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    ELECTRIC MOTOR ASSISTED TAKEOFF DEVICE FOR AN AIR VEHICLE
    131.
    发明公开
    ELECTRIC MOTOR ASSISTED TAKEOFF DEVICE FOR AN AIR VEHICLE 有权
    电动机来辅助起动器适用于飞机

    公开(公告)号：EP1963185A2

    公开(公告)日：2008-09-03

    申请号：EP06838485.8

    申请日：2006-11-29

    Applicant: ITT Manufacturing Enterprises, Inc.

    Inventor： PAGE, Gregory S.

    IPC: B64F1/10

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  F42B15/36

    Abstract: A takeoff assist device for an air vehicle, such as an unmanned air vehicle is provided. The device features an electric motor and is much less complex and lighter than takeoff assist devices heretofore known. A body member is shaped to fit to a portion of the air vehicle. The body member defines a housing in which the majority of the components are housed, including the electric motor, a motor controller, an electrical power source and a main controller. A propeller is attached to a shaft of the electric motor outside of the housing and rotates with a shaft of the electric motor. In addition, there is a latch mechanism that removeably attaches the body member to the host air vehicle for takeoff, and then is controlled to release from the air vehicle after it is airborne at a desired airspeed and altitude. The electric motor-driven takeoff assist device can launch an air vehicle with minimal auxiliary equipment and can be remotely controlled to launch from a site at which a takeoff ready vehicle can be left for extended periods of time.

    PARACHUTE RELEASE DEVICE AND METHODS
    132.
    发明公开
    PARACHUTE RELEASE DEVICE AND METHODS 审中-公开
    降落伞释放设备和方法

    公开(公告)号：EP1945508A1

    公开(公告)日：2008-07-23

    申请号：EP05812878.6

    申请日：2005-11-30

    Applicant: BlueBird Aero Systems Ltd.

    Inventor： NADIR, Ronen

    IPC: B64D17/00

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/80

    Abstract: The disclosure provides a parachute release device which may include a connecting element capable of connecting to an aircraft and to a parachute and a locking mechanism capable of releasing the connecting element from the aircraft upon being actuated by an actuator, wherein the parachute may be connected to the connecting element by a multiplicity of points, wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator and wherein the device may be suitable for use in small weights aircrafts due to its small size and weight . The disclosure further provides a method for releasing a parachute from an aircraft, the method may include activating an actuator capable of releasing a locking mechanism, wherein the locking mechanism is adapted to release a connecting element from an aircraft upon being actuated, wherein the connecting element is adapted to connect a parachute and wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator.

    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER
    134.
    发明公开
    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER 有权
    气动起动器用于轻型飞机

    公开(公告)号：EP1594736A2

    公开(公告)日：2005-11-16

    申请号：EP04809283.7

    申请日：2004-02-19

    Applicant: AAI CORPORATION

    Inventor： MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

    IPC: B64B1/00

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

    Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

    MAN-PORTABLE, MULTI-MODE UNMANNED AERIAL SYSTEM LAUNCHER
    136.
    发明申请
    MAN-PORTABLE, MULTI-MODE UNMANNED AERIAL SYSTEM LAUNCHER 审中-公开
    MAN-PORTABLE，多模式无人驾驶飞机系统

    公开(公告)号：WO2014011296A3

    公开(公告)日：2014-03-27

    申请号：PCT/US2013036750

    申请日：2013-04-16

    Applicant: WINTEC ARROWMAKER INC

    Inventor： JONES JOHN CHARLES ,  GRIGORYEV ARTEM IGOREVICH ,  ESPINOSA LUIS CARLOS

    IPC: B64F1/04

    CPC classification number: B64F1/06 ,  B64C2201/084

    Abstract: A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

    Abstract translation: 便携式无人机系统发射器（UAS）发射器包括具有内部轨道的轨道组件和具有被配置为在内部轨道内平移的底座的滑架组件。 托架组件还包括支架，其构造成支撑UAS和支架，其构造成在底座上方支撑支架。 UAS发射器包括发射控制系统，其配置成将支架组件固定在发射就绪位置，直到发射控制系统接收到发射信号。 UAS发射器还包括一个或多个弹性构件，其构造成接合滑架组件和轨道组件。 一旦滑架组件被转换到发射就绪位置，则通过一个或多个弹性构件将应变施加到滑架组件。 托架组件的释放使得由弹性构件的应变产生的力能够将托架组件推向发射位置。

    LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)
    137.
    发明申请
    LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV) 审中-公开
    无人机（UAV）发射管约束系统

    公开(公告)号：WO2013126111A2

    公开(公告)日：2013-08-29

    申请号：PCT/US2012/067086

    申请日：2012-11-29

    Applicant: AEROVIRONMENT, INC. ,  SU, Guan ,  RODRIGUEZ, Marcos

    Inventor： SU, Guan ,  RODRIGUEZ, Marcos

    IPC: B64C1/22

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

    Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

    Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射设备，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），管 （440），所述管（440）包括配置成可控制地阻碍所述AV突片（510）经过所述突片止挡件（515）的行程的突片止挡件（515），以及一对相对的突片引导件 700），其被配置为定位AV标签（510）以在标签止挡（515）上行进。

    AN AIR INTAKE SYSTEM FOR AN AIR VEHICLE
    138.
    发明申请
    AN 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：WO2012072457A1

    公开(公告)日：2012-06-07

    申请号：PCT/EP2011/070752

    申请日：2011-11-23

    Applicant: MBDA UK LIMITED ,  RICHARDS, Clifford, John

    Inventor： RICHARDS, Clifford, John

    IPC: B64D33/02 ,  F02C7/04 ,  F42B10/32 ,  F42B15/10

    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齐或更优选地同轴的轴线可旋转，该收集位置中管道 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。

    TOW HOOK, SYSTEM AND METHOD FOR LAUNCHING AN UNMANNED AERIAL VEHICLE
    139.
    发明申请
    TOW HOOK, SYSTEM AND METHOD FOR LAUNCHING AN UNMANNED AERIAL VEHICLE 审中-公开
    用于启动无人驾驶的空中客车的系统和方法

    公开(公告)号：WO2012030300A1

    公开(公告)日：2012-03-08

    申请号：PCT/SG2011/000268

    申请日：2011-07-29

    Applicant: SINGAPORE TECHNOLOGIES AEROSPACE LTD ,  TAN, Yio Hock ,  CHAN, Keen Ian

    Inventor： TAN, Yio Hock ,  CHAN, Keen Ian

    IPC: B64F1/06 ,  B64D3/00

    CPC classification number: B64D3/00 ,  B64C39/024 ,  B64C2201/084 ,  B64F1/06

    Abstract: Embodiments of the present invention provide a tow hook for use in launching an unmanned aerial vehicle (UAV), the tow hook comprising: a first end capable of releasably engaging a wing of the UAV, a second end capable of being connected to a tow line; and a rigid member connecting the first end to the second end to extend a connection point said tow line below said wing towards a center of gravity of said UAV. Additional embodiments provide for a system and method for launching a UAV using the tow hook.

    Abstract translation: 本发明的实施例提供了用于发射无人机（UAV）的牵引钩，牵引钩包括：能够可释放地接合无人机的机翼的第一端，能够连接到牵引线的第二端 ; 以及刚性构件，其将所述第一端连接到所述第二端，以将所述翼片下方的所述牵引线的连接点朝向所述UAV的重心延伸。 另外的实施例提供了使用牵引钩发射无人机的系统和方法。

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