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    FIRE FIGHTING DRONE CONFIGURED TO BE RELEASED FROM AN AIRCRAFT
    1.
    发明公开
    FIRE FIGHTING DRONE CONFIGURED TO BE RELEASED FROM AN AIRCRAFT 审中-公开

    公开(公告)号：US20240350843A1

    公开(公告)日：2024-10-24

    申请号：US18291625

    申请日：2023-03-20

    Applicant: LEONARDO S.P.A.

    Inventor： Antonio Piccolo ,  Emanuele Bottone ,  Gaetana Mastroianni ,  Umberto Papa

    IPC: A62C3/02 ,  B64U30/21 ,  B64U70/20 ,  B64U101/47

    CPC classification number: A62C3/0235 ,  B64U30/21 ,  B64U70/20 ,  B64U2101/47

    Abstract: Fire fighting drone comprising an exoskeleton defining an internal space extending along an axis H and a flexible bag stably housed in the internal space, provided with a release valve and configured to contain a fire fighting liquid; a support structure provided with a plurality of thrusters adapted to perform a thrust that enables the support structure to be supported in flight; the support structure is connected to a first end portion of the exoskeleton; a plurality of movable directional wings carried by the exoskeleton, extending outwards from the exoskeleton itself and angularly movable relative to the exoskeleton around respective axes H transverse to the axis H; an electronic control unit adapted to control the thruster, to generate the release signal and adapted to control the actuators that perform the rotation of the wings; the electronic control unit is configured to control said wings to allow the rotation of the wings during the free-fall phase of said drone which is released from an aircraft and thereby performs a certain trajectory of said drone from the aircraft to a launch zone; the electronic unit is configured to enable the discharge of said liquid from said bag and the activation of the thrusters following the discharge of the liquid to enable the flight of the support structure and of the exoskeleton containing the empty bag to a landing zone.

    Unmanned aerial vehicle jettison apparatus
    6.
    发明授权
    Unmanned aerial vehicle jettison apparatus 有权

    公开(公告)号：US11794930B1

    公开(公告)日：2023-10-24

    申请号：US17398274

    申请日：2021-08-10

    Applicant: The United States of America, as represented by the Secretary of the Navy

    Inventor： Shawn Kerry McGann ,  Nicholas McGaha

    IPC: B64U10/14 ,  B64D5/00 ,  B64U70/20

    CPC classification number: B64U10/14 ,  B64D5/00 ,  B64U70/20

    Abstract: An unmanned aerial vehicle (UAV) jettison apparatus. The UAV jettison apparatus may comprise a payload bay, fairing, ejector plate, and releasable latch. The payload bay may be mounted beneath an aircraft and may have an inner space and a top plate attached therewith. The fairing may substantially cover the inner space of the payload bay and may have an opening positioned directly below the top plate. The ejector plate, which may be spring-loaded, may substantially cover the opening and may be used to mount the UAV. The releasable latch, which may be disposed between the top plate and the ejector plate, may releasably lock and hold the UAV in a stowed position and, upon release, may allow the ejector plate to move into a launch position, such that the UAV is released and jettisoned from a larger aircraft.

    VEHICLE, TRANSPORT SYSTEM (VARIANTS) AND METHOD OF MOVING VEHICLE
    8.
    发明公开
    VEHICLE, TRANSPORT SYSTEM (VARIANTS) AND METHOD OF MOVING VEHICLE 审中-公开

    公开(公告)号：US20240109676A1

    公开(公告)日：2024-04-04

    申请号：US18221009

    申请日：2023-07-12

    Applicant: Andreev Pavel Ruslanovich

    Inventor： Andreev Pavel Ruslanovich

    IPC: B64U80/82 ,  B64C1/22 ,  B64C39/02 ,  B64U70/20

    CPC classification number: B64U80/82 ,  B64C1/22 ,  B64C39/024 ,  B64U70/20 ,  B64U2201/20

    Abstract: Provided is a vehicle comprising a fuselage provided with at least one storage module each configured to accommodate therein unmanned aerial systems and at least one docking module each configured to detachably interact with at least one of the unmanned aerial systems so as to enable connection thereof to the fuselage for movement of the vehicle, and a control module configured to present control commands to at least one of the unmanned aerial systems so as to enable release thereof from the storage module for interaction with one of the docking modules. Furthermore, provided are variants of the transport system, each of which variants includes the subject vehicle, and a method of moving the subject vehicle.

    UAV SYSTEM AND METHOD FOR SIMULATION OF REDUCED-GRAVITY ENVIRONMENTS
    10.
    发明公开
    UAV SYSTEM AND METHOD FOR SIMULATION OF REDUCED-GRAVITY ENVIRONMENTS 审中-公开

    公开(公告)号：US20230406549A1

    公开(公告)日：2023-12-21

    申请号：US18252494

    申请日：2021-11-10

    Applicant: RAPTOR AEROSPACE LTD

    Inventor： Callum Dominic Cabielles Rolfe ,  Adam William Oxbury ,  Aaron McNeil

    IPC: B64G7/00 ,  B64U70/20 ,  B64U50/14 ,  B64U50/19 ,  B64U70/83

    CPC classification number: B64G7/00 ,  B64U70/20 ,  B64U50/14 ,  B64U50/19 ,  B64U70/83 ,  B64U2101/60

    Abstract: UAV (400, 500, 600) systems and methods for simulation of reduced-gravity environments are disclosed. A UAV (400, 500, 600) system has an ascent vehicle (104), comprising ascent thrust means, and an aerodynamic, free fall descent UAV (102, 706), comprising descent thrust means. The ascent vehicle (104) comprises means to convey the descent UAV (102, 706) to a drop altitude (108), and the descent UAV (102, 706) is separable from the ascent vehicle (104). The descent thrust means is operable, following separation of the descent UAV (102, 706) from the ascent vehicle (104), to provide a thrust component in a descent direction (256), for countering air resistance on the UAV (400, 500, 600). The descent UAV (102, 706) may comprise a sensor system and controller (204), and the descent thrust means may comprise a ducted fan system. The sensor system may be operable, during descent of the UAV (400, 500, 600), to determine values for parameters associated with the acceleration due to gravity of the UAV (400, 500, 600), the controller (204) being operable to use the determined parameter values to control the ducted fan system to provide the thrust component.

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