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1. 发明申请

US20060049302A1 Apparatus and methods for structurally-integrated conductive conduits for rotor blades 审中-公开
标题翻译：用于转子叶片的结构集成导电管道的装置和方法
公开(公告)号：US20060049302A1
公开(公告)日：2006-03-09
申请号：US10930478
申请日：2004-08-31
申请人： Dennis Kennedy , Friedrich Straub , Robert Murrill
发明人： Dennis Kennedy , Friedrich Straub , Robert Murrill
IPC分类号： B64C27/00
CPC分类号： B64C27/473 , B64C27/615 , B64C27/72 , B64C2027/7216 , B64C2027/725 , B64C2027/7266 , B64C2027/7272 , B64C2027/7277 , B64C2027/7283 , B64C2027/7288 , Y02T50/34
摘要： Structurally-integrated conductive conduits for rotor blades are disclosed. In one embodiment, an elongated rotor blade includes a body having a root portion and a distal portion spaced apart from the root portion, a device coupled to the body, and a conduit assembly disposed within the body and extending between the root portion and the device. The conduit assembly includes a main body assembly having at least one of a conductive lead, a fluid line, and an optical fiber disposed within a matrix material, the conduit assembly extending from the root portion to the device. In alternate embodiments, the device may comprise an actuator, a smart actuator, a piezoelectric material, an electromagnetic device, an electromechanical device, a hydraulic actuator, a pneumatic actuator, a light, and a sensor.
摘要翻译：公开了用于转子叶片的结构集成导电导管。在一个实施例中，细长的转子叶片包括具有根部部分和与根部部分间隔开的远侧部分的主体，联接到主体的装置和设置在主体内并在根部和装置之间延伸的导管组件。导管组件包括主体组件，其具有导电引线，流体管线和布置在基体材料内的光纤中的至少一个，导管组件从根部部分延伸到器件。在替代实施例中，该装置可以包括致动器，智能致动器，压电材料，电磁装置，机电装置，液压致动器，气动致动器，光和传感器。

2. 发明授权

US09120567B2 High speed compound rotary wing aircraft 有权
标题翻译：高速复合旋翼飞机
公开(公告)号：US09120567B2
公开(公告)日：2015-09-01
申请号：US13493559
申请日：2012-06-11
申请人： Mark W. Scott , Stephen M. Gatto
发明人： Mark W. Scott , Stephen M. Gatto
IPC分类号： B64C27/57 , B64C27/72 , B64C27/82 , B64C21/04 , B64C21/08
CPC分类号： B64C27/72 , B64C21/04 , B64C21/08 , B64C27/82 , B64C2027/7227 , B64C2027/725 , B64C2027/7266 , B64C2027/8236 , B64C2230/06 , B64C2230/14 , B64C2230/20 , B64C2230/28 , Y02T50/166 , Y02T50/34
摘要： A rotary wing aircraft includes an airfame and an extending tail extending from the airframe. A main rotor assembly is operably connected to the airframe and includes a plurality of rotor blades operably connected to a rotor shaft, and one or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A tail rotor is operably connected to the extending tail. The tail rotor is rotatable about a tail rotor axis and the tail rotor axis movable from laterally-extending to rearward-extending.
摘要翻译：旋转翼飞机包括从机身延伸的气翼和延伸尾翼。主转子组件可操作地连接到机身并且包括可操作地连接到转子轴的多个转子叶片，以及位于多个转子叶片的一个或多个转子叶片处的一个或多个主动适应装置。一个或多个主动自适应装置可操作地连接到飞行器飞行控制系统，使得当被激活时，一个或多个主动自适应装置改变转子组件的一个或多个操作特性。尾部转子可操作地连接到延伸尾部。尾部转子可围绕尾部转子轴线旋转，并且尾部转子轴线可从横向延伸到向后延伸。

