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    REMOTELY CONTROLLED MICRO/NANOSCALE AERIAL VEHICLE COMPRISING A SYSTEM FOR TRAVELING ON THE GROUND, VERTICAL TAKEOFF, AND LANDING
    25.
    发明申请
    REMOTELY CONTROLLED MICRO/NANOSCALE AERIAL VEHICLE COMPRISING A SYSTEM FOR TRAVELING ON THE GROUND, VERTICAL TAKEOFF, AND LANDING 有权
    远程控制的微型/纳米级空中客车包含在地面，垂直起落和行驶的行驶系统

    公开(公告)号：US20140319266A1

    公开(公告)日：2014-10-30

    申请号：US14008707

    申请日：2012-03-27

    Applicant: Jean-Marc Moschetta ,  Chinnapat Thipyopas

    Inventor： Jean-Marc Moschetta ,  Chinnapat Thipyopas

    IPC: B64C39/02 ,  B64C19/00 ,  B64C25/36

    CPC classification number: B64C39/028 ,  B64C25/36 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/18 ,  B64D45/06

    Abstract: A microscale radio-controlled aerial micro-drone vehicle, having a fixed wing (as opposed to a rotary wing) having a propulsion device the vehicle including wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels being located in front of the center of gravity of the micro-drone, the center of gravity of the micro-drone being located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.

    Abstract translation: 具有具有推进装置的固定翼（相对于旋转翼）的微型无线电遥控的空中微型无人驾驶车辆，该车辆包括用于在地面上行驶的车轮，其附接到翼的一部分的侧端 。 车轮的旋转轴线Y1位于微型无人驾驶飞机重心的前方，微型无人机的重心位于微型无人机的空气动力学中心的前方。 车轮的旋转轴线Y1与推进装置的推力轴线对准，车轮的尺寸使其半径D / 2大于车轮的旋转轴线Y1和机翼的后缘之间的距离 。

    Hydrogen powered aircraft
    26.
    发明授权
    Hydrogen powered aircraft 有权
    氢动力飞机

    公开(公告)号：US08308106B2

    公开(公告)日：2012-11-13

    申请号：US13200466

    申请日：2011-09-23

    Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

    Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

    IPC: B64D27/24 ,  B64D27/00

    CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

    Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere.

    Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。

    System and method for transferring airplanes
    27.
    发明授权
    System and method for transferring airplanes 有权
    飞机转运系统及方法

    公开(公告)号：US07975959B2

    公开(公告)日：2011-07-12

    申请号：US11528647

    申请日：2006-09-28

    Applicant: Arie Perry ,  Ran Braier

    Inventor： Arie Perry ,  Ran Braier

    IPC: B64C25/50

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/187 ,  B64F1/00 ,  Y02T50/82

    Abstract: A method for transferring airplanes and an unmanned airplane transfer system. The airplane transferring system includes: receiving a transfer signal responsive of a movement of an airplane control component; and transferring an airplane, by an unmanned airplane transfer system, in response to the transfer signal.

    Abstract translation: 一种用于转移飞机和无人驾驶飞机转移系统的方法。 飞机传送系统包括：响应飞机控制部件的运动接收传送信号; 并且通过无人驾驶飞行器传送系统来响应于传送信号传送飞机。

    CARGO AIRCRAFT
    28.
    发明申请
    CARGO AIRCRAFT 有权
    货运飞机

    公开(公告)号：US20090026314A1

    公开(公告)日：2009-01-29

    申请号：US11782850

    申请日：2007-07-25

    Applicant: ELIE HELOU, JR.

    Inventor： ELIE HELOU, JR.

    IPC: B64C1/20 ,  B64C1/00

    CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

    Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

    Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

    Small-sized radio-controlled flying device
    30.
    发明授权
    Small-sized radio-controlled flying device 失效
    小型无线电遥控飞行装置

    公开(公告)号：US06676084B2

    公开(公告)日：2004-01-13

    申请号：US10168588

    申请日：2002-06-24

    Applicant: Jean Asseline ,  George De Noni

    Inventor： Jean Asseline ,  George De Noni

    IPC: B64D1734

    CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

    Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires. The wings (13) are a caisson-type supple parachute and are connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

    Abstract translation: 由具有推进式螺旋桨（19）的热力发动机（20）推进的用于遥感的小型无线电控制飞行装置，该装置能够以35Km / h的最大速度短时起飞和着陆并飞行。 该装置包括荚和翼，荚（1）是刚性三轮车，可通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6）。 底座是焊接的单件元件，包括发动机，螺旋桨，油箱和无线电控制。 顶点是焊接的单件元件。 下平面和两个横向平面包括组装在基部和顶点的翼梁（11,12）。 下平面在其三个端角处包括两个后轮（8）和前轮（9），前轮设置成朝向顶点的前部突出，并且轮是低压轮胎。 机翼（13）是沉箱式柔软的降落伞，并且通过两个前吊索（17）和作用在两个翼片/副翼上的两个制动吊索（18）以可调节的方式连接到吊舱。

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