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    FLEXIBLE ANTENNA INTEGRATED WITH AN ARRAY OF SOLAR CELLS
    4.
    发明申请
    FLEXIBLE ANTENNA INTEGRATED WITH AN ARRAY OF SOLAR CELLS 审中-公开
    柔性天线与太阳能电池阵列集成

    公开(公告)号：US20170033247A1

    公开(公告)日：2017-02-02

    申请号：US15302277

    申请日：2015-04-29

    Applicant: The Regents of the University of Michigan

    Inventor： Kamal Sarabandi ,  Kyusang Lee ,  Stephen R. Forrest ,  Jungsuek Oh

    IPC: H01L31/046 ,  B64C39/02 ,  B64C33/00 ,  H01L31/18 ,  H01Q9/04

    CPC classification number: H01L31/046 ,  B64C33/00 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/066 ,  B64D2211/00 ,  H01L27/142 ,  H01L31/022425 ,  H01L31/184 ,  H01L31/1868 ,  H01Q9/0421 ,  Y02E10/50 ,  Y02T50/55

    Abstract: A device comprising a thin film solar cell with an integrated flexible antenna, such as a meander line antenna, is disclosed. In an embodiment, the device comprises a substrate and an array of solar cells disposed on the substrate, wherein the array of solar cells are interconnected by metal conductors that carry DC power from the solar cells and which form at least part of the flexible antenna. In their capacity as an antenna, the metal conductors operate cooperatively with the solar cells to radiate an RF signal, receive an RF signal, or both radiate and receive an RF signal. The device optionally comprises a choke disposed on the substrate and electrically coupled to the array of solar cells, wherein the choke operates to impede conduction of the RF signal. A method of making the disclosed device is also disclosed.

    Abstract translation: 公开了一种包括具有集成柔性天线的薄膜太阳能电池的装置，例如曲折线天线。 在一个实施例中，该装置包括衬底和设置在衬底上的太阳能电池阵列，其中太阳能电池阵列由携带来自太阳能电池的DC电力并且形成柔性天线的至少一部分的金属导体互连。 以它们作为天线的能力，金属导体与太阳能电池协同工作以辐射RF信号，接收RF信号，或者两者辐射并接收RF信号。 该装置可选地包括设置在基板上并电耦合到太阳能电池阵列的扼流器，其中扼流器操作以阻止RF信号的导通。 还公开了制造所公开的装置的方法。

    FLAPPING WING AERIAL VEHICLES
    5.
    发明申请
    FLAPPING WING AERIAL VEHICLES 有权
    飞行机动车

    公开(公告)号：US20150307191A1

    公开(公告)日：2015-10-29

    申请号：US14698375

    申请日：2015-04-28

    Applicant: Daedalus Flight Systems, LLC ,  University of Maryland, College Park

    Inventor： Paul D. SAMUEL ,  Imraan FARUQUE ,  James Sean HUMBERT

    IPC: B64C33/02

    CPC classification number: B64C33/02 ,  B64C39/024 ,  B64C2201/025

    Abstract: An autonomous flapping wing aerial vehicle can have a vehicle body, a pair of flapping wings, tunable wing hinges, and elastic drive mechanisms. The tunable wing hinges can be coupled to the flapping wings. Each wing hinge can be constructed to deliver a force to a respective one of the flapping wings to alter end points of a stroke thereof. The elastic drive mechanisms can rotate the flapping wings about pivot points to produce the strokes of the flapping wings. The elastic drive mechanism can be driven at or near a resonance thereof. Alterations to the strokes of the flapping wings produced by the combined effect of the tunable wing hinges and the elastic drive mechanisms, operating in parallel, can provide steering control of the aerial vehicle.

    Abstract translation: 自主的扑翼机动车辆可以具有车身，一对打翼，可调翼铰链和弹性驱动机构。 可调谐翼铰链可以联接到扑翼。 每个翼铰链可以构造成向相应的一个拍动翼传递一个力，以改变其中风的终点。 弹性驱动机构可以使摆动翼围绕枢转点旋转以产生拍动翼的冲程。 弹性驱动机构可以在其共振处或其附近被驱动。 由可调谐翼铰链和平行操作的弹性驱动机构的组合效应产生的扑翼的冲程的改变可以提供飞行器的转向控制。

    Resonance engine
    6.
    发明授权
    Resonance engine 有权
    共振引擎

    公开(公告)号：US09102407B2

    公开(公告)日：2015-08-11

    申请号：US13515503

    申请日：2010-12-15

    Applicant: Guy Thomas Greenyer

    Inventor： Guy Thomas Greenyer

    IPC: B64C33/02 ,  B64C39/02

    CPC classification number: B64C39/028 ,  B64C33/02 ,  B64C2201/025

    Abstract: A resonance engine is disclosed including: a driver plate, to which is coupled at least one oscillatory transducer; a drive signal generator connected to the oscillatory transducer for excitation thereof; a first spring-mass resonator, having a first natural resonant frequency, with a proximal end attached to the driver plate and a free distal end; and a reaction means attached to the driver plate substantially opposite to the first spring-mass resonator. When the oscillatory transducer is excited by a drive signal from the generator having a component at or close to said natural resonant frequency, the first spring-mass resonator oscillates at resonance, substantially in anti-phase to the driver plate. Small vibrational strains in the oscillatory transducer are converted to large strains of controllable kinematic movements.

