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    Combined submersible vessel and unmanned aerial vehicle
    21.
    发明授权
    Combined submersible vessel and unmanned aerial vehicle 有权
    组合潜艇和无人机

    公开(公告)号：US09296270B2

    公开(公告)日：2016-03-29

    申请号：US13765144

    申请日：2013-02-12

    Applicant: Aurora Flight Sciences Corporation

    Inventor： Robert Parks ,  Adam Woodworth ,  Tom Vaneck ,  Justin McClellan

    IPC: B60F5/02 ,  B64C39/02 ,  F42B15/20

    CPC classification number: B64C37/00 ,  B60F5/02 ,  B63G8/001 ,  B63G8/08 ,  B63G2008/005 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  F42B15/20

    Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

    Abstract translation: 组合潜艇和无人驾驶飞行器优选地包括主体结构，至少一个翼结构，至少一个垂直稳定器结构和至少一个水平稳定器结构。 推进系统联接到车身结构并且被构造成在空中飞行和水下操作中推进飞行潜艇。 优选地，推进系统包括电动机，耦合到电动机并被配置为接收由电动机产生的电力并提供可变输出功率的变速箱;耦合到齿轮箱并被配置为传递由变速箱提供的可变输出功率的驱动轴， 以及联接到所述驱动轴并被配置为接受从所述驱动轴传递到其的动力的螺旋桨。 螺旋桨进一步构造成在空中环境和水下环境中旋转和推进飞行潜艇。

    Multi-Task Frisbee-Umbrella
    22.
    发明申请
    Multi-Task Frisbee-Umbrella 审中-公开
    多任务飞盘伞

    公开(公告)号：US20150360777A1

    公开(公告)日：2015-12-17

    申请号：US14698803

    申请日：2015-04-28

    Applicant: Sima MOTTALE

    Inventor： Sima MOTTALE

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C27/04 ,  B64C27/10 ,  B64C39/08 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/146 ,  B64D47/08 ,  Y02T50/55

    Abstract: The present invention discloses an unmanned aerial vehicle capable of transforming its shape, comprising a) a control apparatus b) one or more propellers being fixed to the control apparatus, c) a multitude of flaps which are foldable reversibly from an open to a closed position, wherein the flaps provide i) in open position about a disc shape which is about in parallel to the plane of the rotating propeller, and ii) in closed position a shuttlecock shape, wherein, at least one of the flaps comprises a battery recharge element, such as a solar panel, photovoltaic element or elements, an electromagnetic harvesting element, a thermoelectric generator and/or a solar thermoelectric generator. The present invention relates also to a rotating disc being suitable for the vehicle, as well as the use of the vehicle and the rotating disc.

    Abstract translation: 本发明公开了一种能够转换其形状的无人驾驶飞行器，包括：a）控制装置; b）固定在控制装置上的一个或多个螺旋桨，c）多个襟翼，其可从开放到闭合位置可逆地折叠 ，其中所述翼片提供i）围绕与所述旋转螺旋桨的平面平行的盘形状的打开位置，以及ii）在关闭位置中的羽毛球形状，其中所述翼片中的至少一个包括电池再充电元件 ，例如太阳能电池板，光电元件或元件，电磁收集元件，热电发电机和/或太阳能热电发电机。 本发明还涉及适用于车辆的旋转盘以及车辆和旋转盘的使用。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH VARIABLE WING GEOMETRY
    24.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH VARIABLE WING GEOMETRY 有权
    垂直起落架和可变轨迹飞机

    公开(公告)号：US20150284075A1

    公开(公告)日：2015-10-08

    申请号：US14243540

    申请日：2014-04-02

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Mark R. Alber

    IPC: B64C27/22 ,  B64C3/42 ,  B64C39/02 ,  B64C29/00 ,  B64C25/10

    CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

    Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, inboard wings extending from opposite sides of the fuselage to define a support plane and engine nacelles disposed along the wings. Each of the wings includes ground alighting elements and a variable geometry such that a portion of the ground alighting elements are alignable with the support plane during in-flight conditions and displaceable from the support plane.

    Abstract translation: 提供垂直起飞和降落（VTOL）飞机，并包括机身，内侧翅膀从机身的相对侧延伸，以限定沿机翼设置的支撑平面和发动机舱。 每个翼包括地面下落元件和可变几何形状，使得地面下落元件的一部分在飞行状态期间与支撑平面对准并且可从支撑平面移位。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    25.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
    垂直起落架和飞机

    公开(公告)号：US20150102157A1

    公开(公告)日：2015-04-16

    申请号：US14460013

    申请日：2014-08-14

    Applicant: SWIFT ENGINEERING, INC.

    Inventor： Robert Godlasky ,  Nate Ogawa ,  Andrew Streett

    IPC: B64C29/00 ,  B64C3/56 ,  B64D27/02

    CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

    Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

    Abstract translation: 垂直起落飞行器包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持在固定方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到达基本水平的飞行路径的路径。

    Supersonic hovering air vehicle
    26.
    发明授权
    Supersonic hovering air vehicle 有权
    超音速悬停飞行器

    公开(公告)号：US09004393B2

    公开(公告)日：2015-04-14

    申请号：US13279827

    申请日：2011-10-24

    Applicant: Ronald M. Barrett-Gonzales

    Inventor： Ronald M. Barrett-Gonzales

    IPC: B64C27/24 ,  B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C27/24 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/102

    Abstract: Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds.

