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1. 发明申请

US20180237129A1 METHOD AND APPARATUS FOR DETERMINING A MOVEMENT DIRECTION OF A COMPONENT OF A MECHANISM 审中-公开
公开(公告)号：US20180237129A1
公开(公告)日：2018-08-23
申请号：US15891629
申请日：2018-02-08
申请人： Airbus Operations Limited
发明人： Murad EL-BAKRY
IPC分类号： B64C25/28 , B64C25/22 , B64C29/00 , F04B17/04 , F04B9/10 , F16K31/124 , F16K37/00
CPC分类号： B64C25/28 , B64C25/22 , B64C29/0091 , B64C2230/02 , B64C2230/06 , F04B9/10 , F04B17/04 , F15B2013/0409 , F16K11/07 , F16K31/124 , F16K37/0041
摘要： An apparatus for determining a movement direction of a component of a mechanism. The apparatus includes an acoustic emission sensor arranged to detect acoustic emission from the mechanism, and a processor arranged to determine a Doppler shift in a frequency characteristic of the measured acoustic emission and to determine a movement direction of a component of the mechanism on the basis of the determined Doppler shift. A method of determining a movement direction of a component of a mechanism including detecting acoustic emission from the mechanism and determining a Doppler shift in a frequency characteristic of the measured acoustic emission and, determining, based on the Doppler shift in the frequency characteristic, a movement direction of the component of the mechanism.

2. 发明授权

US09994301B2 Virtual aerodynamic surface systems 有权
公开(公告)号：US09994301B2
公开(公告)日：2018-06-12
申请号：US14083077
申请日：2013-11-18
申请人： ROHR, INC.
发明人： Teresa M. Kruckenberg , Vijay V. Pujar , Robert L. Braden
IPC分类号： B64C1/00 , B64C1/38 , B64C21/00 , B64C23/00
CPC分类号： B64C1/38 , B64C21/00 , B64C23/005 , B64C2220/00 , B64C2230/02 , Y02T50/166
摘要： A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.

3. 发明申请

US20180079492A1 Flow control device, flow profile body and flow influencing method with acoustic wave generation 审中-公开
公开(公告)号：US20180079492A1
公开(公告)日：2018-03-22
申请号：US15813818
申请日：2017-11-15
申请人： Airbus Defence and Space GmbH , Universität des Saarlandes
发明人： Helmut Seidel , Dara Feili , Karin Bauer , Christian Kiefer
IPC分类号： B64C23/00 , B64D15/16 , H04R1/02 , H04R1/40
CPC分类号： B64C23/005 , B64C23/06 , B64C2230/02 , B64D15/163 , H04R1/028 , H04R1/403 , Y02T50/166
摘要： For adaptively influencing a flow with little intrusion into the surface, a flow control device is provided to influence the flow of a fluid medium on a fluid-dynamical surface of a fluid-dynamical profile body. An acoustic wave generating device is used to generate a standing acoustic wave with locally defined antinodes and nodes, and/or a sonic pulse is focused in a locally defined manner.

4. 发明申请

US20160101877A1 SUSPENSION STRUT SERVICING 审中-公开
标题翻译：停牌服务
公开(公告)号：US20160101877A1
公开(公告)日：2016-04-14
申请号：US14891599
申请日：2014-05-09
申请人： AIRBUS OPERATIONS LIMITED
发明人： Alan SHEPHERD , Julian DUNCAN
IPC分类号： B64F5/00 , G01F23/296 , G01M17/04
CPC分类号： G01M17/04 , B64C25/60 , B64C2230/02 , B64F5/60 , F16F9/063 , G01F23/296 , Y02T50/166
摘要： A method for servicing a landing gear strut in service supporting an aircraft including: determining a current amount of damping fluid in the landing gear strut; determining a required amount of the damping fluid for correct servicing of the landing gear strut; and adjusting the current amount of damping fluid in the landing gear strut so that the current amount of damping fluid complies with the required amount of damping fluid.
摘要翻译：一种用于维修支撑飞行器的起落架支柱的方法，包括：确定起落架支柱中的阻尼流体的当前量; 确定用于正确维修起落架支柱的阻尼流体的所需量; 并且调节起落架支柱中的阻尼流体的当前量，使得阻尼流体的当前量符合所需量的阻尼流体。

