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公开(公告)号：US09908617B2
公开(公告)日：2018-03-06
申请号：US13114006
申请日：2011-05-23
CPC分类号： B64C15/14 , B64C21/02 , B64C2230/02 , Y02T50/166
摘要： An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave.
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公开(公告)号：US20110309201A1
公开(公告)日：2011-12-22
申请号：US13114006
申请日：2011-05-23
IPC分类号： B64C21/04
CPC分类号： B64C15/14 , B64C21/02 , B64C2230/02 , Y02T50/166
摘要： An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave.
摘要翻译： 一种空中飞行器包括设计用于跨音速飞行的翼型。 翼型在跨音速飞行期间具有超音速流动区域。 翼面的表面在该区域内或内部具有上游和下游孔。 空中飞行器还包括一个主动流量控制系统，用于通过控制通过孔口的流量来控制跨音速飞行中的空中飞行器运动，以改变该区域中冲击波的强度和位置。 该系统产生气动不平衡以移动冲击波。
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公开(公告)号：US08016245B2
公开(公告)日：2011-09-13
申请号：US11583140
申请日：2006-10-18
申请人： Ahmed A. Hassan , Bradley A. Osborne , Scott Schwimley , Garry Billman , Mary Billman, legal representative
CPC分类号： B64C23/04 , B64C2003/148 , Y02T50/12
摘要： A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.
摘要翻译： 用于减少移动平台的整体拖动的系统包括气流形成边界层的表面和通常正常的冲击波。 气流处于跨音速和超音速之一的第一速度。 振荡射流注入并提取穿过表面的喷射流。 射流处于基本上小于第一速度的第二速度。 再循环区域是正常冲击波的上游，并且至少部分地设置在边界层中。 至少通过振荡射流建立再循环区域。 一般倾斜的波浪由再循环区域建立，削弱了正常的冲击波，减少了表面经受的整体阻力。
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公开(公告)号：US07255309B2
公开(公告)日：2007-08-14
申请号：US10890639
申请日：2004-07-14
申请人： Clete M. Boldrin , Ahmed A. Hassan
发明人： Clete M. Boldrin , Ahmed A. Hassan
IPC分类号： B64C21/04
CPC分类号： B64C21/08 , B64C2230/04 , B64C2230/18 , Y02T50/166
摘要： Methods and apparatus for controlling the attitude of a mobile platform with a resolution suitable for vernier attitude control. In a preferred embodiment, a method includes flowing fluid through an orifice of an aerodynamic surface. The method also includes modifying a boundary layer of the aerodynamic surface with the flowing fluid. Another preferred embodiment provides an aerodynamic member of a mobile platform. The aerodynamic member includes an aerodynamic surface, an orifice, an actuator, and a fluid moving member. The orifice is in the aerodynamic surface and the actuator is subject to friction and backlash. The fluid moving member communicates with the orifice and causes the fluid to flow through the orifice to modify the boundary layer of aerodynamic surface.
摘要翻译： 用于以适合游标态度控制的分辨率来控制移动平台姿态的方法和装置。 在优选实施例中，一种方法包括使流体流过空气动力学表面的孔口。 该方法还包括用流动的流体改变空气动力学表面的边界层。 另一个优选实施例提供了一种移动平台的空气动力学构件。 空气动力学构件包括空气动力学表面，孔，致动器和流体移动构件。 孔口处于空气动力学表面，致动器经受摩擦和间隙。 流体移动构件与孔口连通并使流体流过孔口以改变空气动力学表面的边界层。
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公开(公告)号：US07195210B2
公开(公告)日：2007-03-27
申请号：US10357022
申请日：2003-02-03
IPC分类号： B64C3/46
CPC分类号： B64C3/54 , B64C3/30 , B64C3/38 , B64C3/46 , B64C5/10 , B64C27/473 , B64C2003/445 , Y02T50/14
摘要： An airfoil member (14) includes a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. The exterior wall (32) includes a layer with one or more fibers embedded therein. The exterior wall (32) controls size, shape, and expansion ability of the geometric morphing device (18).
摘要翻译： 机翼构件（14）包括几何变形装置（18）。 几何变形装置（18）具有可充气构件（30）。 可膨胀构件（30）具有外壁（32）和多个充气状态。 外壁（32）包括具有嵌入其中的一个或多个纤维的层。 外壁（32）控制几何变形装置（18）的尺寸，形状和膨胀能力。
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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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7.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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公开(公告)号：US5711651A
公开(公告)日：1998-01-27
申请号：US662601
申请日：1996-06-13
CPC分类号： B64C27/001 , B64C27/463 , B64C2027/7266 , Y02T50/34
摘要： An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to be actuated to a deflected position during rotation of the rotor blade through predetermined regions of the rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of the rotor azimuth. Through the careful azimuth-dependent deployment and retraction of the flap over the rotor disk, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved).
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公开(公告)号：US20090084906A1
公开(公告)日：2009-04-02
申请号：US11583140
申请日：2006-10-18
IPC分类号： B64C21/08
CPC分类号： B64C23/04 , B64C2003/148 , Y02T50/12
摘要： A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.
摘要翻译： 用于减少移动平台的整体拖动的系统包括气流形成边界层的表面和通常正常的冲击波。 气流处于跨音速和超音速之一的第一速度。 振荡射流注入并提取穿过表面的喷射流。 射流处于基本上小于第一速度的第二速度。 再循环区域是正常冲击波的上游，并且至少部分地设置在边界层中。 至少通过振荡射流建立再循环区域。 一般倾斜的波浪由再循环区域建立，削弱了正常的冲击波，减少了表面经受的整体阻力。
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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。
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