3. 发明授权

US06234751B1 Oscillating air jets for reducing HSI noise 有权
标题翻译：振荡式喷气式飞机降低HSI噪音
公开(公告)号：US06234751B1
公开(公告)日：2001-05-22
申请号：US09198843
申请日：1998-11-24
申请人： Ahmed A. Hassan , Hormoz Tadghighi , Ram D. Janakiram
发明人： Ahmed A. Hassan , Hormoz Tadghighi , Ram D. Janakiram
IPC分类号： B64C2704
CPC分类号： B64C23/04 , B64C27/001 , B64C27/467 , B64C27/51 , B64C2027/725 , B64C2230/02 , B64C2230/06 , B64C2230/14 , B64C2230/18 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y02T50/34 , Y10S416/50
摘要： Porous surfaces on an aerodynamic structure driven with positive and negative pressures are used in an active control system for attenuating shock waves responsible for high-speed impulsive (HSI) noise. The control system includes an array of apertures in the outer skin of the structure providing fluid communication between the exterior flow stream and an interior volume of the structure. A movable diaphragm within the structure pushes air out of and pulls air in through the apertures under the action of a drive mechanism within the structure, thus creating oscillating air jets. The drive mechanism may be actuated by a controller based on information supplied by a sensor in the leading edge of the aerodynamic structure. The array of apertures may be spaced apart along the outer skin of the aerodynamic structure so as to span a distance of about 15% of the chord length. The oscillating airjets may be provided on multiple surfaces of the aerodynamic structure, including the upper and lower surfaces.
摘要翻译：用于正压和负压驱动的空气动力学结构上的多孔表面用于主动控制系统，用于衰减负责高速脉冲（HSI）噪声的冲击波。控制系统包括在结构的外皮中的孔阵列，从而提供外部流动流和结构的内部体积之间的流体连通。该结构内的可移动隔膜在结构内的驱动机构的作用下将空气推出并通过孔拉入空气，从而产生振荡空气射流。驱动机构可以由控制器基于由空气动力结构的前缘中的传感器提供的信息来致动。孔阵列可以沿着空气动力学结构的外表面间隔开，以便跨过弦长的约15％的距离。可以在空气动力学结构的多个表面上设置振荡空气喷射器，包括上表面和下表面。

4. 发明授权

US06821090B1 Gust alleviation/flutter suppression device 有权
标题翻译：阵风减轻/扑灭抑制装置
公开(公告)号：US06821090B1
公开(公告)日：2004-11-23
申请号：US09226418
申请日：1999-01-06
申请人： Ahmed A. Hassan , Brian K. Hamilton , Hieu T. Ngo
发明人： Ahmed A. Hassan , Brian K. Hamilton , Hieu T. Ngo
IPC分类号： B64C2704
CPC分类号： B64C27/51 , B64C23/04 , B64C27/001 , B64C27/467 , B64C2027/725 , B64C2230/02 , B64C2230/06 , B64C2230/14 , B64C2230/18 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y02T50/34 , Y10S416/50
摘要： An active control device is disclosed comprising an array of actively controlled oscillating air jets disposed on an aircraft structure. In a preferred embodiment, the device senses parameters associated with incipient unsteady aerodynamic excitation, such as free stream gusts, shed wakes in rotor and turbomachinery flows, or oscillatory motion of trailing edge control surfaces such as ailerons. These parameters are provided as input signals to a processor. Based on the input signals, the processor generates output signals that are used to operate the air jet array in a manner counteractive to the unsteady forcing. The air jet array can be used on numerous aircraft structures, including rotor blades, wings, engine inlets, engine exhausts, blunt surfaces and nozzles.
摘要翻译：公开了一种主动控制装置，其包括设置在飞机结构上的主动控制的振荡空气射流阵列。在优选实施例中，该装置感测与初始不稳定空气动力学激励相关的参数，例如自由流阵风，转子和涡轮机械流中的脱落唤醒，或后缘控制表面（例如副翼）的振荡运动。这些参数作为输入信号提供给处理器。基于输入信号，处理器产生用于以与非稳态强制相反的方式操作空气喷射阵列的输出信号。空气喷射阵列可以用于许多飞行器结构，包括转子叶片，翼，发动机入口，发动机排气，钝表面和喷嘴。

