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公开(公告)号：US5938404A
公开(公告)日：1999-08-17
申请号：US869372
申请日：1997-06-05
CPC分类号： B64C27/001 , B64C23/04 , B64C2230/02 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/18 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y10S416/50
摘要： An active control device for use on an aerodynamic structure is provided. The aerodynamic structure includes an outer aerodynamic skin and an interior volume, wherein the outer aerodynamic skin surrounds the interior volume. The active control device includes at least one aperture disposed on the outer aerodynamic skin and a diaphragm disposed in the interior volume of the aerodynamic structure. The at least one aperture connects the outer aerodynamic skin to the interior volume, and the diaphragm in the interior volume is movable between a first position and a second position. Movement of the diaphragm from the first position to the second position pushes air through the at least one aperture and out of the interior volume. Movement of the diaphragm from the second position to the first position draws air through the at least one aperture and into the interior volume. The diaphragm may be circular, or may be oval-shaped.
摘要翻译： 提供了一种用于空气动力学结构的主动控制装置。 空气动力学结构包括外部空气动力学皮肤和内部空间，其中外部空气动力学皮肤围绕内部空间。 主动控制装置包括设置在外部空气动力学皮肤上的至少一个孔和设置在空气动力结构的内部空间中的隔膜。 至少一个孔将外部空气动力学皮肤连接到内部空间，并且内部空间中的隔膜可在第一位置和第二位置之间移动。 隔膜从第一位置到第二位置的移动推动空气穿过至少一个孔并离开内部空间。 隔膜从第二位置到第一位置的移动通过至少一个孔吸入空气并进入内部空间。 隔膜可以是圆形的，或者可以是椭圆形。
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2.发明授权
公开(公告)号：US5813625A
公开(公告)日：1998-09-29
申请号：US727980
申请日：1996-10-09
IPC分类号： B64C23/06 , B64C27/467 , B64C27/00
CPC分类号： B64C27/467 , B64C23/06 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/22 , B64C2230/28 , Y02T50/162 , Y02T50/166
摘要： A pressurized porous surface near the leading edge of a rotorcraft blade, is designed to be used as an active control device which alleviates the aerodynamics of blade vortex interactions (BVI) and thus the impulsive BVI noise levels and signature. The pressurized porous surface can be actuated on an azimuth-dependent deployment schedule or actuated continuously. The pressurized porous surface is supplied with either positively pressurized air, negatively pressurized air, or a combination of both, when actuated. The pressurized porous surface targets the local blade aerodynamics, rather than the vortex strength or blade/vortex separation distance. This targeting can be achieved through use of negatively pressurized air (suction) blowing in a direction normal to the blade surface to reduce the rotor blade's effective thickness resulting in a smaller leading edge radius as perceived by the vortex wake, and positively pressurized air (blowing) to increase the effective thickness resulting in an increase in the leading edge radius of the blade.
摘要翻译： 旋翼飞机叶片前缘附近的加压多孔表面被设计为用作主动控制装置，其减轻叶片涡流相互作用（BVI）的空气动力学，从而减轻脉冲BVI噪声水平和签名。 加压的多孔表面可以在依赖于方位的部署计划上被致动或连续致动。 被加压的多孔表面在被致动时被供应有正压空气，负压空气或两者的组合。 加压多孔表面针对局部叶片的空气动力学，而不是涡流强度或叶片/涡流分离距离。 这种瞄准可以通过在垂直于叶片表面的方向上使用负压空气（吸入）吹气来实现，以减小转子叶片的有效厚度，从而导致由涡流尾迹感知到的较小的前缘半径，以及正压的空气 ）以增加有效厚度，导致叶片的前缘半径增加。
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3.发明授权Oscillating air jets for helicopter rotor aerodynamic control and BVI noise reduction 失效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
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。
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公开(公告)号：US06851990B2
公开(公告)日：2005-02-08
申请号：US10323105
申请日：2002-12-18
CPC分类号： B63H11/06 , B63G2013/022 , F04B17/044
摘要： A method and apparatus is disclosed for producing propulsion underwater with minimal acoustical emission. In basic concept, the method comprises the expulsion and sucking of liquid into and out of a liquid port of a watercraft in a manner generating compression and expansion waves adjacent the liquid port. Such expansion and compression waves generate a positive net thrust on the watercraft in a direction opposite that of their expulsion. A reciprocating member and an actuator are also disclosed for generating the forces and energy necessary to create the expansion and compression waves.
