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    High speed rotor blade design
    1.
    发明授权
    High speed rotor blade design 有权

    公开(公告)号：US12116119B2

    公开(公告)日：2024-10-15

    申请号：US17706531

    申请日：2022-03-28

    申请人： LOCKHEED MARTIN CORPORATION

    发明人： Byung-Young Min ,  Vera Klimchenko ,  Annie Gao ,  Alexander F. Dunn ,  Claude George Matalanis ,  Brian Ernest Wake

    IPC分类号： B64C27/46 ,  B64C27/467 ,  B64C27/473

    CPC分类号： B64C27/467 ,  B64C27/473

    摘要： A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

    Single-blade aircraft rotor
    4.
    发明授权
    Single-blade aircraft rotor 有权

    公开(公告)号：US11987347B2

    公开(公告)日：2024-05-21

    申请号：US17774285

    申请日：2020-11-04

    申请人： INNOSTAR ,  HUTCHINSON

    发明人： Jean-Michel Simon ,  Louis Chemouni

    IPC分类号： B64C27/473 ,  B64C27/00 ,  B64C27/43 ,  B64C27/51

    CPC分类号： B64C27/43 ,  B64C27/001 ,  B64C27/473 ,  B64C27/51 ,  B64C2027/005

    摘要： A rotor for a rotary wing aircraft having a single blade with a longitudinal pitch axis and that is hinge mounted on the rotary shaft for rotating the rotor, the hinge being about an axis that is transversal relative to the rotary shaft, said rotary wing describing a cone when its pitch angle is not zero, the rotor possessing a balancing flyweight device for balancing the resultant of the horizontal component of the lift force and of the rotary drag force of the blade, the device being mounted to rotate with the rotary wing about its rotary shaft and, under the effect of the centrifugal force to which it is subjected while the rotary wing is rotating, generating a horizontal force that is applied to the rotary shaft of the motor and that opposes the above-mentioned resultant with a magnitude of that is a function of the position of the flyweight(s) of the balancing device relative to the rotary shaft of the rotor.

    Rotorcraft
    7.
    发明授权
    Rotorcraft 有权

    公开(公告)号：US11713119B2

    公开(公告)日：2023-08-01

    申请号：US16396795

    申请日：2019-04-29

    申请人： Coretronic Intelligent Robotics Corporation

    发明人： I-Ta Yang ,  Ying-Chieh Chen ,  Chi-Tong Hsieh ,  Hsu-Chih Cheng

    IPC分类号： B64C27/473 ,  B64U10/13 ,  B64U30/20 ,  B64C39/02

    CPC分类号： B64C39/024 ,  B64C27/473 ,  B64U10/13 ,  B64U30/20

    摘要： A rotorcraft includes a body and a plurality of rotary-wing parts. The body has a front-end portion, a rear-end portion, two side portions, and a reference plane passing through the front-end portion, the rear-end portion, and the two side portions. The plurality of rotary-wing parts are disposed to the body. Each of the rotary-wing parts includes at least one blade and a shaft coupled to the at least one blade. The at least one blade is rotated around an axis of the shaft. An angle between the axis of the shaft and a normal line of the reference plane is between 5 and 30 degrees. The rotorcraft can provide additional lift force, to help reduce the weight of the rotorcraft.

    Lift rotor and vertical or short take-off and/or landing hybrid aerodyne comprising same
    9.
    发明授权
    Lift rotor and vertical or short take-off and/or landing hybrid aerodyne comprising same 有权

    公开(公告)号：US11685522B2

    公开(公告)日：2023-06-27

    申请号：US15749356

    申请日：2016-07-18

    申请人： INNOSTAR

    发明人： Jean-Michel Simon

    IPC分类号： B64C27/473 ,  B64C27/32 ,  B64C27/00 ,  B64C29/00 ,  B64C27/30 ,  B64C27/20

    CPC分类号： B64C27/473 ,  B64C27/008 ,  B64C27/20 ,  B64C27/30 ,  B64C27/32 ,  B64C29/0008

    摘要： The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.