5. 发明申请

US20150314870A1 MICRO UNMANNED AERIAL VEHICLE AND METHOD OF CONTROL THEREFOR 有权
标题翻译：微型无人驾驶航空器及其控制方法
公开(公告)号：US20150314870A1
公开(公告)日：2015-11-05
申请号：US14738467
申请日：2015-06-12
申请人： BCB INTERNATIONAL LTD.
发明人： Barry Davies
IPC分类号： B64C39/02 , G05D1/10 , G01S15/89 , G05D1/00
CPC分类号： B64C39/024 , B64C19/00 , B64C39/028 , B64C2201/00 , B64C2201/14 , B64C2201/141 , B64C2230/00 , B64C2230/02 , G01S15/06 , G01S15/88 , G01S15/89 , G01S15/8913 , G01S15/8929 , G01S15/8993 , G01S15/93 , G05D1/0088 , G05D1/0202 , G05D1/101 , G05D1/102 , Y10S367/909
摘要： A micro unmanned aerial vehicle or drone (“UAV”) 10 is remotely controlled through an HMI, although this remote control is supplemented by and selectively suppressed by an on-board controller. The controller operates to control the generation of a sonar bubble that generally encapsulates the UAV. The sonar bubble, which may be ultrasonic in nature, is produced by a multiplicity of sonar lobes generated by specific sonar emitters associated with each axis of movement for the UAV. The emitters produce individual and beamformed sonar lobes that partially overlap to provide stereo or bioptic data in the form of individual echo responses detected by axis-specific sonar detectors. In this way, the on-board controller is able to interpret and then generate 3-D spatial imaging of the physical environment in which the UAV is currently moving or positioned. The controller is therefore able to plot relative and absolute movement of the UAV through the 3-D space by recording measurements from on-board gyroscopes, magnetometers and accelerometers. Data from the sonar bubble can therefore both proactively prevent collisions with objects by imposing a corrective instruction to rotors and other flight control system and can also assess and compensate for sensor drift.
摘要翻译：微型无人驾驶飞行器或无人驾驶飞机（“UAV”）10通过HMI进行远程控制，尽管该遥控器由车载控制器补充并选择性地抑制。控制器用于控制通常封装无人机的声纳气泡的产生。本质上可能是超声波的声纳气泡由与用于UAV的每个运动轴相关联的特定声纳发射器产生的多个声纳波瓣产生。发射器产生单个和波束形成的声纳波瓣，其部分重叠以提供以轴特定声纳探测器检测的单独回波响应形式的立体声或生物数据。以这种方式，车载控制器能够解释然后生成UAV当前正在移动或定位的物理环境的三维空间成像。因此，控制器能够通过记录来自车载陀螺仪，磁力计和加速度计的测量值来绘制UAV通过3-D空间的相对和绝对运动。因此，来自声纳气泡的数据可以通过对转子和其他飞行控制系统施加纠正指令来主动防止与物体的碰撞，并且还可以评估和补偿传感器漂移。

6. 发明授权

US08887482B1 Active flow control with pulse detonation actuators 有权
标题翻译：主动流量控制与脉冲爆震执行器
公开(公告)号：US08887482B1
公开(公告)日：2014-11-18
申请号：US12704675
申请日：2010-02-12
申请人： Robert T. Ruggeri , Ephraim Gutmark
发明人： Robert T. Ruggeri , Ephraim Gutmark
IPC分类号： F02K7/02 , F02C5/00
CPC分类号： F02C7/00 , B64C23/04 , B64C2230/02 , F02K1/82 , F02K9/34 , F02K9/60 , F05D2270/17 , Y02T50/166
摘要： Concepts and technologies described herein provide for the creation of a high speed actuating fluid flow utilizing one or more pulse detonation actuators. According to one aspect of the disclosure provided herein, an actuating flow trigger is detected with respect to a high speed airflow over an aerodynamic surface. In response, a pulse detonation actuator is activated and a resulting high speed actuating flow is directed into the high speed airflow to alter at least one attribute of the high speed airflow.
摘要翻译：本文描述的概念和技术提供了利用一个或多个脉冲爆震致动器创建高速致动流体流。根据本文提供的本发明的一个方面，相对于空气动力学表面上的高速气流检测起动流量触发器。作为响应，脉冲爆震致动器被激活，并且所得到的高速致动流被引导到高速气流中以改变高速气流的至少一个属性。

7. 发明授权

US08645007B2 Aircraft with an arrangement of flow-influencing devices 有权
标题翻译：具有流量影响装置布置的飞机
公开(公告)号：US08645007B2
公开(公告)日：2014-02-04
申请号：US13491629
申请日：2012-06-08
申请人： Burkhard Gölling , Rudibert King , Ulrich Notger Heinz , Wolfgang Nitsche
发明人： Burkhard Gölling , Rudibert King , Ulrich Notger Heinz , Wolfgang Nitsche
IPC分类号： B64C19/00
CPC分类号： B64C21/025 , B64C21/08 , B64C2230/02 , Y02T50/166
摘要： An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.
摘要翻译：一种飞机，其在每个机翼的至少一个表面段中具有相应的流量影响装置的布置，其在翼展方向上延伸以便影响表面段上的流体流动，以及用于测量流动状态的流动状态传感器装置在飞行控制装置上，其中所述飞行控制装置具有流量影响目标参数设定装置，该流量影响目标参数设定装置与所述流量影响装置的装置连接，用于产生所述至少一个表面的流量影响装置的目标参数其中所述流量影响装置被设计成使用所述目标参数来改变所述局部升力系数或在分别位于所述段的所述牵引系数和升力系数之间的相关性。

