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    TETHERED UNMANNED AERIAL VEHICLE SYSTEM
    201.
    发明申请
    TETHERED UNMANNED AERIAL VEHICLE SYSTEM 审中-公开

    公开(公告)号：US20170190419A1

    公开(公告)日：2017-07-06

    申请号：US15210039

    申请日：2016-07-14

    Applicant: Tribune Broadcasting Company, LLC

    Inventor： Hank J. HUNDEMER

    IPC: B64C39/02 ,  B64F1/02 ,  B64F3/02

    CPC classification number: B64C39/022 ,  B64C39/024 ,  B64C2201/148 ,  B64C2201/182 ,  B64C2201/208 ,  B64D2201/00 ,  B64F1/02 ,  B64F3/00 ,  B64F3/02

    Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.

    INFLATABLE PARACHUTE AIRBAG SYSTEM
    202.
    发明申请
    INFLATABLE PARACHUTE AIRBAG SYSTEM 审中-公开

    公开(公告)号：US20170158337A1

    公开(公告)日：2017-06-08

    申请号：US15436604

    申请日：2017-02-17

    Applicant: Indemnis, Inc.

    Inventor： Alan Jamal Erickson

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

    CPC classification number: B64D17/72 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/185 ,  B64D17/80 ,  B64D25/00 ,  B64D2201/00

    Abstract: A system and method that reduces the descent velocity of an aerial vehicle, the system including a control system, an inflation device, and a deployable, inflatable cage. The control system detects a descent condition, such as an uncontrolled descent and activates the inflation device to inflate the cage to at least partially encase the aerial vehicle and protect the vehicle during descent and landing. The inflatable cage includes a main fill tube, a perimeter tube, and support tubes. The support tubes are connected between the main fill tube and the perimeter tube, and enable gas to flow from the inflation device through the support and perimeter tubes and into the perimeter tube. A drag inducing material enclosure is connected to the inflatable cage and structured to induce drag to reduce a descent speed of the aerial vehicle.

    Buoyancy system for an aircraft
    205.
    发明授权
    Buoyancy system for an aircraft 有权
    飞机浮力系统

    公开(公告)号：US09533757B2

    公开(公告)日：2017-01-03

    申请号：US14513508

    申请日：2014-10-14

    Applicant: AIRBUS HELICOPTERS

    Inventor： Louis Delorme ,  Nicolas Lamarche ,  David Ayache ,  Bernard Certain

    IPC: B64C25/56 ,  B64D25/00 ,  B64C25/32

    CPC classification number: B64C25/56 ,  B64C2025/325 ,  B64D25/00 ,  B64D2201/00

    Abstract: A buoyancy system (10) for an aircraft (1), the buoyancy system (10) being provided with at least one inflatable float (15). The buoyancy system (10) has at least one inflator (25) and at least one actuator (30) interposed between the inflator (25) and a float (15), the actuator (30) having a cylinder (35) and a rod (40) partially received in the cylinder (35). The rod (40) is secured to a piston (50) defining a first chamber (61) within the cylinder (35) and in fluid flow communication with the inflator (25), and a second chamber (62) within the rod (40) and in fluid flow communication with the float (15), and the piston (50) has a channel (63) to put the first chamber (61) into fluid flow communication with the second chamber (62), the deployment device (20) having a shutter (70) for shutting the channel (63).

    Abstract translation: 一种用于飞机（1）的浮力系统（10），所述浮力系统（10）设置有至少一个可充气浮子（15）。 浮力系统（10）具有至少一个充气机（25）和置于充气机（25）和浮子（15）之间的至少一个致动器（30），所述致动器（30）具有气缸（35）和杆 （40）部分地容纳在气缸（35）中。 所述杆（40）固定到限定所述气缸（35）内并与所述充气机（25）流体连通的第一室（61）的活塞（50），并且所述杆（40）内的第二室（62） ）并且与所述浮子（15）流体连通，并且所述活塞（50）具有通道（63）以使所述第一室（61）与所述第二室（62）流体连通，所述展开装置（20） ）具有用于关闭通道（63）的快门（70）。

