulsed and steered. The present invention also provides a system including a laser and microwave antenna for controlling the noise of a supersonic vehicle. The laser is directed at a first volume while the antenna is pointed at a second volume that envelops the first volume. The location of the second volume is such that it will be overrun by the shockwave system of the vehicle.
摘要翻译：抑制噪音的方法和装置本发明提供了一种方法，其包括将激光器引导到第一体积的气体并将微波辐射引导到第二体积。该方法包括选择第二体积的位置，使其由超音速车辆的冲击波系统超速。优选地，辐射的引导来自在高空飞行且具有实际长度（例如，100-400英尺或更大））的车辆。辐射可以是脉冲和转向的。本发明还提供了一种包括用于控制超音速车辆的噪声的激光和微波天线的系统。当天线指向包围第一体积的第二体积时，激光被定向在第一体积上。第二卷的位置使得它将被车辆的冲击波系统超载。

76. 发明申请

US20090321559A1 Aircraft noise reduction apparatus 有权
标题翻译：飞机降噪装置
公开(公告)号：US20090321559A1
公开(公告)日：2009-12-31
申请号：US12153493
申请日：2008-05-20
申请人： Leung Choi Chow , Christopher Neil Wood , Philip Campbell
发明人： Leung Choi Chow , Christopher Neil Wood , Philip Campbell
IPC分类号： B64C23/00 , B64C1/40 , B64C25/04
CPC分类号： B64C25/001 , B64C7/00 , B64C2025/003
摘要： The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear.
摘要翻译：本发明涉及飞机降噪装置，特别地但不排他地涉及飞机起落架上的降噪装置。飞机降噪装置包括用于飞行器的起落架的降噪附件。降噪装置可在第一位置和第二位置之间移动，第一位置使空气偏离起落架的噪声感应部件，而第二位置允许进入噪声感应部件。第一和第二位置之间的降噪附件的运动由起落架的一部分致动。

77. 发明申请

US20090078821A1 LANDING GEAR 有权
标题翻译：起落架
公开(公告)号：US20090078821A1
公开(公告)日：2009-03-26
申请号：US12255039
申请日：2008-10-21
申请人： Leung Choi Chow , Christopher Neil Wood , Philip Campbell
发明人： Leung Choi Chow , Christopher Neil Wood , Philip Campbell
IPC分类号： B64C23/00 , B64C25/10
CPC分类号： B64C7/00 , B64C25/16 , B64C2025/003
摘要： An aircraft noise-reduction apparatus (10) for a landing gear (20) comprises a skeleton structure (14), which supports and acts to maintain the profile of a noise-reducing layer. The skeleton structure may comprise blades (16). The noise-reducing layer may have more than 10 apertures through which, in use, air can pass and may be in the form of a deformable mesh (12).
摘要翻译：用于起落架（20）的飞行器降噪装置（10）包括骨架结构（14），其支撑并用于保持降噪层的轮廓。骨架结构可以包括叶片（16）。减噪层可以具有多于10个孔，在使用中，空气可以通过，并且可以是可变形网（12）的形式。

78. 发明申请

US20090045289A1 Flow-driven oscillating acoustic attenuator 有权
标题翻译：流动振荡声衰减器
公开(公告)号：US20090045289A1
公开(公告)日：2009-02-19
申请号：US12008134
申请日：2008-01-09
申请人： Alan J. Bilanin , Todd J. Quackenbush , Pavel V. Danilov
发明人： Alan J. Bilanin , Todd J. Quackenbush , Pavel V. Danilov
IPC分类号： B64C23/00
CPC分类号： B64C23/005 , B64C2230/08 , B64C2230/24 , F15D1/10 , Y02T50/166
摘要： An apparatus for attenuating acoustic resonance generated by flow over a cavity in a surface comprises a plurality of flat flaps proximate to an upstream edge of the cavity. The flaps are disposed in an array spaced in a width direction of the cavity edge, and are oscillated by the flow in two degrees of freedom solely by the flow, independent of an actuation mechanism. Each flap includes a first hinge generally coextensive with the surface for enabling oscillation in a first degree of freedom and a second hinge orthogonal to the first hinge and forming a tab for enabling oscillation in a second degree of freedom. The hinges are constructed with torsional spring constants that provide predetermined oscillation frequencies and magnitudes. The apparatus can include a deployment mechanism for moving each flap between a stowed position wherein it is generally flush with the surface and a deployed position wherein the flap can be oscillated by the flow.
摘要翻译：用于衰减由表面上的腔体上的流动产生的声共振的装置包括靠近空腔的上游边缘的多个平板。翼片被设置成在空腔边缘的宽度方向上间隔开的阵列中，并且仅通过流动而以两个自由度的流动振荡，而与致动机构无关。每个翼片包括通常与表面共同延伸的第一铰链，用于使得能够在第一自由度中摆动，而第二铰链与第一铰链正交并形成用于使第二自由度摆动的翼片。铰链由扭转弹簧常数构成，提供预定的振荡频率和幅度。该装置可以包括一个展开机构，用于在收集位置之间移动每个折板，其中它与表面大致齐平，并且展开位置，其中翼片可以被流动摆动。

79. 发明申请

US20080296438A1 Control surface actuation system 失效
标题翻译：控制面驱动系统
公开(公告)号：US20080296438A1
公开(公告)日：2008-12-04
申请号：US12153859
申请日：2008-05-27
申请人： Frank Wong , Camille Alain Rabbath , Nicholas Lechevin
发明人： Frank Wong , Camille Alain Rabbath , Nicholas Lechevin
IPC分类号： B64C23/00
CPC分类号： B64C23/005 , F42B10/64
摘要： Systems for controlling flow effector control surfaces. The system comprises a flow effector control coupled to an elongated bar at one end of the bar. The elongated bar is coupled at the other end to the middle of a T-shaped member. A compliant link is coupled to the bar between the control surface and the T-shaped member. At each end of the T-shaped member is coupled a shape memory alloy wire which acts as an actuating means. When one of the shape memory alloy wire contracts, the elongated bar pivots about the compliant link and activates or retracts the flow effector control surface.
摘要翻译：用于控制流量效应器控制面的系统。该系统包括耦合到杆的一端处的细长杆的流动执行器控制。细长的杆在另一端连接到T形构件的中间。柔性连接件连接到控制表面和T形构件之间的杆上。在T形构件的每个端部连接有用作致动装置的形状记忆合金线。当形状记忆合金线中的一个收缩时，细长杆围绕柔性链条枢转并且启动或缩回流动效应器控制表面。

80. 发明申请

US20080237395A1 BVI NOISE REDUCTION METHOD AND APPARATUS FOR HELICOPTER 失效
标题翻译： 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。

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