    Abstract translation: 本发明的实施例包括能够持续地面效应悬停飞行和持续的超音速飞行的飞机。 至少一些实施例包括由发动机驱动的两个翼，以在盘旋时反向旋转，并且在以跨音速和超音速飞行的同时不旋转和扫掠。 其它实施例包括两个旋转翼，其在悬停期间在旋转翼盘内产生每100英寸/ ft 2以下的每单位面积的力。 另外的实施例包括具有旋转翼的车辆，其可以增加俯仰以加速飞行器，将翼的弦线与气流对准，并且扫掠翼。 另外的实施例包括在悬停期间为未被引导的旋转翼提供动力的动力装置，并且与翼分离，以超音速推进飞行器。

    Systems and methods for launching a folding aircraft
    27.
    发明授权
    Systems and methods for launching a folding aircraft 有权
    发射折叠飞机的系统和方法

    公开(公告)号：US08894007B2

    公开(公告)日：2014-11-25

    申请号：US13558728

    申请日：2012-07-26

    Applicant: Andrew McComas ,  Jon Clark

    Inventor： Andrew McComas ,  Jon Clark

    IPC: B64F1/04 ,  B64F1/06

    CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/102

    Abstract: A canister system for a folding aircraft may include a canister housing and a launch mechanism powered by one or more compression springs. A hand-operated drive mechanism may rotate a plurality of threaded rods to drive the launch mechanism from a released position to a cocked position, in which mechanical energy is stored in the springs. A latch mechanism may capture the launch mechanism in the cocked position. The canister may include a housing for receiving and storing the aircraft when the launch mechanism is in the cocked position. A trigger mechanism may release the latch mechanism, permitting the energy stored in the compressed springs to drive the launch mechanism toward the released position and propel the aircraft from the housing at launch velocity.

    Abstract translation: 用于折叠飞机的罐系统可以包括罐壳体和由一个或多个压缩弹簧驱动的发射机构。 手动驱动机构可以旋转多个螺杆，以将发射机构从释放位置驱动到起动位置，其中机械能存储在弹簧中。 闩锁机构可以捕捉发动机构处于俯视位置。 罐可以包括用于在发射机构处于起动位置时接收和存储飞行器的壳体。 触发机构可以释放闩锁机构，允许存储在压缩弹簧中的能量将发射机构驱动到释放位置，并以发射速度将飞行器从壳体推进。

    Aircraft wing with knuckled rib structure
    28.
    发明授权
    Aircraft wing with knuckled rib structure 有权
    飞机机翼带指节肋骨结构

    公开(公告)号：US08783604B2

    公开(公告)日：2014-07-22

    申请号：US13278477

    申请日：2011-10-21

    Applicant: Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

    Inventor： Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

    IPC: B64C3/56

    CPC classification number: B64C3/56 ,  B64C2201/102

    Abstract: An aircraft wing has hinged ribs, and a skin covering the ribs. The ribs each include plural rib sections, array from the leading edge of the wing, to the trailing edge of the wing, and a lock to hold the rib sections together in a deployed state or condition. The wings are initially in a stowed state, with the ribs and the rib sections having a curved chord, and deploy to the deployed state, in which the ribs have a straightened chord that defines an airfoil state. The wing may have foam material between the ribs to allow the wings to expand in the wingspan direction, for instance after the ribs have been placed in the deployed state.

    Abstract translation: 飞机机翼有铰链肋骨和覆盖肋骨的皮肤。 肋条各自包括从翼的前缘到翼的后缘阵列的多个肋部，以及在展开状态或状态下将肋部保持在一起的锁。 翼部最初处于收起状态，肋和肋部具有弯曲的弦，并且部署到展开状态，其中肋具有限定翼型状态的矫直弦。 机翼可以在肋之间具有泡沫材料，以允许翼在翼展方向上膨胀，例如在肋已经处于展开状态之后。

    Inflatable airfoil system having reduced radar and infrared observability
    29.
    发明授权
    Inflatable airfoil system having reduced radar and infrared observability 有权
    充气翼型系统具有降低的雷达和红外可观测性

    公开(公告)号：US08727280B1

    公开(公告)日：2014-05-20

    申请号：US12633272

    申请日：2009-12-08

    Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    IPC: B64C1/00 ,  B64C3/00 ,  B64C5/00

    CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

    Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

    Abstract translation: 一种用于操作翼型系统的方法和装置。 可能产生气体。 气体可以被送入包括可膨胀的气翼和截面的充气翼型系统中。 可膨胀翼型件可以具有内端和外端，其中可膨胀翼型可以由许多基本上通过电磁波通过可充气翼型的材料构成。 该部分可以具有多个开口，其中可充气翼片的内端可以与该部分相关联。 该部分可以被配置为与机身相关联。 开口的数量可以被配置为提供与可膨胀翼型件的内部的通信。 具有开口数量的部分可以被配置为减少遇到该部分的电磁波的反射。

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