摘要翻译： 公开了一种在最小声发射下生产水下推进的方法和装置。 在基本概念中，该方法包括以邻近液体端口产生压缩和膨胀波的方式将液体排出和吸入船舶的液体端口。 这种膨胀和压缩波在与其驱逐相反的方向上产生对船只的正净推力。 还公开了往复式构件和致动器，用于产生产生膨胀和压缩波所需的力和能量。
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5.发明授权Oscillating air jets for implementing blade variable twist, enhancing engine and blade efficiency, and reducing drag, vibration, download and ir signature 有权振荡式空气喷射器，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
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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6.发明授权Method and device for low-noise underwater propulsion and for reducing hull drag 有权用于低噪声水下推进和减少船体阻力的方法和装置公开(公告)号：US06860770B2
公开(公告)日：2005-03-01
申请号：US10631125
申请日：2003-07-31
CPC分类号： B63H11/06 , B63G2013/022 , F04B17/044
摘要： A method and apparatus is disclosed for producing propulsion underwater with minimal acoustical emission. In basic concept, the method comprises the expulsion and sucking of liquid into and out of a liquid port of a watercraft in a manner generating compression and expansion waves adjacent the liquid port. Such expansion and compression waves generate a positive net thrust on the watercraft in a direction opposite that of their expulsion. Also disclosed is a method and apparatus for reducing the drag caused by hull skin friction by actively increasing the momentum of the liquid stream boundary layer adjacent a watercraft via the expulsion of fluid (liquid or gas) from ports in the hull of such a watercraft.
摘要翻译： 公开了一种在最小声发射下生产水下推进的方法和装置。 在基本概念中，该方法包括以邻近液体端口产生压缩和膨胀波的方式将液体排出和吸入船舶的液体端口。 这种膨胀和压缩波在与其驱逐相反的方向上产生对船只的正净推力。 还公开了一种用于通过从这种船舶的船体中的端口排出流体（液体或气体）而主动地增加邻近船舶的液体流边界层的动量来减少由船体表面摩擦引起的阻力的方法和装置。
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公开(公告)号：US06471477B2
公开(公告)日：2002-10-29
申请号：US09742489
申请日：2000-12-22
IPC分类号： B64C2704
CPC分类号： B64C23/04 , B64C2230/02 , Y02T50/166
摘要： A jet actuator positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof includes a movable member linearly displaced by a voice coil mechanism and a flexible diaphragm defining a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the movable member changes the shape of the flexible diaphragm to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a pair of pistons joined by a cross element, one of the pistons being attached to the flexible diaphragm. In one embodiment, the flexible diaphragm comprises a bladder sealed around the orifice. The movable member is desirably made of composite material to reduce its inertia, and at least the piston attached to the flexible diaphragm may be stiffened with a composite laminate structure. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. In this regard, multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid ingestion.
