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    ROTARY AND FIXED WING CONVERTIBLE AIRCRAFT WITH MONOCOPTERS
    3.
    发明公开
    ROTARY AND FIXED WING CONVERTIBLE AIRCRAFT WITH MONOCOPTERS 审中-公开

    公开(公告)号：US20230406551A1

    公开(公告)日：2023-12-21

    申请号：US18335045

    申请日：2023-06-14

    申请人： Aeroseed LLC

    发明人： Ricardo Emilio Dao

    IPC分类号： B64U10/20 ,  B64U30/12 ,  B64U30/297 ,  B64U40/10 ,  B64U30/21 ,  B64U20/40

    CPC分类号： B64U10/20 ,  B64U30/12 ,  B64U30/297 ,  B64U2201/20 ,  B64U30/21 ,  B64U20/40 ,  B64U40/10

    摘要： Systems, methods and devices for rotary and fixed wing convertible aircraft with monocopters. A monocopter flying device may include a main body and a wing pivotally coupled to the main body. A wing actuator operably coupled to the wing may be configured to pivot the wing about its longitudinal axis. The flying device may include a propulsion unit pivotally coupled to the main body that includes a motor and a propeller having a hub and radially extending blades. A propulsion unit actuator may be configured to pivot the propulsion unit about an axis non-parallel to the axis of rotation of the propellor. The flying device may include a control system including one or more processors configured to control operation of the devices. The flying devices may connect together to form a flying system having multiple flight modes with varying orientations. The flying system may disaggregate the flying devices in flight.

    ROTARY WING AIRCRAFT
    4.
    发明公开
    ROTARY WING AIRCRAFT 审中-公开

    公开(公告)号：US20230202686A1

    公开(公告)日：2023-06-29

    申请号：US18000057

    申请日：2020-05-27

    申请人： AERONEXT INC.

    发明人： Yoichi SUZUKI

    IPC分类号： B64U10/16 ,  B64C27/24 ,  B64U30/21 ,  B64U50/13 ,  B64D35/00

    CPC分类号： B64U10/16 ,  B64C27/24 ,  B64U30/21 ,  B64U50/13 ,  B64D35/00

    摘要： The operational efficiency of a rotorcraft in cruising. The rotary wing aircraft, according to the present disclosure, has a main body and a plurality of motors provided in the main body for rotating each of the rotors, which are parallel to a reference plane. When the main body is inclined with respect to one direction of travel and flying in the direction of travel, the rotational speed of each of the plurality of motors is approximately the same.

    FIRE FIGHTING DRONE CONFIGURED TO BE RELEASED FROM AN AIRCRAFT
    5.
    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

    申请人： LEONARDO S.P.A.

    发明人： Antonio Piccolo ,  Emanuele Bottone ,  Gaetana Mastroianni ,  Umberto Papa

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

    CPC分类号： A62C3/0235 ,  B64U30/21 ,  B64U70/20 ,  B64U2101/47

    摘要： 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.

    AERIAL VEHICLE
    7.
    发明公开
    AERIAL VEHICLE 审中-公开

    公开(公告)号：US20240278943A1

    公开(公告)日：2024-08-22

    申请号：US18573267

    申请日：2021-06-22

    申请人： AERONEXT INC.

    发明人： Yoichi SUZUKI

    IPC分类号： B64U10/14 ,  B64U20/77 ,  B64U30/21

    CPC分类号： B64U10/14 ,  B64U20/77 ,  B64U30/21

    摘要： According to this invention, an aerial vehicle can be provided that reduces the effect of wind in a given direction striking its frame during flight of the aerial vehicle, thereby improving fuel consumption and stability. The aerial vehicle of this invention is equipped with a flight part including a frame to which a plurality of rotor blades including at least a propeller and a motor are connected, wherein the frame includes a right frame and a left frame extending side by side in the front-rear direction of the aerial vehicle, and at least one of the right frame and the left frame has a substantially wing-shaped portion with a leading edge located outside the aerial vehicle and a trailing edge located inside the aerial vehicle relative to a vertical center line in the frame. The substantially wing-shaped shape is a symmetrical wing shape.

    A PROPELLER FOR AN AIRCRAFT
    8.
    发明公开
    A PROPELLER FOR AN AIRCRAFT 审中-公开

    公开(公告)号：US20240051687A1

    公开(公告)日：2024-02-15

    申请号：US17766444

    申请日：2021-04-27

    申请人： KATLA AERO AB

    发明人： Gustav WIBERG

    IPC分类号： B64U10/16 ,  B64U30/21

    CPC分类号： B64U10/16 ,  B64U30/21

    摘要： A propeller for an aircraft includes at least two blades, arranged about a central hub, which is coupled to at least one motor, driven by a power source. At least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub. An inner surface of each of the at least one sleeve member includes at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element. Each of the at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position. Each of the at least one sleeve member positions its blade in an operational position when its, at least one, projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element. Each of the at least one sleeve member positions its blade in a storage position when its, at least one, projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element. A rotation of the first cylindrical element moves each of the at least one sleeve member thereabout along their first recessed guide path. An arrangement includes the propeller and a compartment configured to accommodate the propeller. An aircraft includes at least one wing and at least one propeller.

    MOBILE BODY, METHOD OF CONTROLLING MOBILE BODY, PROGRAM OF CONTROLLING MOBILE BODY, AND ELECTRIC POWER SUPPLY SYSTEM
    9.
    发明公开
    MOBILE BODY, METHOD OF CONTROLLING MOBILE BODY, PROGRAM OF CONTROLLING MOBILE BODY, AND ELECTRIC POWER SUPPLY SYSTEM 审中-公开

    公开(公告)号：US20230234731A1

    公开(公告)日：2023-07-27

    申请号：US17999405

    申请日：2021-04-13

    申请人： Sony Group Corporation

    发明人： Hirotaka TANAKA

    IPC分类号： B64U50/30 ,  B64U30/21 ,  H01M10/613 ,  H01M10/625 ,  B64U50/19

    CPC分类号： B64U50/30 ,  B64U30/21 ,  H01M10/613 ,  H01M10/625 ,  B64U50/19 ,  B64U10/14

    摘要： Heating a battery and cooling an electric power conversion device are achieved together. This mobile body includes an electric motor, a battery, a thermoelectric conversion element, an electric power conversion device, and a controller. The electric motor is a driving source. The electric power conversion device is configured to convert electric power outputted from the battery into driving electric power for the electric motor. The electric power conversion device is disposed in direct contact or in indirect contact with the battery with the thermoelectric conversion element interposed therebetween. The controller is configured to control electric power to be supplied to the thermoelectric conversion element. The controller controls, in a case where the battery is in a predetermined low-temperature state, the electric power to be supplied to the thermoelectric conversion element to cause a surface of the thermoelectric conversion element coupled to the battery to serve as a heat dissipation surface.