    Abstract translation: 公开了一种共振发动机，包括：驱动器板，其耦合至少一个振荡换能器; 驱动信号发生器，连接到所述振荡换能器以用于激励; 具有第一自然谐振频率的第一弹簧质量谐振器，其近端连接到驱动器板和自由远端; 以及附接到驱动器板的基本上与第一弹簧质量谐振器相对的反作用装置。 当振荡传感器被来自具有等于或接近于所述固有谐振频率的分量的发生器的驱动信号激发时，第一弹簧 - 质量谐振器以谐振器振荡，基本上与驱动器板反相。 振荡传感器中的小振动应变被转换成大的可控运动运动。

    Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping
    7.
    发明申请
    Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping 有权
    非正弦翼飞行器的飞行器飞行机构与控制方法

    公开(公告)号：US20140158821A1

    公开(公告)日：2014-06-12

    申请号：US13969258

    申请日：2013-08-16

    Applicant: AeroVironment, Inc.

    Inventor： Matthew Todd Keennon ,  Alexander Andryukov ,  Karl Robert Klingebiel ,  Henry Thome Won

    IPC: B64C39/00

    CPC classification number: B64C39/003 ,  B64C33/02 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/042

    Abstract: A flapping wing driving apparatus includes at least one crank gear capstan rotatably coupled to a crank gear, the at least one crank gear capstan disposed radially offset from a center of rotation of the crank gear; a first wing capstan coupled to a first wing, the first wing capstan having a first variable-radius drive pulley portion; and a first drive linking member configured to drive the first wing capstan, the first drive linking member windably coupled between the first variable-radius drive pulley portion and one of the at least one crank gear capstan; wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank gear.

    Abstract translation: 拍动翼驱动装置包括可旋转地联接到曲柄齿轮的至少一个曲柄齿轮主动轮，所述至少一个曲柄齿轮主动轮设置在径向偏离曲柄齿轮的旋转中心; 第一翼形绞盘，其联接到第一翼，所述第一翼形绞盘具有第一可变半径的驱动皮带轮部分; 以及第一驱动连接构件，其构造成驱动所述第一翼形主导轮，所述第一驱动连接构件可变地联接在所述第一可变半径驱动滑轮部分和所述至少一个曲柄齿轮绞盘之一之间; 其中所述第一翼形绞盘被配置成响应于所述曲柄齿轮的恒定角度旋转而不间断地，有角度地旋转。

    Micro aviation vehicle
    9.
    发明申请
    Micro aviation vehicle 审中-公开
    微型航空车辆

    公开(公告)号：US20070205322A1

    公开(公告)日：2007-09-06

    申请号：US11367377

    申请日：2006-03-06

    Applicant: Wei-Hsiang Liao

    Inventor： Wei-Hsiang Liao

    IPC: B64C33/00

    CPC classification number: B64C33/02 ,  B64C39/028 ,  B64C2201/025

    Abstract: A micro aviation vehicle is provided which includes a body, a first wing set, a second wing set, an actuator and a power module. The first wing set and the second wing set are disposed on the left and right sides of the body respectively, and are connected with one end of the actuator. A first angle controller and a second angle controller are used to control the swing angle of the first wing set and the swing angle of the second wing set, respectively. The power module draws the actuator through the rotation of a driving gear, and then the first wing set together with the second wing set are associated with the actuator to flap back-and-forth.

    Abstract translation: 提供一种微型航空器，其包括主体，第一机翼组，第二机翼组，致动器和电源模块。 第一翼组和第二翼组分别设置在主体的左侧和右侧，并且与致动器的一端连接。 第一角度控制器和第二角度控制器分别用于控制第一机翼组的摆动角度和第二机翼组的摆动角度。 功率模块通过驱动齿轮的旋转拉动致动器，然后与第二机翼组一起的第一机翼组件与致动器相关联以前后翻动。

    Microstructures using carbon fiber composite honeycomb beams
    10.
    发明授权
    Microstructures using carbon fiber composite honeycomb beams 失效
    使用碳纤维复合蜂窝梁的微观结构

    公开(公告)号：US07036769B2

    公开(公告)日：2006-05-02

    申请号：US10830374

    申请日：2004-04-22

    Applicant: Robert Wood

    Inventor： Robert Wood

    IPC: B64C244/11

    CPC classification number: B64C39/028 ,  B64C33/02 ,  B64C2201/025

    Abstract: A drive assembly for a wing of a micromechanical flying insect. The drive assembly comprises a honey comb structure. A method for flying a micromechanical flying insect comprising moving a wing with a drive assembly having a stiffness to weight ratio greater than about 16×1010 N/mKg.

    Abstract translation: 用于微机械飞行昆虫机翼的驱动组件。 驱动组件包括蜂巢结构。 一种用于飞行微机械飞行昆虫的方法，包括用具有大于约16×10 10 N / mKg的刚度重量比的驱动组件移动机翼。

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