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    Pulse-Induced Cyclic Control Lift Propeller
    1.
    发明申请
    Pulse-Induced Cyclic Control Lift Propeller 有权

    公开(公告)号：US20210354813A1

    公开(公告)日：2021-11-18

    申请号：US17323096

    申请日：2021-05-18

    申请人： IQinetics Technologies, Inc.

    发明人： Matthew Piccoli

    IPC分类号： B64C27/39 ,  B64C27/605

    摘要： The present application relates to a propulsion device having a motor, a mast connected to the motor, an angle sensing device detecting the angle of the mast, a controller receiving the angle of the mast as an input and outputting a motor torque signal to the motor in response thereto, a hub attached to the mast via a single skewed hinge, and a propeller assembly with one or more blades connected to a hub.

    Propeller units
    2.
    发明授权
    Propeller units 有权

    公开(公告)号：US11066156B2

    公开(公告)日：2021-07-20

    申请号：US16174228

    申请日：2018-10-29

    申请人： Wing Aviation LLC

    发明人： Parsa Dormiani ,  James Ryan Burgess

    IPC分类号： B64C27/26 ,  B64C27/39 ,  B64C39/02 ,  B64C11/28 ,  B64C27/30

    摘要： An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.

    Hinge mechanism for a weight-shifting coaxial helicopter
    3.
    发明授权
    Hinge mechanism for a weight-shifting coaxial helicopter 有权

    公开(公告)号：US10814968B2

    公开(公告)日：2020-10-27

    申请号：US15447845

    申请日：2017-03-02

    申请人： Lockheed Martin Corporation

    发明人： Dustin E. Gamble ,  Matthew Curran ,  Brian Miller

    IPC分类号： B64C27/39 ,  B64C27/48 ,  B64C27/50 ,  B64C27/10 ,  B64C39/02 ,  B64C17/04 ,  B64C27/52 ,  B64C25/32

    摘要： A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

    PASSIVE PITCH ANGLE ADJUSTMENT APPARATUS
    6.
    发明申请
    PASSIVE PITCH ANGLE ADJUSTMENT APPARATUS 审中-公开

    公开(公告)号：US20190263514A1

    公开(公告)日：2019-08-29

    申请号：US16284926

    申请日：2019-02-25

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Patrik SCHMIEDEL ,  Harald LEITNER ,  Julian KRAUS ,  Ludwig DANNEMANN ,  Uwe KIESEWETTER

    IPC分类号： B64C27/72 ,  B64C27/39 ,  B64C27/04

    摘要： A rotor or propeller may have rotor blades and a passive pitch angle adjustment apparatus. The passive pitch angle adjustment apparatus may include levers, rods, and central rod. Levers may be connected to rotor blades and rotate them around a respective pitch axis. Rods may be connected to levers and mechanically link levers with each other via central point that is located outside rotor plane. Central rod may connect central point with base point that is located in a longitudinal direction of rotor axis. The passive pitch angle adjustment apparatus may enable a cyclic pitch adjustment of the rotor blades and block a collective pitch adjustment of the rotor blades.

    FOLDABLE ROTOR BLADE ASSEMBLY AND AERIAL VEHICLE WITH A FOLDABLE ROTOR BLADE ASSEMBLY
    7.
    发明申请
    FOLDABLE ROTOR BLADE ASSEMBLY AND AERIAL VEHICLE WITH A FOLDABLE ROTOR BLADE ASSEMBLY 审中-公开

    公开(公告)号：US20190210718A1

    公开(公告)日：2019-07-11

    申请号：US16243593

    申请日：2019-01-09

    申请人： Hangzhou Zero Zero Technology Co., Ltd.

    发明人： Zhaozhe Wang

    IPC分类号： B64C27/39 ,  B64C27/48 ,  B64C27/72

    CPC分类号： B64C27/39 ,  B64C27/48 ,  B64C27/72 ,  B64C2027/7211

    摘要： An aerial vehicle is described herein. The aerial vehicle includes a lift mechanism that includes a rotor blade assembly coupled to a motor assembly. The rotor blade assembly includes a plurality of rotor blades that are pivotably coupled to a rotor blade clamping mechanism. The rotor blade clamping mechanism includes an upper paddle clamp that is coupled to a lower paddle clamp. The upper paddle clamp includes a center protrusion and a plurality of blade support protrusions extending outwardly from the lower outer surface. The center protrusion includes a center shaft aperture sized and shaped to receive a motor shaft therein. Each blade support protrusion is sized and shaped to be inserted through a corresponding positioning aperture of a corresponding rotor blade. The lower paddle clamp includes a central recess to receive the center protrusion therein and a plurality of blade recesses to receive a corresponding blade support protrusion therein.