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    ROTOR BLADE USING ADAPTIVE TRAILING EDGE ASSEMBLY
    1.
    发明公开
    ROTOR BLADE USING ADAPTIVE TRAILING EDGE ASSEMBLY 审中-公开

    公开(公告)号：US20230303241A1

    公开(公告)日：2023-09-28

    申请号：US17706527

    申请日：2022-03-28

    Applicant: LOCKHEED MARTIN CORPORATION

    Inventor： Byung-Young Min

    IPC: B64C27/467 ,  B64C9/04 ,  B64C13/24

    CPC classification number: B64C27/467 ,  B64C9/04 ,  B64C13/24

    Abstract: A rotor blade assembly includes a rotor blade having inboard and outboard regions, a blade body, and an internal spar, the blade body defining leading and trailing edges. A trailing edge assembly extends from and is connected to the trailing edge, and has a trailing edge flap and an actuator configured to deploy the trailing edge flap between first and second positions. In one of the first and second positions, an upper surface of the trailing edge flap conforms in profile to an upper surface of the rotor blade, and in the other, the trailing edge flap is inclined relative to the blade. During hovering flight, at least one trailing edge flap segment is deflected to enhance hover performance. During forward flight, at least one trailing edge flap segment is either not deflected for reduced effect on forward flight or is deflected for additional thrust.

    Rotor blade using adaptive trailing edge assembly
    4.
    发明授权
    Rotor blade using adaptive trailing edge assembly 有权

    公开(公告)号：US12116118B2

    公开(公告)日：2024-10-15

    申请号：US17706527

    申请日：2022-03-28

    Applicant: LOCKHEED MARTIN CORPORATION

    Inventor： Byung-Young Min

    IPC: B64C27/467 ,  B64C9/04 ,  B64C13/24 ,  B64C27/615 ,  B64C27/72

    CPC classification number: B64C27/467 ,  B64C9/04 ,  B64C13/24 ,  B64C27/615 ,  B64C2027/7266

    Abstract: A rotor blade assembly includes a rotor blade having inboard and outboard regions, a blade body, and an internal spar, the blade body defining leading and trailing edges. A trailing edge assembly extends from and is connected to the trailing edge, and has a trailing edge flap and an actuator configured to deploy the trailing edge flap between first and second positions. In one of the first and second positions, an upper surface of the trailing edge flap conforms in profile to an upper surface of the rotor blade, and in the other, the trailing edge flap is inclined relative to the blade. During hovering flight, at least one trailing edge flap segment is deflected to enhance hover performance. During forward flight, at least one trailing edge flap segment is either not deflected for reduced effect on forward flight or is deflected for additional thrust.

    HIGH SPEED ROTOR BLADE DESIGN
    6.
    发明公开
    HIGH SPEED ROTOR BLADE DESIGN 审中-公开

    公开(公告)号：US20230322373A1

    公开(公告)日：2023-10-12

    申请号：US17706531

    申请日：2022-03-28

    Applicant: LOCKHEED MARTIN CORPORATION

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

    IPC: B64C27/473 ,  B64C27/467

    CPC classification number: B64C27/467 ,  B64C27/473

    Abstract: 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.

    High speed rotor blade design
    8.
    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

    Applicant: LOCKHEED MARTIN CORPORATION

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

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

    CPC classification number: B64C27/467 ,  B64C27/473

    Abstract: 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.

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