5. 发明授权

US6142425A Apparatus and method for aerodynamic blowing control using smart materials 失效
标题翻译：使用智能材料进行气动吹风控制的装置和方法
公开(公告)号：US6142425A
公开(公告)日：2000-11-07
申请号：US131464
申请日：1998-08-10
申请人： Erian A. Armanios , D. Stefan Dancila
发明人： Erian A. Armanios , D. Stefan Dancila
IPC分类号： B64C9/38 , B64C23/00 , B64C27/615 , B64C21/04
CPC分类号： B64C9/38 , B64C23/00 , B64C27/615 , B64C2027/725 , B64C2230/04 , B64C2230/06 , B64C2230/16 , B64C2230/28 , Y02T50/166 , Y02T50/32 , Y02T50/34 , Y02T50/44
摘要： A method and apparatus for controlling the blowing of compressed air from an aerodynamic structure such as an aircraft wing or helicopter rotor blade and thus controlling the aerodynamic properties of the wing comprises a narrow slot (13) in the upper surface 915) of the structure near its trailing edge (14). Inside the wing (12) is a chamber (23) that is connected to the narrow slot (13) in the wing surface (15). The chamber (23) houses a compressed air conduit (16) for supplying and holding compressed air. A passageway (25) connects the conduit (16) to the slot (13) in the upper surface (25) of the wing (12). The lower wall (27) of the passage (25) has a slit (32) allowing a shutter (31) to move selectively into the passage (25) and obstruct the flow of compressed air through the passageway (25). The shutter (31) is attached to a smart material actuator comprising a piezoelectrical bender (29). When a control voltage is applied to the bender (29), the bender (29) will bend. The bending of the bender (29) causes the shutter (31) to move up into the passage (25) and obstruct the flow of compressed air. In this way, the flow of air out of the slot (13) in the wing surface (15) may be dynamically controlled by application of selective control voltages to the bender (29).
摘要翻译：用于控制来自诸如飞行器机翼或直升机转子叶片的空气动力学结构的压缩空气的吹送并因此控制机翼的空气动力特性的方法和装置包括在该结构的上表面915中的窄槽（13）其后缘（14）。在机翼（12）的内部是与机翼表面（15）中的窄槽（13）连接的室（23）。腔室（23）容纳用于供应和保持压缩空气的压缩空气管道（16）。通道（25）将导管（16）连接到机翼（12）的上表面（25）中的狭槽（13）。通道（25）的下壁（27）具有狭缝（32），允许挡板（31）选择性地移动到通道（25）中并阻止压缩空气流过通道（25）。快门（31）附接到包括压电弯曲机（29）的智能材料致动器。当控制电压施加到弯曲器（29）时，弯曲器（29）将弯曲。弯曲器（29）的弯曲使得挡板（31）向上移动到通道（25）中并阻碍压缩空气的流动。以这种方式，可以通过向弯曲机（29）施加选择性控制电压来动态地控制从机翼表面（15）中的狭槽（13）流出的空气流。

6. 发明授权

US6092990A Oscillating air jets for helicopter rotor aerodynamic control and BVI noise reduction 失效
标题翻译：用于直升机转子空气动力学控制和BVI降噪的振荡空气喷射
公开(公告)号：US6092990A
公开(公告)日：2000-07-25
申请号：US869725
申请日：1997-06-05
申请人： Ahmed A. Hassan , Friedrich K. Straub , David B. Domzalski
发明人： Ahmed A. Hassan , Friedrich K. Straub , David B. Domzalski
IPC分类号： B64C23/04 , B64C27/467 , B64C27/51 , B64C27/04
CPC分类号： B64C27/467 , B64C23/04 , B64C27/51 , B64C2027/725 , B64C2230/02 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/18 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y02T50/34 , Y10S416/50
摘要： An active control system for reducing blade-vortex-interaction (BVI) noise generated by a rotor blade. The active control system includes a pressure sensor assembly, a device for changing a lift generated by the rotor blade, and a controller for activating the device upon a detected change in air pressure by the sensor assembly. The sensor assembly is disposed in close proximity to the rotor blade, and is adapted to detect a change in air pressure on a surface of the rotor blade near a leading edge of the rotor blade. The device is adapted to be activated by the controller, to thereby change a lift of the rotor blade. The controller activates the device to change a lift of the rotor blade in order to introduce a compensating pressure onto the surface of the rotor blade. This compensating pressure attenuates the magnitude of the change of air pressure. The device for changing a lift generated by the rotor blade can include at least one aperture on the rotor blade and a diaphragm in the interior of the rotor blade. The diaphragm can be activated and moved between a first position and a second position at a frequency. Movement of the diaphragm from the first position to the second position pushes air out of the at least one aperture, and movement of the diaphragm from the second position to the first position draws air into the at least one aperture.
摘要翻译：一种用于减少由转子叶片产生的叶片 - 涡流相互作用（BVI）噪声的主动控制系统。主动控制系统包括压力传感器组件，用于改变由转子叶片产生的升力的装置，以及用于通过传感器组件检测到的空气压力变化来启动装置的控制器。传感器组件设置成紧邻转子叶片，并且适于检测在转子叶片的前缘附近的转子叶片的表面上的空气压力的变化。该装置适于被控制器激活，从而改变转子叶片的升力。控制器激活装置以改变转子叶片的升力，以便在转子叶片的表面上引入补偿压力。这种补偿压力会降低气压变化的大小。用于改变由转子叶片产生的升力的装置可包括转子叶片上的至少一个孔和转子叶片内部的隔膜。隔膜可以在第一位置和第二位置之间以一个频率被激活和移动。隔膜从第一位置移动到第二位置将空气推出至少一个孔，并且隔膜从第二位置移动到第一位置将空气吸入至少一个孔。