8. 发明授权

US07990287B2 Ultrasonic drag modulation 有权
标题翻译：超声波拖曳调制
公开(公告)号：US07990287B2
公开(公告)日：2011-08-02
申请号：US12834155
申请日：2010-07-12
申请人： Peter M. Bonutti
发明人： Peter M. Bonutti
IPC分类号： H04B14/00
CPC分类号： F15D1/0075 , B60C19/00 , B62D35/00 , B63B1/34 , B63B2039/068 , B63H9/04 , B63H9/06 , B64C23/005 , B64C2230/02 , F02B2075/125 , F02M27/08 , F02M69/041 , F15D1/12 , Y02T10/123 , Y02T50/166 , Y02T70/121 , Y02T70/583 , Y10T137/0391 , Y10T137/206 , Y10T137/2191
摘要： Drag experienced by a vehicle travelling through an environmental media, such as air, is actively modulated by an energy beam which may either increase or decrease the drag. The energy beam may provide either a chemical, acoustic, or electromagnetic energy at a transition region between turbulent and laminar flow or at the leading edge of a laminar flow, or in the direction of a crosswind, in order to facilitate the respective increase or decrease in drag. An energy beam may be directed in a rearwards direction, relative to a direction of travel.
摘要翻译：通过环境介质（如空气）行驶的车辆经历的拖动由能量束主动调制，能量束可能增加或减少阻力。能量束可以在湍流和层流之间的过渡区域或在层流的前缘处或在侧风方向上提供化学，声学或电磁能，以便于相应的增加或减小在拖动。能量束可以相对于行进方向在向后的方向上被引导。

9. 发明授权

US07802760B2 Boundary layer control arrangement 有权
标题翻译：边界层控制布置
公开(公告)号：US07802760B2
公开(公告)日：2010-09-28
申请号：US11176247
申请日：2005-07-08
申请人： John R Webster
发明人： John R Webster
IPC分类号： B64C21/04
CPC分类号： F02C7/04 , B64C2230/02 , B64D2033/0226 , F01D5/145 , F04D29/681 , F15D1/12 , Y02T50/166 , Y02T50/673
摘要： A boundary layer control arrangement comprises a pulse generator communicating with a surface having a fluid boundary layer thereacross. The boundary layer control arrangement further includes a fluid supply means for supplying a fluid to the surface via the pulse generator. The pulse generator is constructed such that fluid acts on the pulse generator to cause the fluid to pulse. Pulsing fluid passes from the pulse generator to the surface.
摘要翻译：边界层控制装置包括与其上具有流体边界层的表面连通的脉冲发生器。边界层控制装置还包括用于经由脉冲发生器将流体供应到表面的流体供应装置。脉冲发生器被构造成使得流体作用在脉冲发生器上以使流体脉冲。脉冲流体从脉冲发生器传递到表面。

10. 发明申请

US20060196638A1 System and method for thermal management using distributed synthetic jet actuators 审中-公开
公开(公告)号：US20060196638A1
公开(公告)日：2006-09-07
申请号：US11325239
申请日：2006-01-04
申请人： Ari Glezer , Raghavendran Mahalingam
发明人： Ari Glezer , Raghavendran Mahalingam
IPC分类号： F24H3/02
CPC分类号： H01L23/467 , B64C2230/02 , F04F7/00 , F15D1/009 , F15D1/08 , G06F1/20 , H01L2924/0002 , H05K7/20172 , Y02T50/166 , H01L2924/00
摘要： One embodiment of the device comprises a device for thermal management. More particularly, one embodiment comprises a synthetic jet actuator (60) and a tube (61). The synthetic jet actuator (60), though not required, typically comprises a housing (47) defining an internal chamber (45) and having an orifice (46) in a wall (44) of the housing (47). The synthetic jet actuator (60) typically also comprises a flexible diaphragm (42) forming a portion of the housing (47). The tube (61) of this exemplary embodiment typically comprises a proximal end (64) and a distal end (65), the proximal end (64) being positioned adjacent to the synthetic jet actuator (60). In this embodiment, operation of the synthetic jet actuator (60) causes a synthetic jet stream (52) to form at the distal end (65) of the tube (61).

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