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    Parachute release device for unmanned aerial vehicle (UAV)
    125.
    发明授权
    Parachute release device for unmanned aerial vehicle (UAV) 有权
    无人机（UAV）降落伞释放装置

    公开(公告)号：US08191831B2

    公开(公告)日：2012-06-05

    申请号：US11992188

    申请日：2005-11-30

    Applicant: Ronen Nadir

    Inventor： Ronen Nadir

    IPC: B64D17/00 ,  B64D17/54

    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.

    Abstract translation: 本公开提供了一种降落伞释放装置，其可以包括能够连接到飞机和降落伞的连接元件，以及能够由致动器致动时能够从飞行器释放连接元件的锁定机构，其中降落伞可以连接到 所述连接元件由多个点组成，其中所述锁定机构适于阻止施加到所述致动器的力，并且其中所述装置由于其小的尺寸和重量而适合用于小型重量飞机。 本发明还提供了一种用于从飞行器释放降落伞的方法，所述方法可包括激活能够释放锁定机构的致动器，其中所述锁定机构适于在致动时从飞行器释放连接元件，其中所述连接元件 适于连接降落伞，并且其中所述锁定机构适于阻止施加在所述致动器上的力。

    Frangible fasteners for aircraft components and associated systems and methods
    126.
    发明授权
    Frangible fasteners for aircraft components and associated systems and methods 有权
    用于飞机部件和相关系统和方法的易碎紧固件

    公开(公告)号：US08136766B2

    公开(公告)日：2012-03-20

    申请号：US12024861

    申请日：2008-02-01

    Applicant: Brian D. Dennis

    Inventor： Brian D. Dennis

    IPC: B64C23/06 ,  B64C1/00

    CPC classification number: B64C3/38 ,  B64C23/069 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  F16B31/021 ,  F16B41/002 ,  Y02T50/164 ,  Y10T29/49947

    Abstract: Frangible fasteners and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage portion, a wing portion, and a winglet carried by the wing portion. The aircraft can also include at least one frangible fastener coupling the winglet to the wing portion. The fastener is coupled to only partially release the winglet from the wing portion when a force on the winglet exceeds a threshold value.

    Abstract translation: 本文公开了易碎紧固件及相关系统和方法。 在一个实施例中，例如，无人飞行器可以包括机身部分，翼部分和由翼部分承载的小翼。 飞机还可以包括将小翼片连接到机翼部分的至少一个易碎紧固件。 当小翼上的力超过阈值时，紧固件联接成仅从翼部分部分地释放小翼。

    Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and breaking subsequent grip motion
    127.
    发明授权
    Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and breaking subsequent grip motion 有权
    用于发射无人机的方法和装置，包括在发射期间可释放地夹持飞行器并且打破随后的抓地力

    公开(公告)号：US07360741B2

    公开(公告)日：2008-04-22

    申请号：US11603815

    申请日：2006-11-21

    Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

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

    IPC: B64F1/06

    CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

    Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

    Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有与飞行器接触的至少一个抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

    Electric motor assisted takeoff device for an air vehicle
    128.
    发明申请
    Electric motor assisted takeoff device for an air vehicle 有权
    用于机动车辆的电动辅助起飞装置

    公开(公告)号：US20070145182A1

    公开(公告)日：2007-06-28

    申请号：US11304535

    申请日：2005-12-16

    Applicant: Gregory Page

    Inventor： Gregory Page

    IPC: B64F1/04

    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.

    Abstract translation: 提供了一种用于空中客车的起飞辅助装置，例如无人机。 该装置具有电动机，并且比迄今为止已知的起飞辅助装置复杂和轻巧。 身体构件被成形为适合于空中车辆的一部分。 主体构件限定了容纳大部分部件的壳体，包括电动马达，马达控制器，电源和主控制器。 螺旋桨安装在外壳外的电动机的轴上，并与电动机的轴一起旋转。 此外，还有一个可将主体部件可移除地连接到主机空中的起飞位置的闩锁机构，然后在空气车辆以期望的空速和高度空气传播后被控制以释放。 电动马达起飞辅助装置可以发射具有最小辅助设备的空中飞行器，并且可以远程控制以从起飞准备好的车辆可以长时间留下的地点发射。

    Aircraft configuration for micro and mini uav
    129.
    发明申请
    Aircraft configuration for micro and mini uav 有权
    飞机配置微型和迷你型

    公开(公告)号：US20070029440A1

    公开(公告)日：2007-02-08

    申请号：US10573570

    申请日：2004-07-22

    Applicant: Michael Shepshelovich ,  Mario Sletean ,  Moshe Steinbuch ,  David Levy

    Inventor： Michael Shepshelovich ,  Mario Sletean ,  Moshe Steinbuch ,  David Levy

    IPC: B64C1/00 ,  B64C13/20

    CPC classification number: B64D15/163 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/165

    Abstract: An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive sweep, while the fore wing (14) has non-positive trailing edge sweep. The fore wing (14) and the aft wing (12) are disposed at different height, and the aircraft arrangement has no other wings or tail arrangements.

    Abstract translation: 一种用于迷你或微型无人机的飞行器装置，其包括串联闭合联接装置的前翼（14）和后翼（12）。 后翼（12）具有侧板（18）和控制表面（19），并且具有正扫掠的锥形平面，而前翼（14）具有非正的后缘扫掠。 前翼（14）和后翼（12）设置在不同的高度，并且飞行器装置没有其他翼或尾翼装置。

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