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    High performance ‘X’-configuration airplane for storage and launch from a tubular container
    311.
    发明授权
    High performance ‘X’-configuration airplane for storage and launch from a tubular container 有权
    高性能“X”型飞机用于从管状容器存储和发射

    公开(公告)号：US08444082B1

    公开(公告)日：2013-05-21

    申请号：US12859639

    申请日：2010-08-19

    Applicant: Richard J Foch

    Inventor： Richard J Foch

    IPC: B64C3/56

    CPC classification number: B64C3/10 ,  B64C23/072 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  Y02T50/12 ,  Y02T50/164

    Abstract: An air vehicle can be folded into or unfolded from a compact tubular storage container without assembly or disassembly of the air vehicle. The air vehicle includes a fuselage, two aerodynamic surfaces rotatably mounted on the fuselage along a common axis with at least one pivot mechanism, and at least one spring mechanism configured to deploy the aerodynamic surfaces so they extend outwardly from the body. In a stowed configuration, both aerodynamic surfaces are parallel to the fuselage for stowage of the aircraft in a container. Each aerodynamic surface has a winglet located at an outer edge of the tail portion of the aerodynamic surface, and a rudder on each winglet. The aircraft does not require a vertical stabilizer or rudder system on the fuselage. An outer backward-swept wing portion can be unfolded from the outer edge of each aerodynamic surface to increase the wing aspect ratio.

    Abstract translation: 空中交通工具可以从紧凑的管状存储容器折叠进入或展开，而不需要组装或拆卸空中交通工具。 机动车辆包括机身，具有至少一个枢转机构的共同轴线可旋转地安装在机身上的两个空气动力学表面，以及至少一个弹簧机构，其构造成展开空气动力学表面，使得它们从主体向外延伸。 在收起的构造中，两个空气动力学表面平行于机身，用于将飞行器存储在容器中。 每个空气动力学表面具有位于空气动力学表面的尾部的外边缘处的小翼和在每个小翼上的舵。 飞机在机身上不需要垂直稳定器或方向舵系统。 外侧后掠翼部分可以从每个空气动力学表面的外边缘展开，以增加机翼纵横比。

    Unmanned air vehicle
    314.
    发明授权
    Unmanned air vehicle 失效
    无人机

    公开(公告)号：US08146855B2

    公开(公告)日：2012-04-03

    申请号：US12230638

    申请日：2008-09-03

    Applicant: Anvar Ismailov

    Inventor： Anvar Ismailov

    IPC: B64C3/56

    CPC classification number: F42B10/64 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  F42B10/14

    Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

    Abstract translation: 用于军事，陆上安全等操作的无人驾驶飞行器包括设置有可折叠翼的机身，其具有前缘翼片和后缘副翼，其可以在发射时上升操作以控制翼折叠的飞行图案，翼部署成 在适当的时候打开展开位置。 车辆被容纳在发射的荚内，并且提供着陆甲板以在车辆返回陆地时减速和阻止车辆。

    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    315.
    发明申请
    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE 有权
    用于远程操作的无人驾驶航空器报警系统和设备 - 带便携式射频透明发射管的超级发射器

    公开(公告)号：US20120001020A1

    公开(公告)日：2012-01-05

    申请号：US13234044

    申请日：2011-09-15

    Applicant: Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

    Inventor： Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

    IPC: B64F1/04

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

    Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

    Abstract translation: 一种无人驾驶飞行器（UAV）发射管，其包括被配置为将UAV接合在由内壁限定的发射器体积内的拴系的艉板，所述拴系的突出部的尺寸被设计成在内壁处提供压力密封并且系在内壁上，以及 其中所述系留式破碎器是中空的，其具有朝向高压容积的开口端，并且连接在所述破坏物的中空部内并且附接到保持高压容积的内壁或附接到内底壁的内壁的系绳。 一种包括通信节点和发射器的系统，其包括处于预发射状态的无人驾驶飞行器（UAV），其被配置为接收并响应来自所述通信节点的命令输入。

    COMBINED SUBMERSIBLE VESSEL AND UNMANNED AERIAL VEHICLE
    316.
    发明申请
    COMBINED SUBMERSIBLE VESSEL AND UNMANNED AERIAL VEHICLE 审中-公开
    组合的不合格船只和无人驾驶的航空器

    公开(公告)号：US20110226174A1

    公开(公告)日：2011-09-22

    申请号：US12484557

    申请日：2009-06-15

    Applicant: ROBERT PARKS

    Inventor： ROBERT PARKS

    IPC: B63G8/00 ,  B63G8/08

    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 coupled to the body structure, at least one vertical stabilizer structure coupled to the body structure, and at least one horizontal stabilizer structure coupled to the body 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，联接到主体结构的至少一个翼结构，联接到主体结构的至少一个垂直稳定器结构，以及耦合到主体结构的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。

    MORPHING AIRCRAFT
    317.
    发明申请
    MORPHING AIRCRAFT 有权
    MORPHING飞机

    公开(公告)号：US20110155840A1

    公开(公告)日：2011-06-30

    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 ,  B64C13/24 ,  B64C3/56 ,  B64C5/12 ,  B64C5/06 ,  B64C11/00 ,  G09F3/00 ,  B64C27/04 ,  B64C27/50

    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

    Unmanned Aerial Surveillance Device
    320.
    发明申请
    Unmanned Aerial Surveillance Device 审中-公开
    无人机空中监控装置

    公开(公告)号：US20100282897A1

    公开(公告)日：2010-11-11

    申请号：US11464973

    申请日：2006-08-16

    Applicant: Samuel de la Torre

    Inventor： Samuel de la Torre

    IPC: B64C3/56 ,  B64C3/00 ,  G01C21/00 ,  F42B25/00 ,  H04N7/18

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203

    Abstract: An aerial surveillance device is provided, comprising an image capturing device capable of being supported by an airframe structure above the ground. The airframe structure includes a body portion defining a longitudinal axis and configured to support the image-capturing device. A tail portion having control surfaces is operably engaged with the body portion along the axis. Transversely-extending wing portions are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars extending from a spaced-apart disposition at the body portion to a common connection distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

    Abstract translation: 提供了一种空中监视装置，包括能够由地面上方的机身结构支撑的图像捕获装置。 机身结构包括限定纵向轴线并被配置为支撑图像捕获装置的主体部分。 具有控制表面的尾部部分沿着轴线与主体部分可操作地接合。 横向延伸的翼部直接与主体部分接合。 每个翼部分由纵向相对的翼梁限定，纵向相对的翼梁从主体部分处的间隔设置延伸到远离主体部分的公共连接。 翼梁具有在其间延伸的织物以提供机翼表面。 支撑构件沿着空气动力学中心横向于每个翼部的主体部分延伸，以使翼部被张紧和刚化，以便为翼部提供正弧形并形成翼型。

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