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    Collapsible wing assembly
    141.
    发明授权
    Collapsible wing assembly 有权
    可折叠翼组件

    公开(公告)号：US09150301B2

    公开(公告)日：2015-10-06

    申请号：US13710323

    申请日：2012-12-10

    Applicant: SINGAPORE TECHNOLOGIES AEROSPACE LTD

    Inventor： Yong Wee Liu ,  Hian Beng Kek

    IPC: B64C3/56 ,  B64C39/02

    CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102

    Abstract: Disclosed herein is a collapsible wing assembly of an unmanned aerial vehicle (UAV) and a method of locking and unlocking the collapsible wing assembly of an unmanned aerial vehicle (UAV). The collapsible wing assembly comprising a center wing adapted to be attached to the fuselage; and a pair of outboard wings, wherein each of the outboard edges of the center wing comprises a first attachment structure, and each of the inboard edges of the outboard wings comprises a second attachment structure, wherein the first attachment structure is operable to engage with the second attachment structure and displace the second attachment structure to a captive position towards the trailing edge of the center wing.

    Abstract translation: 本文公开了一种无人飞行器（UAV）的可折叠翼组件以及锁定和解锁无人机（UAV）的可折叠翼组件的方法。 可折叠翼组件包括适于附接到机身的中心翼; 以及一对外侧翼，其中所述中心翼的所述外侧边缘中的每一个包括第一附接结构，并且所述外侧翼的每个内侧边缘包括第二附接结构，其中所述第一附接结构可操作以与 第二附接结构，并且使第二附接结构朝着中心翼的后缘移动到捕获位置。

    Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles
    144.
    发明授权
    Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles 有权
    在无人驾驶飞行器上部署并致动翼型的机构

    公开(公告)号：US08946607B2

    公开(公告)日：2015-02-03

    申请号：US13324193

    申请日：2011-12-13

    Applicant: Jonathan David Gettinger

    Inventor： Jonathan David Gettinger

    IPC: F42B15/01

    CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C5/12 ,  B64C2201/102

    Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.

    Abstract translation: 部署和控制致动机构被并入具有折叠翼和/或折叠的猫和/或折叠的垂直稳定器的无人驾驶飞行器中。 可以使用相应的四杆过中心机构来部署折叠式鸭子和折叠式垂直稳定器。 可枢转地安装到折叠卡瓦的电梯和可枢转地安装到折叠垂直稳定器的舵可以通过相应的扭转连杆机构来控制。 折叠翼具有相应的翼根，其由相应的气弹簧驱动，以围绕具有控制伺服线路径的翼根轮毂的轴承枢转。

    Folding configuration for air vehicle
    146.
    发明授权
    Folding configuration for air vehicle 有权
    机动车折叠配置

    公开(公告)号：US08899515B2

    公开(公告)日：2014-12-02

    申请号：US13475371

    申请日：2012-05-18

    Applicant: Suneal Guptaa ,  Jeremy Bley

    Inventor： Suneal Guptaa ,  Jeremy Bley

    IPC: B64C3/56

    CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  F42B10/16 ,  Y02T50/14

    Abstract: An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.

    Abstract translation: 一种空中飞行器以及用于折叠用于存储的空中飞行器的方法可以包括机身和连接到机身的机翼。 机翼可以包括彼此相对定位的两个端部，并且机翼可以基本上垂直于机身。 端部中的至少一个可以限定机身和机翼之间的空间。 当机翼围绕机身缠绕时，该空间的大小可以接收机翼的一部分。

    Morphing aircraft
    147.
    发明授权
    Morphing aircraft 有权
    变形飞机

    公开(公告)号：US08888035B2

    公开(公告)日：2014-11-18

    申请号：US13061019

    申请日：2009-08-25

    Applicant: Richard Charles Lind, Jr. ,  Daniel Thurmond Grant ,  David Eaton

    Inventor： Richard Charles Lind, Jr. ,  Daniel Thurmond Grant ,  David Eaton

    IPC: B64C39/02 ,  B64C37/00 ,  B60F3/00 ,  B64C1/00

    CPC classification number: B64C39/024 ,  B60F3/00 ,  B64C37/00 ,  B64C2001/0045 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/203

    Abstract: A morphing aircraft that is achieves multi-modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.

    Abstract translation: 实现多模式位置和伪装用于有效载荷的变形飞机变形飞机包括基本上圆柱形的机身，其包括被配置为具有第一端和第二端的包装容器的形状。一组翼结合到机身。该组 的翼部包括第一位置，其中所述一组翼从机身向外延伸，并且第二位置，其中该组翼向内朝向机身A缩回。尾部联接到圆柱形机身的第二端。尾部包括第一位置 其中尾部从机身向外延伸，而第二位置则是尾部朝向机身向内缩进。螺旋桨安装在机身的第一端。发动机机械地联接到螺旋桨。发动机被封闭在机身内并且动力 螺旋桨

    Systems And Methods For Launching A Folding Aircraft
    149.
    发明申请
    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：US20130026286A1

    公开(公告)日：2013-01-31

    申请号：US13558728

    申请日：2012-07-26

    Applicant: Andrew MCCOMAS ,  Jon CLARK

    Inventor： Andrew MCCOMAS ,  Jon CLARK

    IPC: B64F1/04

    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。

    SUPERSONIC HOVERING AIR VEHICLE
    150.
    发明申请
    SUPERSONIC HOVERING AIR VEHICLE 有权
    超级空中飞行器

    公开(公告)号：US20120097801A1

    公开(公告)日：2012-04-26

    申请号：US13279827

    申请日：2011-10-24

    Applicant: Ronald M. Barrett

    Inventor： Ronald M. Barrett

    IPC: B64C27/24 ,  B64C29/00 ,  B64C27/00 ,  B64C30/00

    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。

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