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83 条记录 (耗时 0.016 秒)

    PERFORATED CAPSULE HOOK FOR STABLE HIGH SPEED RETRACT
    63.
    发明公开
    PERFORATED CAPSULE HOOK FOR STABLE HIGH SPEED RETRACT 审中-公开

    公开(公告)号：EP4169836A1

    公开(公告)日：2023-04-26

    申请号：EP22213770.5

    申请日：2019-04-17

    申请人： Wing Aviation LLC

    发明人： PRAGER, Andre

    IPC分类号： B64D1/22 ,  B64D1/12 ,  B66C1/34 ,  B64D1/10 ,  G06Q10/08 ,  B64U10/13 ,  B64U101/64 ,  B64U101/66 ,  B64U101/67

    摘要： A payload coupling apparatus is provided that includes a housing having an upper portion, a lower portion, and a side wall positioned between the upper and lower portions, an attachment point on the housing adapted for attachment to a first end of a tether, a slot in the housing that extends downwardly towards a center of the housing thereby forming a hook or lip on the lower portion of the housing beneath the slot, a plurality of holes in the upper portion of the housing; and a plurality of holes in the lower portion of the housing. A method of retracting a payload coupling apparatus during UAV flight is also provided.

    AN UNMANNED AERIAL VEHICLE
    65.
    发明公开
    AN UNMANNED AERIAL VEHICLE 审中-公开

    公开(公告)号：EP4434897A3

    公开(公告)日：2024-11-13

    申请号：EP24193323.3

    申请日：2019-12-06

    申请人： Hybrid Drones Limited

    发明人： PRIOR, Stephen

    IPC分类号： B64C29/00 ,  B64D1/22 ,  B64U10/13 ,  B64U50/12 ,  B64U50/19 ,  B64U101/60

    摘要： The present invention provides an unmanned aerial vehicle comprising: a flight system for producing thrust to manoeuvre the unmanned aerial vehicle. The flight system comprises: one or more flight rotors defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor for driving the one or more flight rotors. The unmanned aerial vehicle further comprises: a cargo area for coupling to or receiving a load; and a load system for providing thrust additional to the thrust provided by the flight system to thereby lift a load coupled to or received in the cargoarea. The load system comprises: a plurality of gas turbine propulsion systems fixed with N-fold rotational symmetry, wherein N is the number of gas turbine propulsion systems; and a controller configured to control the flight system and load system.