    Holding container for shock absorbing self-deployable device
    206.
    发明授权
    Holding container for shock absorbing self-deployable device 有权
    用于冲击吸收自展装置的容器

    公开(公告)号：US09522737B2

    公开(公告)日：2016-12-20

    申请号：US14307673

    申请日：2014-06-18

    Applicant: Eric Fradet

    Inventor： Eric Fradet

    IPC: B64D17/78 ,  B64D17/30 ,  B64D1/14

    CPC classification number: B64D17/78 ,  B64D1/14 ,  B64D17/30 ,  B64D2201/00

    Abstract: A device for absorbing impacts of a parachutist or airdropped package upon landing, which can equip a harness, and/or a skydiver or dropping pallet for performing the aircraft jump without any risk of interferences, allows, during the aircraft exit and free fall, to hold, neutralized in a reduced volume, an air-inflatable airbag, for deployment during the canopy descent. It includes a container back pad hooked to the harness and/or to the user or to the dropping pallet, which can be made removable by straps and bridles, in which an airbag is arranged such that its air scoop is closed by flaps locked by a cutaway cable. When the user exerts an action on the opening handle or when the parachute opens, the cable separates the flaps, allowing to unballast the airbag and open the air scoop to the air flow from the movement of the harness during the descent.

    Abstract translation: 用于吸收爬升器或空中投放的包装物在着陆时的冲击的装置，其可以装备线束，和/或用于执行飞行器跳跃的跳伞者或落料托盘而没有任何干扰的风险，允许在飞行器出口和自由落体期间 保持，减小体积的中空，充气的气囊，用于在冠层下降期间展开。 它包括钩在线束上和/或与用户或落下的托盘上的容器背垫，该托盘可以通过带子和马口将其卸下，其中气囊被布置成使得其空气勺被由 切断电缆 当使用者对开启手柄施加动作时，或者当降落伞打开时，电缆分离襟翼，允许不安全气囊，并且在下降期间将气勺从线束的运动打开到空气流中。

    AUTONOMOUS AIRBAG SYSTEM FOR UNMANNED AERIAL VEHICLES
    208.
    发明申请
    AUTONOMOUS AIRBAG SYSTEM FOR UNMANNED AERIAL VEHICLES 审中-公开
    用于无人机动车的自动安全气囊系统

    公开(公告)号：US20160272333A1

    公开(公告)日：2016-09-22

    申请号：US14660165

    申请日：2015-03-17

    Applicant: Sharper Shape Oy

    Inventor： Tero Heinonen

    IPC: B64D25/00 ,  B64C13/16 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64D2201/00

    Abstract: The present disclosure is related to an autonomous airbag unit (AAU) for an unmanned aerial vehicle (UAV). The AAU includes a first sensor configured to determine a speed of the UAV, a second sensor configured to determine a relative speed of the UAV in relation to an object with which the UAV is likely to collide, an airbag cushion, an inflator connected to the airbag cushion, and an airbag control unit, connected to the first and second sensors and inflator. The airbag control unit is configured to estimate a momentum of the UAV based on a speed of the UAV, determine if the momentum of the UAV exceeds a threshold momentum value, determine if the relative speed of the UAV in relation to the object exceeds a threshold relative speed, and enable the inflator to inflate the airbag cushion when the momentum and the relative speed exceeds respective threshold limits.

    Abstract translation: 本公开涉及一种用于无人机（UAV）的自主安全气囊单元（AAU）。 AAU包括被配置为确定UAV的速度的第一传感器，配置成确定UAV相对于UAV可能碰撞的物体的相对速度的第二传感器，气囊垫，连接到UAV的充气器 气囊垫和安全气囊控制单元，连接到第一和第二传感器和充气机。 安全气囊控制单元被配置为基于UAV的速度来估计UAV的动量，确定UAV的动量是否超过阈值动量值，确定UAV相对于对象的相对速度是否超过阈值 相对速度，并且当动量和相对速度超过相应的阈值极限时，使气囊能够使气囊充气。

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