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    Rotor blade assembly for bearingless rotor
    5.
    发明授权
    Rotor blade assembly for bearingless rotor 有权

    公开(公告)号：US11541995B2

    公开(公告)日：2023-01-03

    申请号：US16928605

    申请日：2020-07-14

    Applicant: LOCKHEED MARTIN CORPORATION

    Inventor： Eric S. Parsons

    IPC: B64C27/48 ,  B64C27/33 ,  B64C27/82

    Abstract: A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

    Commonly manufactured rotor blade
    7.
    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.

    ROTOR BLADE ASSEMBLY FOR BEARINGLESS ROTOR
    8.
    发明申请
    ROTOR BLADE ASSEMBLY FOR BEARINGLESS ROTOR 有权

    公开(公告)号：US20220017213A1

    公开(公告)日：2022-01-20

    申请号：US16928605

    申请日：2020-07-14

    Applicant: LOCKHEED MARTIN CORPORATION

    Inventor： Eric S. Parsons

    IPC: B64C27/33 ,  B64C27/48

    Abstract: A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

    METHOD OF STABILIZING ARTICULATED ROTOR BLADE
    9.
    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.

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