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    LIFE-SAVING EQUIPMENT FOR UNMANNED AIR VEHICLES
    42.
    发明申请
    LIFE-SAVING EQUIPMENT FOR UNMANNED AIR VEHICLES 审中-公开
    为不间断的空中车辆提供救生设备

    公开(公告)号：US20160221681A1

    公开(公告)日：2016-08-04

    申请号：US15009860

    申请日：2016-01-29

    Applicant: Vysoke Uceni Technicke V Brne ,  Ing. Milan BABOVKA - Galaxy

    Inventor： Milan BABOVKA ,  Robert POPELA ,  Jan PEJCHAR ,  Milos DANIEL ,  Ondrej NEMCAK

    IPC: B64D17/72 ,  B64C39/02 ,  B64D17/80

    CPC classification number: B64D17/725 ,  B64C39/024 ,  B64C2201/185 ,  B64D17/42 ,  B64D17/80

    Abstract: The life-saving equipment for unmanned air vehicles includes a container with an opening, a parachute, consisting of a parachute canopy, suspension lines and a harness, where the parachute can be folded inside the container, a stopper which divides the inner space of the container into the combustion chamber and the storage chamber for storing the parachute, where the storage chamber is arranged between the stopper and the container opening and where the stopper is designed to be slid out of the container through the opening, and a gas pyro actuator placed in the combustion chamber and connectable to the activation line.

    Abstract translation: 用于无人驾驶飞行器的救生设备包括具有开口的容器，降落伞，包括降落伞，悬挂线和吊带，其中降落伞可以折叠在容器内部;塞子，其将内部空间 容器进入燃烧室和用于储存降落伞的储存室，其中存储室布置在止动器和容器开口之间，并且止动器被设计成通过开口滑出容器，并且气体热传感器放置在 在燃烧室中并可连接到激活线。

    Rocket Morphing Aerial Vehicle
    43.
    发明申请
    Rocket Morphing Aerial Vehicle 审中-公开
    火箭变形飞行器

    公开(公告)号：US20160046372A1

    公开(公告)日：2016-02-18

    申请号：US14722104

    申请日：2015-05-26

    Applicant: L'Garde, Inc.

    Inventor： Nathaniel C. Barnes ,  Amir Shahram Gohardani

    IPC: B64C39/02 ,  B64D17/80 ,  B64F1/10

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/082 ,  B64C2201/185

    Abstract: A rocket morphing aerial vehicle has a first rocket configuration and a second aerial vehicle configuration. The rocket morphing aerial vehicle may be used to deploy an aerial vehicle at further distances faster. The rocket configuration may be used to get the aerial vehicle to its desired location, while the aerial vehicle is used for the desired task. The rocket morphing aerial vehicle may include a deceleration mechanism such that the speed of the rocket does not interfere with the deployment of the aerial vehicle.

    Abstract translation: 火箭变形飞行器具有第一火箭构型和第二空中飞行器构造。 火箭变形飞行器可以用于更快地部署更远的飞行器。 可以使用火箭配置来将空中飞行器用于所需的位置，而空中飞行器则用于所需的任务。 火箭变形飞行器可以包括减速机构，使得火箭的速度不会干扰飞行器的展开。

    METHOD OF LANDING OF A SURVEILLANCE UNMANNED AERIAL VEHICLE AND A SURVEILLANCE UNMANNED AERIAL VEHICLE
    45.
    发明申请
    METHOD OF LANDING OF A SURVEILLANCE UNMANNED AERIAL VEHICLE AND A SURVEILLANCE UNMANNED AERIAL VEHICLE 审中-公开
    无人驾驶航空器的监视方法和无人驾驶的空中客车监视

    公开(公告)号：US20140151508A1

    公开(公告)日：2014-06-05

    申请号：US13689853

    申请日：2012-11-30

    Applicant: WB Electronics S.A.

    Inventor： WOJCIECH SZUMINSKI ,  Ryszard Jurecki ,  Grzegorz Krupa ,  Adam Bartosiewicz ,  Piotr Wojciechowski

    IPC: B64D1/08

    CPC classification number: B64D1/08 ,  B60V1/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/185 ,  B64C2201/187

    Abstract: The mode of landing of an unmanned aerial vehicle driven by an electric engine, containing main power supply batteries, control systems of the surveillance head, transmitting and receiving systems, a flight control system, and a container equipped with a surveillance head with a looking down lens, placed in a recess situated in the lower part of the fuselage by which the vehicle is lightened at the last stage of flight shortly before landing, which means the container placed in the recess is detached, then moved outside the vehicle's body and descended by means of a parachute into a desired location, and the lightened vehicle lands in some other place. The recess in the fuselage contains an electrically controlled lock which fixes detachably the container equipped with at least one parachute placed at the bottom section of the container, on the side of the surveillance head.

