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    LAUNCH AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES
    231.
    发明申请
    LAUNCH AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES 有权
    无人驾驶飞机的发射和恢复系统

    公开(公告)号：US20140231585A1

    公开(公告)日：2014-08-21

    申请号：US14010176

    申请日：2013-08-26

    Applicant: Advanced Aerospace Technologies, Inc.

    Inventor： William R. McDonnell

    IPC: B64F1/02 ,  B64C25/68

    CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

    Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

    Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将无人机（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

    UAV launch attachment assembly and launch system
    232.
    发明授权
    UAV launch attachment assembly and launch system 有权
    无人机发射附件组装和发射系统

    公开(公告)号：US08733695B2

    公开(公告)日：2014-05-27

    申请号：US13956225

    申请日：2013-07-31

    Applicant: Arcturus UAV LLC

    Inventor： Andrew B. Robinson

    IPC: B64F1/04

    CPC classification number: B64F1/04 ,  B64C2201/021 ,  B64C2201/084 ,  B64F1/06

    Abstract: A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV.

    Abstract translation: 与包括框架和发射驱动器的UAV发射组件一起使用的UAV附件组件包括基座，UAV支撑件，偏置元件，联接器和保持器。 基座可操作地联接到发射驱动器。 无人机支撑安装在基座上，可放置在垂直折叠和垂直延伸的方向上。 偏置元件使无人机支撑朝向折叠方向偏移。 当UAV支撑处于延伸方向时，联接器将UAV支撑件可释放地耦合到UAV，UAV支撑在处于折叠方向时无UAV。 保持架在启动之前将UAV支撑件保持在垂直延伸的方向，并在发射时释放UAV支撑，使得偏置元件可以使UAV支撑件朝向折叠方向移动并与UAV脱离接合。

    METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT
    233.
    发明申请
    METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT 有权
    自动起飞，检修和维修飞机的方法和装置

    公开(公告)号：US20140124619A1

    公开(公告)日：2014-05-08

    申请号：US13899172

    申请日：2013-05-21

    Applicant: Aerovel Corporation

    Inventor： Brian T. McGeer ,  Andreas H. von Flotow

    IPC: B64F1/02 ,  B64F5/00 ,  B64F1/04 ,  B64F1/12

    CPC classification number: B64F1/12 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64F1/125 ,  B64F1/28 ,  B64F5/00

    Abstract: Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus.

    Abstract translation: 本公开的各种实施例提供了被配置为自动检索，服务和发射飞行器的装置。 为了进行检索，飞机会丢弃加权电缆，并以相对较低的速度将其拉到设备的宽孔中。 在某些情况下，电缆沿着设备的引导表面被拖入并穿过插槽直到其自由端被捕获。 飞机被锚定到设备上，并且被电缆向下拉到插座中。 接收器的导向面调节飞机上探头的位置和方位，引导探头与设备的对接固定装置配合。 一旦交配，飞机将自动关闭并维修。 当需要时，飞机自动启动并进行测试，准备发射，然后释放到自由飞行中。 因此，通过简单，经济的装置实现完整的地面处理循环。

    Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft
    236.
    发明授权
    Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft 有权
    用于自动启动，检索和维护悬停飞机的方法和设备

    公开(公告)号：US08573536B2

    公开(公告)日：2013-11-05

    申请号：US13037436

    申请日：2011-03-01

    Applicant: Brian Theodore McGeer ,  Robert Joseph Heavey ,  Damon Lucas McMillan ,  John William Stafford

    Inventor： Brian Theodore McGeer ,  Robert Joseph Heavey ,  Damon Lucas McMillan ,  John William Stafford

    IPC: B64F1/02 ,  B64F1/04

    CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/182 ,  B64D37/00 ,  B64F5/00

    Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus. It can be used with low risk of damage, and requires only moderate accuracy in manual or automatic flight control.

    Abstract translation: 可以使用适合在小型船舶上使用的设备或具有类似有限空间或不规则运动的基座自动检索，维修和启动能够推力飞行的飞机。 为了检索，飞机坠落系绳，并以相对较低的速度将系绳拉到与水平导轨接触的位置。 将系绳拉过引导件，直到引导件被钩或其他端部执行器捕获。 然后根据需要调整系绳长度，并且飞机在引导件上摆动以悬在倒立的位置。 沿着导轨翻转系绳，然后将飞机带到对接车厢，飞机停在其中，以便维修。 为了发射，托架正直摆动，末端执行器从引导件释放，飞机起飞进入自由飞行。 因此，可以使用简单经济的装置自动完成全面的地面处理循环。 它可以使用低损害风险，并且在手动或自动飞行控制中只需要适度的准确性。

    AIR INTAKE SYSTEM FOR AN AIR VEHICLE
    237.
    发明申请
    AIR INTAKE SYSTEM FOR AN AIR VEHICLE 审中-公开
    用于空气车辆的空气进气系统

    公开(公告)号：US20130284279A1

    公开(公告)日：2013-10-31

    申请号：US13976235

    申请日：2011-11-23

    Applicant: Clifford John Richards

    Inventor： Clifford John Richards

    IPC: B64D33/02

    CPC classification number: B64D33/02 ,  B64C2201/084 ,  B64D2241/00 ,  F02C7/042 ,  F05D2250/411 ,  F05D2250/51 ,  F42B10/32 ,  F42B15/10 ,  Y10T137/0536

    Abstract: A missile comprises a propulsion system, a passageway for delivering air to the propulsion system and a ducting element associated with the passageway. The ducting element has a ducting surface for ducting air into the passageway, and the ducting element is rotatable, about an axis that is aligned, or more preferably co-axial, with the axis of the passageway, from a stowed position in which the ducting surface is received in the passageway, to a deployed position in which the ducting surface protrudes from the passageway to duct air into the passageway.

    Abstract translation: 导弹包括推进系统，用于将空气输送到推进系统的通道和与通道相关联的管道元件。 管道元件具有用于将空气引导到通道中的管道表面，并且管道元件围绕与通道的轴线对准，或更优选地同轴地从收起位置旋转的管道元件，其中管道 表面被容纳在通道中，到达展开位置，其中管道表面从通道突出到管道空气进入通道。

    Systems And Methods For Launching A Folding Aircraft
    239.
    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
    240.
    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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