摘要翻译： 位于空气动力结构中的中空空间内的喷气致动器，用于控制其空气动力学表面上的流动，包括由音圈机构线性移位的可移动部件和限定通过空气动力学表面外部的压缩室的柔性隔膜 孔。 可动构件的往复位移改变了柔性隔膜的形状，以便将流体（例如空气）交替地排出并通过孔口将流体拉入压缩室。 可动构件包括一对由十字元件连接的活塞，一个活塞附接到柔性隔膜。 在一个实施例中，柔性隔膜包括围绕孔口密封的囊。 可移动部件期望地由复合材料制成以减小其惯性，并且至少附接到柔性隔膜的活塞可以用复合层压结构加固。 可以通过使用位于空气动力学表面或活塞中的单向阀来增加到压缩室的流体进入。 在这方面，多个挡板阀可以围绕空气动力学表面中的孔口以增加流体摄取。
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公开(公告)号：US06713901B2
公开(公告)日：2004-03-30
申请号：US10098107
申请日：2002-03-14
IPC分类号： H02K4100
CPC分类号： H02K33/18 , B64C21/02 , B64C2230/02 , F04B35/045 , Y02T50/166
摘要： A linear electromagnetic zero net mass jet (ZNMJ) actuator incorporating a pair of permanent magnets. The magnets are arranged such that an air gap is formed therebetween and further such that opposite poles of the magnets are arranged on opposite sides of the air gap. This concentrates the flux field across the air gap. A coil is disposed in the air gap. The coil is attached to a diaphragm which acts as a piston. When an electric current is applied to the coil, the flux field across the air gap causes a rapidly oscillating motion of the diaphragm. The actuator provides an increased rate of displacement of the piston as compared to single magnet ZNMJ actuators, and thus provides a higher momentum output across a broad frequency and voltage spectrum than conventional ZNMJ actuators using a single magnet.
摘要翻译： 包含一对永磁体的线性电磁零网质量喷射（ZNMJ）致动器。 磁体被布置成使得在它们之间形成气隙，并且进一步使得磁体的相对极布置在气隙的相对侧上。 这将通量场集中在气隙上。 线圈设置在气隙中。 线圈连接到作为活塞的隔膜。 当向线圈施加电流时，横跨气隙的磁场将导致隔膜的快速振荡运动。 与单磁体ZNMJ致动器相比，致动器提供了增加的活塞位移率，因此与使用单个磁体的常规ZNMJ致动器相比，在宽频率和电压频谱上提供更高的动量输出。
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公开(公告)号：US6135713A
公开(公告)日：2000-10-24
申请号：US233986
申请日：1999-01-19
IPC分类号： B64C27/00 , B64C27/615 , B64C9/00
CPC分类号： B64C27/615 , B64C27/001 , B64C2027/7277 , B64C2027/7283 , B64C2027/7288 , Y02T50/34
摘要： An actively controlled helicopter rotor blade includes a trailing edge flap actuated by a fast-acting actuator. A lightweight, rugged, fast-acting actuator suitable for use as the flap actuator comprises a pair of column actuators composed of a smart material such as piezoelectric, magnetostrictive, shape memory alloy or other material that exhibits a shape change when subjected to an external stimulus. Each of the column actuators is composed of multiple piezoelectric ceramic actuator elements bonded together to form the individual columns. Each of the column actuators engages the base of an actuator tube that, in turn, is urged against the column actuators by a tension member. Differential voltage applied to the columns causes a differential elongation of the column actuators, which causes the actuator tube to pivot about an axis proximal the tips of the column actuators. The movement of the actuator tube is coupled by a linkage to the rotor blade flap. Spherical joints are disposed between the column actuators and the actuator tube to prevent transmission of substantial bending loads to the column actuators and a mid-point support is also provided for each of the column actuators to limit the magnitude of acceleration induced bending loads, which would otherwise lead to tensile failure of the ceramic actuator elements.
摘要翻译： 主动控制的直升机转子叶片包括由快速作用的致动器驱动的后缘翼片。 一种轻巧，坚固，快速作用的致动器，适合用作翼片致动器，包括一对柱形致动器，其由诸如压电，磁致伸缩，形状记忆合金或其它材料的智能材料组成，当受到外部刺激时，其表现出形状变化 。 每个柱致动器由多个压电陶瓷致动器元件组成，结合在一起以形成各个柱。 每个柱致动器接合致动器管的基部，而致动器管的基部又被张力构件推靠在柱致动器上。 施加到柱的差分电压导致柱致动器的差异伸长，这导致致动器管围绕靠近柱致动器的尖端的轴线枢转。 致动器管的运动通过连接件与转子叶片翼片联接。 球形接头设置在柱致动器和致动器管之间，以防止将实质的弯曲载荷传递到柱致动器，并且还为每个柱致动器提供中点支撑件，以限制加速度引起的弯曲载荷的大小， 否则导致陶瓷致动器元件的拉伸失效。
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