    Abstract translation: 由电动发动机驱动的无人驾驶飞机的模式，包含主电源电池，监视头的控制系统，发射和接收系统，飞行控制系统和装备有俯视监视头的集装箱 透镜放置在位于机身下部的凹部中，车辆在着陆前不久的最后阶段减轻，这意味着放置在凹槽中的容器被分离，然后移动到车身的外部并且下降 降落伞进入所需位置的方式，轻型车辆落在其他地方。 机身中的凹槽包含一个电控锁，其可拆卸地固定装备有至少一个放置在容器底部的降落伞的容器，在监视头的一侧。

    Unmanned aerial vehicle for logistical delivery
    46.
    发明授权
    Unmanned aerial vehicle for logistical delivery 失效
    无人机用于后勤运输

    公开(公告)号：US07059566B2

    公开(公告)日：2006-06-13

    申请号：US10856360

    申请日：2004-05-27

    Applicant: David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

    Inventor： David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

    IPC: B64C1/00

    CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

    Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

    Abstract translation: 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。

    Unmanned airborne reconnaissance system
    47.
    发明授权
    Unmanned airborne reconnaissance system 有权

    公开(公告)号：US07014141B2

    公开(公告)日：2006-03-21

    申请号：US10194814

    申请日：2002-07-12

    Applicant: Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

    Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

    IPC: B64C13/20 ,  B64C13/00

    CPC classification number: F41G3/02 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06 ,  Y02T50/82

    Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

    Method for deploying a parachute on a drone
    48.
    发明授权
    Method for deploying a parachute on a drone 失效
    在无人机上部署降落伞的方法

    公开(公告)号：US06471160B2

    公开(公告)日：2002-10-29

    申请号：US09865106

    申请日：2001-05-24

    Applicant: Wolfram Grieser

    Inventor： Wolfram Grieser

    IPC: B64C2556

    CPC classification number: B64D17/80 ,  B64C2201/185

    Abstract: A flying drone includes a flight control computer, a parachute system with a parachute, a power supply system, a propulsion system, and an actuating drive system, without any of these systems being redundantly duplicated. To prevent uncontrolled crashing of the drone due to a critical error of any subsystem, signals or data are supplied from the power supply system, the propulsion system, and the actuating drive system, to an error detection or recognition device, which detects defined errors or error combinations in the provided signals or data and then supplies a deployment signal to the parachute system, which responsively generates a control signal that triggers an ejection mechanism to eject the parachute.

    Abstract translation: 飞行无人机包括飞行控制计算机，具有降落伞的降落伞系统，电源系统，推进系统和致动驱动系统，而没有任何这些系统被冗余地重复。 为了防止由于任何子系统的关键错误导致的无人驾驶飞机的不受控制的撞击，信号或数据从电源系统，推进系统和致动驱动系统提供给检错定义的错误或错误检测或识别装置 所提供的信号或数据中的错误组合，然后将部署信号提供给降落伞系统，其响应地产生触发弹射机构以弹出降落伞的控制信号。

    Method for deploying a parachute on a drone
    49.
    发明申请
    Method for deploying a parachute on a drone 失效
    在无人机上部署降落伞的方法

    公开(公告)号：US20010048050A1

    公开(公告)日：2001-12-06

    申请号：US09865106

    申请日：2001-05-24

    Inventor： Wolfram Grieser

    IPC: B64D017/14 ,  B64D017/18 ,  B64D017/34

    CPC classification number: B64D17/80 ,  B64C2201/185

    Abstract: A flying drone includes a flight control computer, a parachute system with a parachute, a power supply system, a propulsion system, and an actuating drive system, without any of these systems being redundantly duplicated. To prevent uncontrolled crashing of the drone due to a critical error of any subsystem, signals or data are supplied from the power supply system, the propulsion system, and the actuating drive system, to an error detection or recognition device, which detects defined errors or error combinations in the provided signals or data and then supplies a deployment signal to the parachute system, which responsively generates a control signal that triggers an ejection mechanism to eject the parachute.

    Abstract translation: 飞行无人机包括飞行控制计算机，具有降落伞的降落伞系统，电源系统，推进系统和致动驱动系统，而没有任何这些系统被冗余地重复。 为了防止由于任何子系统的关键错误导致的无人驾驶飞机的不受控制的撞击，信号或数据从电源系统，推进系统和致动驱动系统提供给检错定义的错误或错误检测或识别装置 所提供的信号或数据中的错误组合，然后将部署信号提供给降落伞系统，其响应地产生触发弹射机构以弹出降落伞的控制信号。

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