7. 发明授权

US5791601A Apparatus and method for aerodynamic blowing control using smart materials 失效
标题翻译：使用智能材料进行气动吹风控制的装置和方法
公开(公告)号：US5791601A
公开(公告)日：1998-08-11
申请号：US517951
申请日：1995-08-22
申请人： D. Stefan Dancila , Erian A. Armanios
发明人： D. Stefan Dancila , Erian A. Armanios
IPC分类号： B64C9/38 , B64C23/00 , B64C27/615 , B64C21/04
CPC分类号： B64C27/615 , B64C23/00 , B64C9/38 , B64C2027/725 , B64C2230/04 , B64C2230/06 , B64C2230/16 , B64C2230/28 , Y02T50/166 , Y02T50/32 , Y02T50/34 , Y02T50/44
摘要： A method and apparatus for controlling the blowing of compressed air from an aerodynamic structure such as an aircraft wing or helicopter rotor blade and thus controlling the aerodynamic properties of the wing comprises a narrow slot (13) in the upper surface (15) of the structure near its trailing edge (14). Inside the wing (12) is a chamber (23) that is connected to the narrow slot (13) in the wing surface (15). The chamber (23) houses a compressed air conduit (16) for supplying and holding compressed air. A passageway (25) connects the conduit (16) to the slot (13) in the upper surface (15) of the wing (12). The lower wall (27) of the passage (25) has a slit (32) allowing a shutter (31) to move selectively into the passage (25) and obstruct the flow of compressed air through the passageway (25). The shutter (31) is attached to a smart material actuator comprising a piezoelectrical bender (29). When a control voltage is applied to the bender (29), the bender (29) will bend. The bending of the bender (29) causes the shutter (31) to move up into the passage (25) and obstruct the flow of compressed air. In this way, the flow of air out of the slot (13) in the wing surface (15) may be dynamically controlled by application of selective control voltages to the bender (29).
摘要翻译：用于控制来自诸如飞行器机翼或直升机转子叶片的空气动力学结构的压缩空气的吹送并因此控制机翼的空气动力特性的方法和装置包括在结构的上表面（15）中的窄槽（13）靠近其后缘（14）。在机翼（12）的内部是与机翼表面（15）中的窄槽（13）连接的室（23）。腔室（23）容纳用于供应和保持压缩空气的压缩空气管道（16）。通道（25）将导管（16）连接到机翼（12）的上表面（15）中的槽（13）。通道（25）的下壁（27）具有狭缝（32），允许挡板（31）选择性地移动到通道（25）中并阻止压缩空气流过通道（25）。快门（31）附接到包括压电弯曲机（29）的智能材料致动器。当控制电压施加到弯曲器（29）时，弯曲器（29）将弯曲。弯曲器（29）的弯曲使得挡板（31）向上移动到通道（25）中并阻碍压缩空气的流动。以这种方式，可以通过向弯曲机（29）施加选择性控制电压来动态地控制从机翼表面（15）中的狭槽（13）流出的空气流。

8. 发明授权

US5529458A Circulation control aerofoils 失效
标题翻译：循环控制机翼
公开(公告)号：US5529458A
公开(公告)日：1996-06-25
申请号：US291089
申请日：1994-08-18
申请人： David V. Humpherson
发明人： David V. Humpherson
IPC分类号： B64C3/14 , F04D29/18
CPC分类号： B64C3/141 , B64C2027/725 , Y02T50/34
摘要： A circulation control aerofoil having an internal chamber for receiving during operation air for exhaust through a circulation control air exhaust slot defined by spaced-apart slot lips is provided with a plurality of actuators of electrically deformable material adapted during operation to cause local bending of the aerofoil structure to which they are attached to selectively adjust the width of the air exhaust slot. The actuators may be piezo-electric actuators.
摘要翻译：具有用于在操作期间通过由间隔开的槽口限定的循环控制排气槽的用于排气的空气的循环控制机翼设置有多个可电动变形材料的致动器，其在操作期间适于引起机翼的局部弯曲它们被连接到的结构以选择性地调节排气槽的宽度。致动器可以是压电致动器。

