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    MICRO HYBRID GENERATOR SYSTEM DRONE
    42.
    发明申请
    MICRO HYBRID GENERATOR SYSTEM DRONE 有权
    微型混合发电机系统

    公开(公告)号：US20160137304A1

    公开(公告)日：2016-05-19

    申请号：US14942600

    申请日：2015-11-16

    Applicant: TOP FLIGHT TECHNOLOGIES, INC.

    Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

    IPC: B64D27/02 ,  B64D33/08 ,  B64C39/02 ,  B64C27/00 ,  B64C27/08

    CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

    Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

    Abstract translation: 一种包括至少一个转子电动机的无人驾驶飞行器。 转子电机由微型混合发电系统供电。 微型混合发电机系统包括被配置为向至少一个转子电动机提供电力的可再充电电池，被配置为产生机械功率的小型发动机，耦合到小型发动机的发电机电动机，并且被配置为使用由 小型发动机，桥式整流器，被配置为将由发电电动机产生的交流电力转换为直流电力，并将DC电力提供给可再充电电池和至少一个转子电动机中的一个或两者;以及电子控制单元， 所述小型发动机的节气门至少部分地基于至少一个负载的功率需求，所述至少一个负载包括所述至少一个转子电动机。

    ROTARY ENGINE
    44.
    发明申请
    ROTARY ENGINE 审中-公开
    旋转发动机

    公开(公告)号：US20130183183A1

    公开(公告)日：2013-07-18

    申请号：US13733138

    申请日：2013-01-02

    Applicant: Manousos Pattakos ,  Argyro Pattakou ,  Emmanouel Pattakos

    Inventor： Manousos Pattakos ,  Argyro Pattakou ,  Emmanouel Pattakos

    IPC: F01C21/00

    CPC classification number: F01C21/008 ,  B64C27/08 ,  B64C39/026 ,  B64C2201/024 ,  B64C2201/044 ,  F01C1/063 ,  F02B53/00 ,  F02B2075/027

    Abstract: A “cat and mouse” rotary engine/pump comprising two inclined power shafts at the two ends of the rotor-pistons. Each power shaft connects to both rotor-pistons by concentric crosses. Either piston can be suspended from the bearings of the inclined shafts indirectly, through the inclined shafts and the crosses, avoiding any touching with the other piston and the casing. The arrangement improves the balance of the engine, rids the bearings of the rotor-pistons from heavy idle loads, allows lighter and more robust structure. The power is shared between the two counter-rotating shafts. The arrangement fits to divided load applications, like portable flyers, REM.

    Abstract translation: 一个“猫鼠”旋转发动机/泵，在转子活塞的两端包括两个倾斜的动力轴。 每个动力轴通过同心十字架连接到两个转子活塞。 活塞可以通过倾斜的轴和十字架间接悬挂在倾斜轴的轴承之间，避免与另一个活塞和壳体接触。 该装置改善了发动机的平衡，使转子 - 活塞的轴承处于重型怠速负载状态，允许更轻更坚固的结构。 在两个反向旋转轴之间共享电力。 该装置适用于分散负载应用，如便携式传单，REM。

    Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft
    45.
    发明申请
    Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft 审中-公开
    无人机并联混合动力推进系统

    公开(公告)号：US20120209456A1

    公开(公告)日：2012-08-16

    申请号：US13396760

    申请日：2012-02-15

    Applicant: Frederick G. Harmon ,  Ryan M. Hiserote ,  Matthew D. Rippl ,  Joseph K. Ausserer

    Inventor： Frederick G. Harmon ,  Ryan M. Hiserote ,  Matthew D. Rippl ,  Joseph K. Ausserer

    IPC: B64C19/02

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64D35/08 ,  B64D2027/026 ,  Y02T50/64

    Abstract: An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.

