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    METHODS FOR OPERATING AN AIR VEHICLE
    31.
    发明申请
    METHODS FOR OPERATING AN AIR VEHICLE 审中-公开
    运行空气车辆的方法

    公开(公告)号：US20160347451A1

    公开(公告)日：2016-12-01

    申请号：US15113368

    申请日：2015-01-27

    Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

    Inventor： Michael Shepshelovich ,  Danny Abramov ,  Yonatan Klein

    IPC: B64C39/02 ,  B64D43/02 ,  B64C15/12 ,  B64C3/14

    CPC classification number: B64C39/024 ,  B64C3/14 ,  B64C13/16 ,  B64C15/12 ,  B64C29/00 ,  B64C2201/084 ,  B64C2201/104 ,  B64D43/02 ,  Y02T50/12

    Abstract: Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated flow over the fixed wings and conditions of attached flow over the fixed wings. Such methods also include the step of using the operating map for guidance, causing the air vehicle to operate at least within a low Reynolds numbers range corresponding to the operating map, such as to avoid or minimize risk of causing the air vehicle to operate at conditions of separated flow over the fixed wings.

    Abstract translation: 提供了用于操作具有固定翼的机动车辆的方法。 这样的方法包括提供与固定翼相关的迎角与雷诺数相关的操作图的步骤，包括在固定翼上分离的流动的条件以及固定翼上附着流的条件。 这种方法还包括使用操作图来进行引导的步骤，使得空中飞行器至少在对应于操作图的低雷诺数范围内操作，以避免或最小化导致飞行器在条件下操作的风险 分离流过固定翼。

    Airborne Surveillance Kite
    34.
    发明申请
    Airborne Surveillance Kite 审中-公开
    机载监控风筝

    公开(公告)号：US20160207626A1

    公开(公告)日：2016-07-21

    申请号：US15002612

    申请日：2016-01-21

    Applicant: Glen R. Bailey

    Inventor： Glen R. Bailey

    IPC: B64C39/02 ,  B64F3/02 ,  B64C3/00 ,  B64C27/08 ,  B64D17/00 ,  B64D27/24 ,  B64C27/06

    CPC classification number: B64C39/022 ,  B64C31/06 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/148

    Abstract: A deployable airborne surveillance kite for flying in a wind over a surface includes a wing, a tail, and a spar coupling the wing to the tail. The kite further includes a thrust rotor mounted to the kite in a vertical orientation for providing vertical lift to the kite. A tether assembly extends from the kite to the surface and couples the kite to the surface providing downward resistance in opposition to the vertical lift provided by the thrust rotor.

    Abstract translation: 用于在表面上风中飞行的可部署的机载监视风筝包括机翼，尾翼和将翼连接到尾部的翼梁。 风筝还包括以垂直方向安装到风筝上的推力转子，以提供对风筝的垂直升力。 系绳组件从风筝延伸到表面并将风筝结合到表面，提供与由推力转子提供的垂直升力相反的向下的阻力。

    Aircraft Capable of Vertical Take-Off
    35.
    发明申请
    Aircraft Capable of Vertical Take-Off 审中-公开
    飞机能够垂直起飞

    公开(公告)号：US20160207625A1

    公开(公告)日：2016-07-21

    申请号：US14915101

    申请日：2014-08-29

    Applicant: Airbus Defence and Space GmbH ,  STEUBBEUS FLUGZEUG- UND LEICHTBAU GMBH

    Inventor： Michael JUDAS ,  Friederike STRATENBERG ,  Jan VAN TOOR ,  Werner SCHOLZ ,  Berthold KARRAIS ,  Wolfgang STANGL

    IPC: B64C29/00 ,  B64C27/08 ,  B64C27/473 ,  B64C3/38 ,  B64C5/08 ,  B64D27/02 ,  B64D27/24 ,  B64C39/02 ,  B64C39/08

    CPC classification number: B64C29/0025 ,  B64C3/38 ,  B64C5/08 ,  B64C27/08 ,  B64C27/473 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D27/24 ,  B64D2027/026

    Abstract: The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive.

