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    Electrical Power Transmission for Propeller Deicing
    3.
    发明公开
    Electrical Power Transmission for Propeller Deicing 审中-公开

    公开(公告)号：US20240109663A1

    公开(公告)日：2024-04-04

    申请号：US18274809

    申请日：2022-02-14

    Applicant: UBIQ Aerospace AS

    Inventor： Shibarchi Majumder ,  Kim Sørensen

    IPC: B64D15/12 ,  B64C11/00

    CPC classification number: B64D15/12 ,  B64C11/00

    Abstract: A propulsion system for a propeller of an aircraft is described, wherein the propulsion system allows for transmission of electrical power such as for a deicing system for the propeller. The propulsion system comprises a rotatable shaft for transmission of mechanical power; aircraft end electrical connections at an aircraft end of the shaft for connection to first and second terminals of a source of electrical power; propeller end electrical connections at a propeller end of the shaft and being for connection to first and second terminals for supplying electrical power to electrical components on the propeller; and a mechanical coupling at the propeller end of the shaft for mounting the propeller to the shaft. The shaft comprises: an inner conductor extending along the length of the shaft; an outer conductor extending along the length of the shaft; and an electrical insulator extending along the shaft in between the inner and outer conductor.

    IMPROVED ACOUSTIC ATTENUATION DEVICE FOR AN AIRCRAFT PROPULSION UNIT
    4.
    发明公开
    IMPROVED ACOUSTIC ATTENUATION DEVICE FOR AN AIRCRAFT PROPULSION UNIT 审中-公开

    公开(公告)号：US20240059396A1

    公开(公告)日：2024-02-22

    申请号：US18260967

    申请日：2022-01-07

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Fernando GEA AGUILERA ,  Adrien Clément Marcel DUBOIS ,  Jean-Michel Daniel Paul BOITEUX ,  Ludovic Mathieu René WIART

    IPC: B64C11/00

    CPC classification number: B64C11/00 ,  B64C2230/14

    Abstract: Propulsion assembly for an aircraft comprising a turbomachine having at least one rotating part rotating about an axis of rotation, an attachment strut, and a structural element carrying the turbomachine via the attachment strut, the rotating part being disposed upstream of the structural element and of the attachment strut such that an air jet emerging from the rotating part, in the wake of thereof, impacts the structural element and the attachment strut, a leading edge of the structural element and/or of said attachment strut locally comprising at least one acoustic attenuation device disposed at least partly in the wake of the rotating part, the acoustic attenuation device being a local modification of the structure and/or of the profile of the leading edge.

    Drone rotor cage
    5.
    发明授权
    Drone rotor cage 有权

    公开(公告)号：US11851170B2

    公开(公告)日：2023-12-26

    申请号：US17002466

    申请日：2020-08-25

    Applicant: Intel Corporation

    Inventor： Fabian Oberndorfer

    IPC: B64C27/00 ,  B64C39/02 ,  B64C11/20 ,  B64C11/00 ,  B64U10/00 ,  B64U30/20

    CPC classification number: B64C27/006 ,  B64C11/205 ,  B64C39/024 ,  B64C11/00 ,  B64U10/00 ,  B64U30/20

    Abstract: Disclosed is a drone rotor cage. The drone rotor cage may include a motor housing, a plurality of spars, and a plurality of ribs. The plurality of spars may extend from the motor housing. Each of the plurality of spars may have a spar height and a spar thickness. The spar height may be greater than the spar thickness. Each of the ribs may extend from a respective one of the plurality of spars. Each of the plurality of ribs may have a rib height and a rib thickness. The rib height may be greater than the rib thickness. The plurality of spars and the plurality of ribs may define a space sized to allow a rotor to spin freely when the rotor cage is attached to a drone.

    Tiltrotor Aircraft having Rotatable Wing Extensions
    9.
    发明申请
    Tiltrotor Aircraft having Rotatable Wing Extensions 有权

    公开(公告)号：US20180057159A1

    公开(公告)日：2018-03-01

    申请号：US15252545

    申请日：2016-08-31

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Steven Ray Ivans ,  Nathan Gabriel Wu

    IPC: B64C29/00 ,  B64C11/00 ,  B64C3/38 ,  B64C7/02

    CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C5/08 ,  B64C7/02 ,  B64C11/00 ,  B64C27/28 ,  B64C29/02

    Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode. The rotor assembly includes a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.

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