9. 发明申请

US20130327879A1 HIGH SPEED COMPOUND ROTARY WING AIRCRAFT 有权
标题翻译：高速化合物旋转翼飞机
公开(公告)号：US20130327879A1
公开(公告)日：2013-12-12
申请号：US13493559
申请日：2012-06-11
申请人： Mark W. Scott , Stephen M. Gatto
发明人： Mark W. Scott , Stephen M. Gatto
IPC分类号： B64C27/72 , B64C27/82
CPC分类号： B64C27/72 , B64C21/04 , B64C21/08 , B64C27/82 , B64C2027/7227 , B64C2027/725 , B64C2027/7266 , B64C2027/8236 , B64C2230/06 , B64C2230/14 , B64C2230/20 , B64C2230/28 , Y02T50/166 , Y02T50/34
摘要： A rotary wing aircraft includes an airfame and an extending tail extending from the airframe. A main rotor assembly is operably connected to the airframe and includes a plurality of rotor blades operably connected to a rotor shaft, and one or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A tail rotor is operably connected to the extending tail. The tail rotor is rotatable about a tail rotor axis and the tail rotor axis movable from laterally-extending to rearward-extending.
摘要翻译：旋转翼飞机包括从机身延伸的气翼和延伸尾翼。主转子组件可操作地连接到机身并且包括可操作地连接到转子轴的多个转子叶片，以及位于多个转子叶片的一个或多个转子叶片处的一个或多个主动适应装置。一个或多个主动自适应装置可操作地连接到飞行器飞行控制系统，使得当被激活时，一个或多个主动自适应装置改变转子组件的一个或多个操作特性。尾部转子可操作地连接到延伸尾部。尾部转子可围绕尾部转子轴线旋转，并且尾部转子轴线可从横向延伸到向后延伸。

10. 发明授权

US06543719B1 Oscillating air jets for implementing blade variable twist, enhancing engine and blade efficiency, and reducing drag, vibration, download and ir signature 有权
标题翻译：振荡式空气喷射器，用于实现叶片可变扭转，增强发动机和叶片效率，并减少阻力，振动，下载和不签名
公开(公告)号：US06543719B1
公开(公告)日：2003-04-08
申请号：US09198800
申请日：1998-11-24
申请人： Ahmed A. Hassan , Friedrich K. Straub , David B. Domzalski
发明人： Ahmed A. Hassan , Friedrich K. Straub , David B. Domzalski
IPC分类号： B64C2704
CPC分类号： B64C23/04 , B64C27/001 , B64C27/467 , B64C27/51 , B64C2027/725 , B64C2230/02 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/18 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y02T50/34
摘要： A porous surface on an aircraft structure driven with oscillating positive and negative pressures is used as an active control device for attenuating negative aerodynamic interactions. The porous surfaces can be driven with positive and negative pressures either continuously or when predetermined flight conditions are present. The porous surfaces can be used on rotor blades to reduce BVI noise in descent flight conditions. The porous surfaces can be configured on rotor blades for affecting blade variable twist in accordance with various flight conditions, and can further be incorporated for reducing rotor hub vibrations as well. Porous surfaces placed on aerodynamic surfaces below the rotor blades of a tiltrotor aircraft can attenuate or eliminate download and fountain flow conditions. When placed on the trailing edges of a tip jet-exhaust driven rotor blade, the porous surfaces of the present invention can supplement the tip jet momentum of the exhaust to thereby reduce an amount of exhaust needed to drive the rotor blade.
摘要翻译：使用以振荡正负压驱动的飞机结构上的多孔表面被用作用于减弱负空气动力学相互作用的主动控制装置。多孔表面可以连续地或者当存在预定的飞行条件时以正和负压力驱动。在下降的飞行条件下，多孔表面可用于转子叶片上以减少BVI噪声。多孔表面可以配置在转子叶片上，以根据各种飞行条件影响叶片可变扭曲，并且还可以结合用于减小转子毂振动。放置在倾斜旋翼飞机转子叶片下面的空气动力学表面上的多孔表面可以减弱或消除下载和喷泉流动条件。当放置在尖端喷射排气驱动的转子叶片的后缘时，本发明的多孔表面可以补充排气的尖端喷射动量，从而减少驱动转子叶片所需的排气量。

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