    Abstract translation: 提供了一种无人驾驶飞行器，其包括安装在机身上的机身和并联混合动力推进系统。 并联混合动力推进系统包括内燃机和电动马达。 混合控制器被配置为控制内燃机和电动马达。 螺旋桨连接到机械连杆。 机械连杆将内燃机和电动马达连接到螺旋桨以驱动螺旋桨。 备用的无人驾驶飞行器包括由电动机驱动的第二螺旋桨。 在这种替代的无人驾驶飞行器中，内燃机与电动机分离。

    Payload quick release for an aerial system
    46.
    发明授权
    Payload quick release for an aerial system 失效
    空中系统的有效载荷快速释放

    公开(公告)号：US08162263B2

    公开(公告)日：2012-04-24

    申请号：US12415463

    申请日：2009-03-31

    Applicant: Kimberly Wong ,  Armand Losinski

    Inventor： Kimberly Wong ,  Armand Losinski

    IPC: B64D1/12

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64D1/02 ,  F16B21/02

    Abstract: A payload quick release mechanism for an unmanned aerial vehicle is provided. This mechanism is affixed to a structure on the unmanned aerial vehicle, and allows for quick attachment and removal of a payload from the unmanned aerial vehicle. The attachment device includes a body with a perimeter and a plurality of arms that extend from the body perimeter. Each arm includes an indented section, within which a tab extending from the payload top may be placed. When the payload tab rests within the indented section, the payload is prevented from translation and is attached to the mechanism.

    Abstract translation: 提供了一种用于无人机的有效载荷快速释放机构。 该机构固定在无人驾驶飞行器上的结构上，并允许从无人驾驶飞行器快速附接和移除有效载荷。 附接装置包括具有周边的主体和从主体周边延伸的多个臂。 每个臂包括一个缩进的部分，其中可以放置从有效载荷顶部延伸的突片。 当有效载荷标签搁置在缩进部分内时，防止有效载荷平移并附着在机构上。

    Ring generator
    48.
    发明授权
    Ring generator 失效
    环形发电机

    公开(公告)号：US07728446B2

    公开(公告)日：2010-06-01

    申请号：US10560147

    申请日：2004-06-25

    Applicant: Peter Hofbauer ,  Patrick McCleer

    Inventor： Peter Hofbauer ,  Patrick McCleer

    IPC: F02B63/04 ,  F03D9/00 ,  H02P9/04

    CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/162 ,  F02B61/04 ,  F02B75/24 ,  F03G7/08 ,  H02K7/183 ,  H02K7/1884 ,  Y02E10/725

    Abstract: The present invention is a rotary device that may be adapted for use as a propeller assembly and electrical generator for aerial vehicles or other vehicles intended for fluid media. In one example, the device includes a ring assembly having a plurality of centrally linked blades coupled to a rotatable common hub. Rotary motion of the ring assembly is facilitated by coupling it to an opposed cylinder, opposed piston, internal combustion. The ring assembly includes components of an electrical power generating system so that electrical power is produced from the rotation of the ring assembly.

    Abstract translation: 本发明是一种旋转装置，其可以适用于用作飞行器或用于流体介质的其它车辆的螺旋桨组件和发电机。 在一个示例中，该装置包括环组件，其具有联接到可旋转公共毂的多个中心连接的叶片。 环组件的旋转运动通过将其联接到相对的气缸，相对的活塞，内燃来实现。 环组件包括发电系统的部件，使得从环组件的旋转产生电力。

    Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and breaking subsequent grip motion
    49.
    发明授权
    Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and breaking subsequent grip motion 有权
    用于发射无人机的方法和装置，包括在发射期间可释放地夹持飞行器并且打破随后的抓地力

    公开(公告)号：US07360741B2

    公开(公告)日：2008-04-22

    申请号：US11603815

    申请日：2006-11-21

    Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

    Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

    IPC: B64F1/06

    CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

    Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

    Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有与飞行器接触的至少一个抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

    Wireless-controlled airplane
    50.
    发明申请
    Wireless-controlled airplane 失效
    无线控制的飞机

    公开(公告)号：US20070084971A1

    公开(公告)日：2007-04-19

    申请号：US11252185

    申请日：2005-10-18

    Applicant: Haru Miyake

    Inventor： Haru Miyake

    IPC: B64C13/20

    CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

    Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

    Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

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