    Abstract translation: 本发明涉及一种能够垂直起飞和着陆的飞机，其可以悬停并且以高巡航速度水平飞行。 飞行器具有支撑结构，翼结构，至少三个，优选至少四个提升转子和至少一个推力驱动。 机翼结构被设计成在水平运动期间为飞机产生提升力。 为了实现这一点，翼结构具有至少一个主平面，其具有产生动态升力的轮廓。 机翼结构优选地被设计为串联翼结构。 每个提升转子固定在支撑结构上，具有螺旋桨，并被设计成通过螺旋桨的旋转而产生用于飞行器的提升力，所述力作用在垂直方向上。 推力驱动器被设计成在支撑结构上产生推力，所述力在水平方向上作用。 提升转子可以具有简单的结构，例如它们可以具有简单的刚性推进器，并且可以通过简单地控制速度来简单地控制飞机的垂直起飞或悬停 提升转子。 由于额外的水平作用推力驱动，可以实现高巡航速度。

    Dual mode flight vehicle
    37.
    发明授权
    Dual mode flight vehicle 有权
    双模飞行器

    公开(公告)号：US09266609B1

    公开(公告)日：2016-02-23

    申请号：US14518770

    申请日：2014-10-20

    Applicant: Insitu, Inc.

    Inventor： Peter J. Kunz

    IPC: B64C27/22 ,  B64C29/00

    CPC classification number: B64C29/0008 ,  B64C17/04 ,  B64C29/0091 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104

    Abstract: A fixed wing flight vehicle has wing, a center-mounted propulsion unit and a pod that is moveable between a center of the wing and a displaced position at or near one end of the wing. When the pod is at or near the center of the wing, that is, having a center of mass at or near a thrust vector of the propulsion unit, the flight vehicle flies with the characteristics of a regular fixed wing aircraft. However, when the pod is translated to the position at or near an end of the wing, an overall center of mass of the flight vehicle is substantially offset from the thrust vector of the propulsion unit. This causes the flight vehicle to spin like a samara, e.g., a maple seed, so that the flight vehicle can take off or land in a very limited space, much like a helicopter.

    Abstract translation: 固定翼飞行器具有机翼，中心安装的推进单元和荚，其可以在翼的中心和机翼的一端或附近的位移位置之间移动。 当荚在机翼的中心处或附近时，即具有在推进单元的推力矢量处或附近的质心时，飞行器具有常规固定翼飞机的特征。 然而，当货舱被翻译到机翼末端或其附近的位置时，飞行车辆的整体质心基本上偏离推进装置的推力矢量。 这使得飞行车辆像萨马拉一样旋转，例如枫树种子，使得飞行车辆能够在非常有限的空间中起飞或着陆，就像直升机一样。

    REMOTELY OR AUTONOMOUSLY PILOTED REDUCED SIZE AIRCRAFT WITH VERTICAL TAKE-OFF AND LANDING CAPABILITIES
    38.
    发明申请
    REMOTELY OR AUTONOMOUSLY PILOTED REDUCED SIZE AIRCRAFT WITH VERTICAL TAKE-OFF AND LANDING CAPABILITIES 审中-公开
    远程或自动直升机减少尺寸的飞机具有垂直起落架能力

    公开(公告)号：US20150225079A1

    公开(公告)日：2015-08-13

    申请号：US14054080

    申请日：2013-10-15

    Applicant: Douglas L. Starck ,  Errica M. Starck

    Inventor： Douglas L. Starck ,  Errica M. Starck

    IPC: B64C29/00 ,  B64C39/10 ,  B64D27/16

    CPC classification number: B64C39/10 ,  B64C29/0066 ,  B64C39/024 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/22 ,  B64D27/16 ,  Y02T50/12 ,  Y02T50/44

    Abstract: An aircraft having a vertical take-off and landing (“VTOL”) propulsion system aircraft, smaller than a standard manned aircraft and remotely or autonomously piloted. The aircraft comprises a symmetrical airfoil shape for the center body section that consists of ribs and spars maintaining an open area in the center. Situated within the open area of the center of the aircraft resides a duct system consisting of a ducted fan and five outlet vents. The main outlet vent functions as the exhaust exiting the aft portion of the aircraft, with the remaining four ducts used for the VTOL capabilities exiting the underside of the aircraft. The aircraft can have a range of wingspan, which can be scaled to satisfy needs and requirements, with a blended wing body that incorporates the inlet and duct system.

    Abstract translation: 具有垂直起飞和着陆（“VTOL”）推进系统飞机的飞机，小于标准载人飞机，远程或自主驾驶。 该飞行器包括对称的翼型形状，用于中心体部分，其由在中心保持开放区域的肋和翼梁组成。 位于飞机中心开放区域内的管道系统由管道风扇和五个出风孔组成。 主出口排气口作为离开飞机尾部的排气口，剩余的四个管道用于从飞机底面离开的垂直起降能力。 飞机可以具有一系列的翼展，其可以通过混合的翼体结合入口和管道系统而被缩放以满足需要和要求。

    REMOTELY CONTROLLED MICRO/NANOSCALE AERIAL VEHICLE COMPRISING A SYSTEM FOR TRAVELING ON THE GROUND, VERTICAL TAKEOFF, AND LANDING
    40.
    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 。

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