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    Commonly manufactured rotor blade
    1.
    发明授权
    Commonly manufactured rotor blade 有权

    公开(公告)号：US11919627B2

    公开(公告)日：2024-03-05

    申请号：US17881497

    申请日：2022-08-04

    Applicant: LOCKHEED MARTIN CORPORATION

    Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Timothy James Conti ,  Frank M. Caputo

    IPC: B64C27/48

    CPC classification number: B64C27/48

    Abstract: A method of modifying a rotor blade is provided for a rotor blade including a spar having an inboard portion with a substantially constant overall height, the inboard portion further including a top layer having a substantially constant first thickness and a bottom layer having a substantially constant second thickness. The method includes removing a root portion of the inboard portion to thereby modify the rotor blade and installing a cuff configured to couple to the rotor blade to an aircraft.

    Commonly manufactured rotor blade
    3.
    发明授权
    Commonly manufactured rotor blade 有权

    公开(公告)号：US12252240B2

    公开(公告)日：2025-03-18

    申请号：US18409652

    申请日：2024-01-10

    Applicant: Lockheed Martin Corporation

    Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Timothy James Conti ,  Frank M. Caputo

    IPC: B64C27/48

    Abstract: A rotor blade configured to be installed on a rotary wing aircraft includes a spar including an inboard portion extending from a root of the rotor blade to a first spanwise position of the rotor blade and an outboard portion meeting the inboard portion at the first spanwise position. The rotor blade further includes an upper skin and a lower skin coupled the outboard portion of the spar. The first spanwise position is defined by a most inboard point at which the upper and lower skins are coupled to the spar. The inboard portion includes a top layer, a bottom layer, and an inner cavity. The top layer has a substantially constant first thickness and the bottom layer has a substantially constant second thickness, and the distance between an outer surface of the top layer and an outer surface of the bottom layer is substantially constant.

    METHOD OF STABILIZING ARTICULATED ROTOR BLADE
    6.
    发明申请
    METHOD OF STABILIZING ARTICULATED ROTOR BLADE 有权

    公开(公告)号：US20250010983A1

    公开(公告)日：2025-01-09

    申请号：US18887678

    申请日：2024-09-17

    Applicant: Lockheed Martin Corporation

    Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Christopher M. Sutton ,  William Paul Adams ,  Timothy James Conti ,  Jared Anapolle ,  Evan Medrano

    IPC: B64C27/467 ,  B64C27/473

    Abstract: A rotor blade includes a spar with forward end, an aft end, and a substantially oval cross-section. The cross-section includes an upper portion tapering from a first thickness to a smaller, second thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end, and a lower portion tapering from a third thickness to a smaller, fourth thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end. The rotor blade further includes an upper blade skin, a lower blade skin, and a leading edge sheath.

    COMMONLY MANUFACTURED ROTOR BLADE
    8.
    发明公开
    COMMONLY MANUFACTURED ROTOR BLADE 审中-公开

    公开(公告)号：US20240140600A1

    公开(公告)日：2024-05-02

    申请号：US18409652

    申请日：2024-01-10

    Applicant: Lockheed Martin Corporation

    Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Timothy James Conti ,  Frank M. Caputo

    IPC: B64C27/48

    CPC classification number: B64C27/48

    Abstract: A rotor blade configured to be installed on a rotary wing aircraft includes a spar including an inboard portion extending from a root of the rotor blade to a first spanwise position of the rotor blade and an outboard portion meeting the inboard portion at the first spanwise position. The rotor blade further includes an upper skin and a lower skin coupled the outboard portion of the spar. The first spanwise position is defined by a most inboard point at which the upper and lower skins are coupled to the spar. The inboard portion includes a top layer, a bottom layer, and an inner cavity. The top layer has a substantially constant first thickness and the bottom layer has a substantially constant second thickness, and the distance between an outer surface of the top layer and an outer surface of the bottom layer is substantially constant.

    COMMONLY MANUFACTURED ROTOR BLADE
    9.
    发明公开
    COMMONLY MANUFACTURED ROTOR BLADE 审中-公开

    公开(公告)号：US20240043116A1

    公开(公告)日：2024-02-08

    申请号：US17881497

    申请日：2022-08-04

    Applicant: LOCKHEED MARTIN CORPORATION

    Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Timothy James Conti ,  Frank M. Caputo

    IPC: B64C27/48

    CPC classification number: B64C27/48

    Abstract: A method of modifying a rotor blade is provided for a rotor blade including a spar having an inboard portion with a substantially constant overall height, the inboard portion further including a top layer having a substantially constant first thickness and a bottom layer having a substantially constant second thickness. The method includes removing a root portion of the inboard portion to thereby modify the rotor blade and installing a cuff configured to couple to the rotor blade to an aircraft.

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